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JPL PUBLICATION 77-70 An InterstellarPrecursor Mission (NASA-CR-156152) Al fIlERSTELLAR PRECURSOR t178-21173 MISSION (Jet Propulsion Lab.) 111 p HC A06/UF A01 CSCL 22A Unclas _G3/12 06616 REPRODUCED BY NATIONAL TECHNICAL INFORMATION SERVICE U S DEPARTMENT OFCOMMERCE SPRINGFIELD, VA. 22161 National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology - Pasadena, California https://ntrs.nasa.gov/search.jsp?R=19780013230 2020-03-22T03:54:47+00:00Z
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An InterstellarPrecursor Mission

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Page 1: An InterstellarPrecursor Mission

JPL PUBLICATION 77-70

An InterstellarPrecursor Mission (NASA-CR-156152) Al fIlERSTELLAR PRECURSOR t178-21173 MISSION (Jet Propulsion Lab) 111 p HC A06UF A01 CSCL 22A

Unclas _G312 06616

REPRODUCEDBY NATIONAL TECHNICAL INFORMATION SERVICE

U S DEPARTMENT OF COMMERCE SPRINGFIELD VA 22161

National Aeronautics and Space Administration

Jet Propulsion Laboratory California Institute of Technology

- Pasadena California

httpsntrsnasagovsearchjspR=19780013230 2020-03-22T035447+0000Z

NOTICE

THIS DOCUMENT HAS BEEN REPRODUCED

FROM THE BEST COPY FURNISHED US BY

THE SPONSORING AGENCY ALTHOUGH IT

IS RECOGNIZED THAT CERTAIN PORTIONS

ARE ILLEGIBLE IT IS BEING RELEASED

IN THE INTEREST OF MAKING AVAILABLE

AS MUCH INFORMATION AS POSSIBLE

JPL PUBLICATION 77-70

An Interstellar Precursor Mission

L D J affe C Ivie J-- Lewis R Lipes H N Norton J W Stearns L D Stimpson P Weissman

October 30 1977

National Aeronautics and Space Administration

Jet Propulsion Laboratory California Institute of Technology Pasadena California

Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration

77-70

PREFACE-

The work described in this report was performed by the Earthand Space

Sciences Systems Telecommunications Science and Engineering Control and

Energy Conversion Applied Mechanics and Information Systems Divisions of

the Jet Propulsion Laboratory for NASA Ames Research Center under NASA

OAST Program 790 Space Systems Studies Stanley R Sadin sponsor

iii

77-70

ABSTRACT

A mntsion out of the planetary system with launch about the year 2000

could provide valuable scientific data as well as test some of the technology

for a later mission to another star A mission to a star is not expected to

be practical around 2000 because the flight time with the technology then

available is expected to exceed 10000 yr

Primary scientific objectives for the precursor mission concern

characteristics of the heliopause the interstellar medium stellar distances

(by parallax measurements) low energy cosmic rays interplanetary gas distrishy

bution and mass of the solar system Secondary objectives include investigashy

tion of Pluto Candidate science instruments are suggested

The mission should extend to 500-1000 AU from the sun A heliocentric

hyperbolic escape velocity of 50-100 kms or more is needed to attain this

distance within a reasonable mission duration The trajectory should be

toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy

ter can be included A second mission targeted parallel to the solar axis

would also be worthwhile

The mission duration is 20 years with an extended mission to a total

of 50 years A system using 1 or 2 stages of nuclear electric propulsion was

selected as a possible baseline The most promising alternatives are ultralight

solar sails or laser sailing with the lasers in Earth orbit for example

The NEP baseline design allows the option of carrying a Pluto orbiter as a

daughter spacecraft

Within the limited depth of this study individual spacecraft systems

for the mission are considered technology requirements and problem areas

noted and a number of recommendations made for technology study and advanced

development The most critical technology needs include attainment of 50-yr

spacecraft lifetime and development of a long-life NEP system

iv

77-70

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

vi

77-70

TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

vii

77-70

Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

viii

77-70

Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

ix

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

x

77-70

INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

1

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

77-70

STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

77-70

This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

77-70

SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

5

77-70

reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

8

77-70

by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

9

77-70

measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

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and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

11

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and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

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(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

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A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

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around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

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A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

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300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

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hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

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After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

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MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

77-70

assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

77-70

system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

48

77-70

Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

49

77-70

on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

77-70

70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

51

77-70

Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

52

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

53

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

54

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

77-70

RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

59

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

61

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

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77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

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own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

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APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

r00465 3811414 5lf45 1IA0S075 nn441 U0234

i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln

srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0

g0nn03 snonI

q

fnniAg onnu53

qnnil6 0n0itl

5fnlnrlq 5n014nq tfl030 q

5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839

5100 5200

5403251 5508794

500328 500322

5401959 5507502

9003P8 900322

540I015 S001PR R506r5P 900322

53qq0 5504933

qn0i9g nn0pn

K9q7469 530O

50nnxpQ 900322

59464q 550n187

3n9 5nn39

5300 5400

5614336 5719877

500316 900310

5613044 5718589

500316 500310

5612100 5717641

r00316 500310

r610479 5716016

g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

q6n07l4 5711PAn

5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

90035 5n0p9 090q4 500289 5n024 500270

rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861

500305 g0olqQo RnOq4 500280 50OP4 90027Q

21555 0pflo S826in 6138166 649701 614q239

500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP

50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q

R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4

5nnxnK srn Q gn09Q4 500n0q nnf04

gnnon

PRW flr 03W77 nArr 7

V-INFINITY = 600 KMS

T - YRS 0=

RAn 1AU

VEL q =

RAr) 3 AU

VEL n =

PAn 5 AU

Vft n = 10

PA) Atl

VFL a = PAn

20 MI VEL PAMn

5p fU VVl

00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60

56979 83199

6P5413 617524

55061 8110l

695863 617714 A1477

A61246324q76 A17P00 807 o 0

APA17 AInO

F56o A14l1

6pov7q 617AAe

7r Qt11171

61nnpQ 615RA7

80 100

10910( 134926

61340l 610860

10A043 133R4q

613R2 610047

lo7177 1st3e1

61361 11flnn

tOAgqo 1502c

A1Po n67or 611AI3940611non

e137n i155 13 flW s

AlAq0 AinIft

120 140

160656 186325

609134 607884

15057P 185236

60q2n5607Q30

1S8872 jAlrp7

600opg07aA0

157O014 IPI1r7

6flQO 008113

J-1N IRinfn

n031 6n0S6

Ierl 14Ut

6mnn An7017

160 180

211940 237538

606q36 6n6103

210895 236441

6n6072 6n6p2

Pjn130 PA5710

6n60q5 6n6940

rnnoo P34654

A7nn O9Apt

20A467 p 43Q30

A7nq1 606P7

11fn PAn I

AnSnSn AnAfl

200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240

28A637 314157

605101 604688

28753f 31305

6n510 6047n5

P6n05 619131 1193I6fl4

2897n0 i 6

65103 An311206

p4tr5 n-ins

6n9168 An4746

5nptSn A

-tpo Anq1 n AA0471

260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340

365150 3Q0628 416096 441554

6n4036 603773 6n3543 603330

364044 389521 41407 440445

6n4048 603784 603592 613348

363031 388780 41P4t5

UIQ0f

6n4nti f 61370 6n3590

An315A

3876A7 414j31n 43q41U

A1u1AOtq Aen 60n60 A1A62

IAJ61o R866P4

u1pnrq u37T 4 a

6n4n8 6fl1I 6ndeg9 A370

16un 3A611 41I-Afln

41in1

AnflnAA Anfnlp sMIn 71 6n3A

360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa

380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480

568742 594162 619579

602594 6024A3 602382

56762P 5P3o5 618466

6n29q 6n2408 6n2386

566p8f 9inf deg17719

6112603 6fn2qj6n2980

966qq 5011j9616P7

Anp6np 6P406 AnPQI

R645n 58o53 e135i

An2613

69Rn9109

R65hn qnoA=IA

6fn9613 Annl 6m Q

o 500 520

644991 67039q

602P88 61 22Nt

643R77 66q0R2

e0P2QP 6n22n9

641126 66A533

A6p295 6129oA

641035 6673140

A62paq AnP1

64degnr 666145

612311 6npois

Aqnq4n 6egna

An1 An1 7

-J 0

540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n

721206 746605

60207 601)77

720092 749412

602050 6O10O

71031R 744736

6npn0p 601ORP

71140 743S35

60n15 Anlpq

7164P7 74P31

A9nq 69t1A0

716455 74 17I

6nn6n 6nlno

600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640

707394 822784

601851 601704

79627A 82166q

601A54 6n17q7

705p4 n2024

61n186 611708

7q4 p07fl7

n 6I0t85q Anln01

70368 lP46

601n61 A1n14

7qP4k7 ct77

6118nl 60inn

660 680

84173 873559

601741 6016q0

847057 872441

6n1743 6n1692

A4Ao AviAv

6n1745 6016qu

A49n 870477

Af1747 An1A06

A4314U pAQP99

snstyn 601AO

A4lll 86R451

An19i 6 17n0

700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760

949706 975004

601559 601514

948580 97096A

60197 601516

9u7983 Q73plO

601558 AnlIr17

046618 071)09

6n11560 An 191 a

45147 07071n

6nlq6 611spl

040MA4A6158 Q68nn finICD3

7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840

1051210 1076583

601405 601372

1050091 1075466

6n1406 6n1373

ln4335 1074707

6nln7 0n1374

1048116 1073487

n14nq tnuARPn An1W76 107105

An1411 611177

10481c7 I071157

Af1012 Aflt1A

860 880

1101954 1127324

601340 601310

1100837 1126206

601342 601311

130007A 11Pq447

601141 6131P

10857 1124PP5

6n1144 6n1314

loq7961ll22q2A

601146 6n1 tq

IQA4A 1121838

An14 eniI7

900 920

1152692 1178060

6012R1 601254

1151579 117694P

6012R3 601255

1150A81 1176183

60128p3 6n1256

1j4q 3 11749qq

6nIP9 60157

11P n 1173653

6IPA6 60158

1147176 117P9916

An1 4 6019 0

940 960

1203426 1228791

601227 601202

1202308 1227673

601228 601203

12019q 12P6013

601P20 60lpo4

12003P4 122i60

601231 An6p125

xo001 12p4376

601039 6n1006

11QT899 1P21t5

6n1943 61nl9

980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O

PRW DATF 011077 PArr Is

V-TNFINITY =600 KMS

S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL

1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql

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r PUBLICATION 77-70

Page 2: An InterstellarPrecursor Mission

NOTICE

THIS DOCUMENT HAS BEEN REPRODUCED

FROM THE BEST COPY FURNISHED US BY

THE SPONSORING AGENCY ALTHOUGH IT

IS RECOGNIZED THAT CERTAIN PORTIONS

ARE ILLEGIBLE IT IS BEING RELEASED

IN THE INTEREST OF MAKING AVAILABLE

AS MUCH INFORMATION AS POSSIBLE

JPL PUBLICATION 77-70

An Interstellar Precursor Mission

L D J affe C Ivie J-- Lewis R Lipes H N Norton J W Stearns L D Stimpson P Weissman

October 30 1977

National Aeronautics and Space Administration

Jet Propulsion Laboratory California Institute of Technology Pasadena California

Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration

77-70

PREFACE-

The work described in this report was performed by the Earthand Space

Sciences Systems Telecommunications Science and Engineering Control and

Energy Conversion Applied Mechanics and Information Systems Divisions of

the Jet Propulsion Laboratory for NASA Ames Research Center under NASA

OAST Program 790 Space Systems Studies Stanley R Sadin sponsor

iii

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ABSTRACT

A mntsion out of the planetary system with launch about the year 2000

could provide valuable scientific data as well as test some of the technology

for a later mission to another star A mission to a star is not expected to

be practical around 2000 because the flight time with the technology then

available is expected to exceed 10000 yr

Primary scientific objectives for the precursor mission concern

characteristics of the heliopause the interstellar medium stellar distances

(by parallax measurements) low energy cosmic rays interplanetary gas distrishy

bution and mass of the solar system Secondary objectives include investigashy

tion of Pluto Candidate science instruments are suggested

The mission should extend to 500-1000 AU from the sun A heliocentric

hyperbolic escape velocity of 50-100 kms or more is needed to attain this

distance within a reasonable mission duration The trajectory should be

toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy

ter can be included A second mission targeted parallel to the solar axis

would also be worthwhile

The mission duration is 20 years with an extended mission to a total

of 50 years A system using 1 or 2 stages of nuclear electric propulsion was

selected as a possible baseline The most promising alternatives are ultralight

solar sails or laser sailing with the lasers in Earth orbit for example

The NEP baseline design allows the option of carrying a Pluto orbiter as a

daughter spacecraft

Within the limited depth of this study individual spacecraft systems

for the mission are considered technology requirements and problem areas

noted and a number of recommendations made for technology study and advanced

development The most critical technology needs include attainment of 50-yr

spacecraft lifetime and development of a long-life NEP system

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RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

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TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

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Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

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Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

x

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INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

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This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

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SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

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reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

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by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

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measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

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and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

11

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and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

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(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

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A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

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around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

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A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

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300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

77-70

hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

77-70

After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

77-70

MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

77-70

According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

77-70

DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

77-70

assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

77-70

system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

48

77-70

Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

49

77-70

on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

77-70

70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

51

77-70

Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

52

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

53

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

54

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

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RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

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77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

79

77-70

II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

80

77-70

This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

77-70

own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

82

77-70

APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

r00465 3811414 5lf45 1IA0S075 nn441 U0234

i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln

srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0

g0nn03 snonI

q

fnniAg onnu53

qnnil6 0n0itl

5fnlnrlq 5n014nq tfl030 q

5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839

5100 5200

5403251 5508794

500328 500322

5401959 5507502

9003P8 900322

540I015 S001PR R506r5P 900322

53qq0 5504933

qn0i9g nn0pn

K9q7469 530O

50nnxpQ 900322

59464q 550n187

3n9 5nn39

5300 5400

5614336 5719877

500316 900310

5613044 5718589

500316 500310

5612100 5717641

r00316 500310

r610479 5716016

g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

q6n07l4 5711PAn

5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

90035 5n0p9 090q4 500289 5n024 500270

rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861

500305 g0olqQo RnOq4 500280 50OP4 90027Q

21555 0pflo S826in 6138166 649701 614q239

500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP

50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q

R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4

5nnxnK srn Q gn09Q4 500n0q nnf04

gnnon

PRW flr 03W77 nArr 7

V-INFINITY = 600 KMS

T - YRS 0=

RAn 1AU

VEL q =

RAr) 3 AU

VEL n =

PAn 5 AU

Vft n = 10

PA) Atl

VFL a = PAn

20 MI VEL PAMn

5p fU VVl

00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60

56979 83199

6P5413 617524

55061 8110l

695863 617714 A1477

A61246324q76 A17P00 807 o 0

APA17 AInO

F56o A14l1

6pov7q 617AAe

7r Qt11171

61nnpQ 615RA7

80 100

10910( 134926

61340l 610860

10A043 133R4q

613R2 610047

lo7177 1st3e1

61361 11flnn

tOAgqo 1502c

A1Po n67or 611AI3940611non

e137n i155 13 flW s

AlAq0 AinIft

120 140

160656 186325

609134 607884

15057P 185236

60q2n5607Q30

1S8872 jAlrp7

600opg07aA0

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r PUBLICATION 77-70

Page 3: An InterstellarPrecursor Mission

JPL PUBLICATION 77-70

An Interstellar Precursor Mission

L D J affe C Ivie J-- Lewis R Lipes H N Norton J W Stearns L D Stimpson P Weissman

October 30 1977

National Aeronautics and Space Administration

Jet Propulsion Laboratory California Institute of Technology Pasadena California

Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration

77-70

PREFACE-

The work described in this report was performed by the Earthand Space

Sciences Systems Telecommunications Science and Engineering Control and

Energy Conversion Applied Mechanics and Information Systems Divisions of

the Jet Propulsion Laboratory for NASA Ames Research Center under NASA

OAST Program 790 Space Systems Studies Stanley R Sadin sponsor

iii

77-70

ABSTRACT

A mntsion out of the planetary system with launch about the year 2000

could provide valuable scientific data as well as test some of the technology

for a later mission to another star A mission to a star is not expected to

be practical around 2000 because the flight time with the technology then

available is expected to exceed 10000 yr

Primary scientific objectives for the precursor mission concern

characteristics of the heliopause the interstellar medium stellar distances

(by parallax measurements) low energy cosmic rays interplanetary gas distrishy

bution and mass of the solar system Secondary objectives include investigashy

tion of Pluto Candidate science instruments are suggested

The mission should extend to 500-1000 AU from the sun A heliocentric

hyperbolic escape velocity of 50-100 kms or more is needed to attain this

distance within a reasonable mission duration The trajectory should be

toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy

ter can be included A second mission targeted parallel to the solar axis

would also be worthwhile

The mission duration is 20 years with an extended mission to a total

of 50 years A system using 1 or 2 stages of nuclear electric propulsion was

selected as a possible baseline The most promising alternatives are ultralight

solar sails or laser sailing with the lasers in Earth orbit for example

The NEP baseline design allows the option of carrying a Pluto orbiter as a

daughter spacecraft

Within the limited depth of this study individual spacecraft systems

for the mission are considered technology requirements and problem areas

noted and a number of recommendations made for technology study and advanced

development The most critical technology needs include attainment of 50-yr

spacecraft lifetime and development of a long-life NEP system

iv

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RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

vi

77-70

TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

vii

77-70

Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

viii

77-70

Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

ix

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

x

77-70

INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

1

77-70

Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

77-70

This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

77-70

SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

5

77-70

reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

8

77-70

by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

9

77-70

measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

77-70

and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

11

77-70

and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

77-70

(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

77-70

TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

77-70

Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

77-70

TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

77-70

TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

77-70

at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

77-70

A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

77-70

be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

77-70

high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

77-70

around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

77-70

A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

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300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

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hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

77-70

After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

77-70

MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

77-70

assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

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system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

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Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

49

77-70

on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

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70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

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Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

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RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

67

77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

77-70

own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

82

77-70

APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

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r PUBLICATION 77-70

Page 4: An InterstellarPrecursor Mission

Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration

77-70

PREFACE-

The work described in this report was performed by the Earthand Space

Sciences Systems Telecommunications Science and Engineering Control and

Energy Conversion Applied Mechanics and Information Systems Divisions of

the Jet Propulsion Laboratory for NASA Ames Research Center under NASA

OAST Program 790 Space Systems Studies Stanley R Sadin sponsor

iii

77-70

ABSTRACT

A mntsion out of the planetary system with launch about the year 2000

could provide valuable scientific data as well as test some of the technology

for a later mission to another star A mission to a star is not expected to

be practical around 2000 because the flight time with the technology then

available is expected to exceed 10000 yr

Primary scientific objectives for the precursor mission concern

characteristics of the heliopause the interstellar medium stellar distances

(by parallax measurements) low energy cosmic rays interplanetary gas distrishy

bution and mass of the solar system Secondary objectives include investigashy

tion of Pluto Candidate science instruments are suggested

The mission should extend to 500-1000 AU from the sun A heliocentric

hyperbolic escape velocity of 50-100 kms or more is needed to attain this

distance within a reasonable mission duration The trajectory should be

toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy

ter can be included A second mission targeted parallel to the solar axis

would also be worthwhile

The mission duration is 20 years with an extended mission to a total

of 50 years A system using 1 or 2 stages of nuclear electric propulsion was

selected as a possible baseline The most promising alternatives are ultralight

solar sails or laser sailing with the lasers in Earth orbit for example

The NEP baseline design allows the option of carrying a Pluto orbiter as a

daughter spacecraft

Within the limited depth of this study individual spacecraft systems

for the mission are considered technology requirements and problem areas

noted and a number of recommendations made for technology study and advanced

development The most critical technology needs include attainment of 50-yr

spacecraft lifetime and development of a long-life NEP system

iv

77-70

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

vi

77-70

TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

vii

77-70

Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

viii

77-70

Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

ix

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

x

77-70

INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

1

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

77-70

STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

77-70

This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

77-70

SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

5

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reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

8

77-70

by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

9

77-70

measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

77-70

and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

11

77-70

and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

77-70

(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

77-70

Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

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A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

77-70

be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

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around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

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A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

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300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

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hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

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After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

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MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

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assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

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system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

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Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

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on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

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70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

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Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

77-70

RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

61

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

64

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

67

77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

69

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

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own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

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APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

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r PUBLICATION 77-70

Page 5: An InterstellarPrecursor Mission

77-70

PREFACE-

The work described in this report was performed by the Earthand Space

Sciences Systems Telecommunications Science and Engineering Control and

Energy Conversion Applied Mechanics and Information Systems Divisions of

the Jet Propulsion Laboratory for NASA Ames Research Center under NASA

OAST Program 790 Space Systems Studies Stanley R Sadin sponsor

iii

77-70

ABSTRACT

A mntsion out of the planetary system with launch about the year 2000

could provide valuable scientific data as well as test some of the technology

for a later mission to another star A mission to a star is not expected to

be practical around 2000 because the flight time with the technology then

available is expected to exceed 10000 yr

Primary scientific objectives for the precursor mission concern

characteristics of the heliopause the interstellar medium stellar distances

(by parallax measurements) low energy cosmic rays interplanetary gas distrishy

bution and mass of the solar system Secondary objectives include investigashy

tion of Pluto Candidate science instruments are suggested

The mission should extend to 500-1000 AU from the sun A heliocentric

hyperbolic escape velocity of 50-100 kms or more is needed to attain this

distance within a reasonable mission duration The trajectory should be

toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy

ter can be included A second mission targeted parallel to the solar axis

would also be worthwhile

The mission duration is 20 years with an extended mission to a total

of 50 years A system using 1 or 2 stages of nuclear electric propulsion was

selected as a possible baseline The most promising alternatives are ultralight

solar sails or laser sailing with the lasers in Earth orbit for example

The NEP baseline design allows the option of carrying a Pluto orbiter as a

daughter spacecraft

Within the limited depth of this study individual spacecraft systems

for the mission are considered technology requirements and problem areas

noted and a number of recommendations made for technology study and advanced

development The most critical technology needs include attainment of 50-yr

spacecraft lifetime and development of a long-life NEP system

iv

77-70

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

vi

77-70

TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

vii

77-70

Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

viii

77-70

Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

ix

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

x

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INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

1

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

77-70

This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

77-70

SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

5

77-70

reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

8

77-70

by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

9

77-70

measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

77-70

and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

11

77-70

and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

77-70

(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

77-70

A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

77-70

high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

77-70

around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

77-70

Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

77-70

A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

77-70

300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

77-70

TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

77-70

If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

77-70

hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

77-70

MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

77-70

After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

77-70

MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

77-70

TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

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assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

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system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

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Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

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on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

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70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

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Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

77-70

RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

67

77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

69

77-70

orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

70

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

71

77-70

REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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77-70

A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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77-70

A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

74

77-70

APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

76

77-70

APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

77

77-70

APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

78

77-70

CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

79

77-70

II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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77-70

This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

77-70

own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

82

77-70

APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

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90017P 500364 509(05650O340 500342 50033-5i

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50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

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53qq0 5504933

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5300 5400

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500316 900310

5613044 5718589

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r00316 500310

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g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

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5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

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V-INFINITY = 600 KMS

T - YRS 0=

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20 MI VEL PAMn

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PRW DATF 011077 PArr Is

V-TNFINITY =600 KMS

S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL

1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql

2400 3053632 600484 3052911 6n0484 30n91746 6n0484 l0fin4QA AiNn44 304010- AnnPS 104710 AftW 2900 3180302 600469 317q1ni 6n0469 1179416 6P046i5 3177167 60fn465 31776q 6noM469 17Nqvl 6nAlA6 2600 3306969 600447 3309846 6n0447 lln n] 6n044 33n183 Ann447 l300441 6n0 44 Al0Wl 6AM44 2700 3433630 6n0410 343o5nA 6n0411 A411743 6n0431 14304ql 6n04ll X4Pqnqi 6n-nAol 14PIP67 6Mnl 2800 3560289 600419 3559167 6n0419 19940P 6nnulq 3597191 Ann416 iq-q74A 6nfn416 is19in Annh16 2c)00 3686944 600401 3685821 6n04n1 36Arin97 6An4nl 368l06 Ann0n01 6AP4ni 6nn4ni1 69n9RP 6nnaop 30-00 3813597 600388 3812476 600i g IR11710 6nnARP 3stn40 Anl03PA 3PoqOiP 6fl0ARq An I01 6 n R shy3100 394n247 600175 393q126 6n0379 3918136n Afl037 3Q37108 Ann3759 T0 67 in3tqqo A n6 shy3200 4066895 6n0363 4065773 6n0i64 4069n07 6n0164 4n63799 6nn364 406P34A 6nnIA4 406m4Aq AnnMmA 4 3300 41g3940 6 00192 4192ulP 6n0353 41q1652 6n0193 419n4no 6n-nlq3 418PqAQ 60nlql 4I871 n fion l Cgt 3400 4320183 6n0342 431Q061 600147 411 95 6n0142 4117n4l 60034P u319611 6nMlu 41117A 6ftnl l 3500 4446824 6n0332 4449i70 600332 44Q36 600133 44416A3 6n0lll 444PP7 6innil 401A 6nnl l 3600 4573462 600323 4572341 6n0123 457t975 6n0121 4-i70321 fi0n03 49fiAgo 6noiP4 4r6AQQA 6mqI0 3700 4700099 6n0314 469R97A 6n0115 46Q9211 An0319 46gfi9Rf AnnII 4699ri41 6nO19 4fqNAOI0 Aftt 15 3800 4826739 6n0106 4829613 6n0306 USP4A46 6n0 0O6 482lqg3 An0WM6 UAP0177 An0IO7 4APnPUq 6nnmn7 3900 4953368 600298 4992246 6n0298 4q91480 A007qq4 Q90226 An04g Uq4PRnn 6nn0Q 404AR74 finnoaq 4000 5080000 600291 507887A 6n0291 n7811p 60091 5076857 An0p t qn943n 60nQt q071400 Annio1 4100 5206630 600284 920950A 6n0P84 Pn474P An0P94 5PO14R7 60nPA4 9pnPO0 6nnI84 900nlll Ann A4 4200 5333259 600277 5332137 600p77 9111371 6n0777 513nI16 60$0P77 3PA6Q6 Anfti77 qlA744 Fnni 8 4300 5459886 600P71 5458769 6n0271 9497998 6nnP71 9456743 6n0p71 r491PI 60ngt71 qKlArfinK ndegoV 1 4400 5586513 600269 5985391 6n0269 9qA4624 60DP6r Sr31An 600PA5 q58194A AnO61K qq7QqA- 6nnAc 4S00 5713138 600P59 571P016 6n0299 r71IP4q 60059 870Q04 O60n~qq $7A577 6nn q -i7nf6nu 6inn-Q 4600 5839761 6n0P53 583863q 6n0293 qA37871 600P3 536617 f0npqi qRj9Iqf 6n09 9PIPPI 6nn o~ 4704 5966364 600248 59)6 1262 60024a 5Q644995 6nnP4S 9503P30 Annp p qO6IRIA An0gt4A qQ9nA4A AnA 4A 480o 6093005 600243 6091881 6n0243 6n91116 6nnP43 6089A6n AnnP4q3 6nA37 66nP4 6na4R6 6nno4N 4900 6219625 600238 621R501 6nn238 6pi7717 60nP3P 6pt6461 6lOnplA Aplqnq 6nno x8 API 071 AftnOle 5000 6346245 600233 6345121 6n0213 6144$6 600P31 614310O 600P11 614167R 6nnoll Al3n6AA fitn0ll 5t00 6472863 6002P8 6471741 6n0228 647nq74 600P2A 646o71A fi00PPS f468Ql 600PQ A46Aino 600g

S 5200 6599481 600224 6998358 6n02P4 6rQ7591l 60024 69q6339 6nnPP4 Ati40na 6noP04 fi9Q9011 Ann4 530 707 606724979 6n0P20 6724P08 60npp0 672PQ91 6nnP 0 67Plr 6n0nln0 671n l~ Aftdegni9 5400 6852713 600216 68q159n 6n02t6 6A9n824 60016 694q567 A00P16 6A4914n 6nn0gt16 6n4At Ann 16 5500 6979327 60023P 697820r 6n02t2 607743A 600pip 6Q76181 6nnP12 -6q7475i4 6n0OgtIP 607p74A 6nplp

2 5600 7105941 600208 7104819 6n0208 71g409P 6no n8 71nP709 AnfnPnA 71n136A 6nnpnR 7nQ0j9A 6ftnoAR 4 - 5700 7232555 6n0204 723143P 6n0n4 7P3066t 6n0p04 7p2 QnA 60npn4 7PP7Q n 60flp05 7r 6Anln

Ir 5800 7359167 600201 7358049 6fl001 71q7P7A 600701 7356021 6nnpni 71949qgt 6nMint 199rPf 6nqgtA082 5900 7485779 6n0197 7484656 6n0ign 7483A89 finnlqA 749263P fin0nI R 7491201 6no|a 7470|A 6n~nlqn

S 6000 7612390 6n0194 7611267 600104 76|A900 6n0194 760OP43 A0njQ4 76n7814 fi0n1o4 76n971) Annin4

r PUBLICATION 77-70

Page 6: An InterstellarPrecursor Mission

77-70

ABSTRACT

A mntsion out of the planetary system with launch about the year 2000

could provide valuable scientific data as well as test some of the technology

for a later mission to another star A mission to a star is not expected to

be practical around 2000 because the flight time with the technology then

available is expected to exceed 10000 yr

Primary scientific objectives for the precursor mission concern

characteristics of the heliopause the interstellar medium stellar distances

(by parallax measurements) low energy cosmic rays interplanetary gas distrishy

bution and mass of the solar system Secondary objectives include investigashy

tion of Pluto Candidate science instruments are suggested

The mission should extend to 500-1000 AU from the sun A heliocentric

hyperbolic escape velocity of 50-100 kms or more is needed to attain this

distance within a reasonable mission duration The trajectory should be

toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy

ter can be included A second mission targeted parallel to the solar axis

would also be worthwhile

The mission duration is 20 years with an extended mission to a total

of 50 years A system using 1 or 2 stages of nuclear electric propulsion was

selected as a possible baseline The most promising alternatives are ultralight

solar sails or laser sailing with the lasers in Earth orbit for example

The NEP baseline design allows the option of carrying a Pluto orbiter as a

daughter spacecraft

Within the limited depth of this study individual spacecraft systems

for the mission are considered technology requirements and problem areas

noted and a number of recommendations made for technology study and advanced

development The most critical technology needs include attainment of 50-yr

spacecraft lifetime and development of a long-life NEP system

iv

77-70

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

vi

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TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

vii

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Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

viii

77-70

Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

ix

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

x

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INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

1

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

77-70

This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

77-70

SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

5

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reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

8

77-70

by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

9

77-70

measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

77-70

and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

11

77-70

and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

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(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

77-70

A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

77-70

around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

77-70

A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

77-70

300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

77-70

TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

77-70

If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

77-70

hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

77-70

MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

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After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

77-70

MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

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assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

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system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

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Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

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on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

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70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

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Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

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RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

67

77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

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own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

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APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

r00465 3811414 5lf45 1IA0S075 nn441 U0234

i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln

srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0

g0nn03 snonI

q

fnniAg onnu53

qnnil6 0n0itl

5fnlnrlq 5n014nq tfl030 q

5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839

5100 5200

5403251 5508794

500328 500322

5401959 5507502

9003P8 900322

540I015 S001PR R506r5P 900322

53qq0 5504933

qn0i9g nn0pn

K9q7469 530O

50nnxpQ 900322

59464q 550n187

3n9 5nn39

5300 5400

5614336 5719877

500316 900310

5613044 5718589

500316 500310

5612100 5717641

r00316 500310

r610479 5716016

g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

q6n07l4 5711PAn

5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

90035 5n0p9 090q4 500289 5n024 500270

rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861

500305 g0olqQo RnOq4 500280 50OP4 90027Q

21555 0pflo S826in 6138166 649701 614q239

500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP

50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q

R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4

5nnxnK srn Q gn09Q4 500n0q nnf04

gnnon

PRW flr 03W77 nArr 7

V-INFINITY = 600 KMS

T - YRS 0=

RAn 1AU

VEL q =

RAr) 3 AU

VEL n =

PAn 5 AU

Vft n = 10

PA) Atl

VFL a = PAn

20 MI VEL PAMn

5p fU VVl

00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60

56979 83199

6P5413 617524

55061 8110l

695863 617714 A1477

A61246324q76 A17P00 807 o 0

APA17 AInO

F56o A14l1

6pov7q 617AAe

7r Qt11171

61nnpQ 615RA7

80 100

10910( 134926

61340l 610860

10A043 133R4q

613R2 610047

lo7177 1st3e1

61361 11flnn

tOAgqo 1502c

A1Po n67or 611AI3940611non

e137n i155 13 flW s

AlAq0 AinIft

120 140

160656 186325

609134 607884

15057P 185236

60q2n5607Q30

1S8872 jAlrp7

600opg07aA0

157O014 IPI1r7

6flQO 008113

J-1N IRinfn

n031 6n0S6

Ierl 14Ut

6mnn An7017

160 180

211940 237538

606q36 6n6103

210895 236441

6n6072 6n6p2

Pjn130 PA5710

6n60q5 6n6940

rnnoo P34654

A7nn O9Apt

20A467 p 43Q30

A7nq1 606P7

11fn PAn I

AnSnSn AnAfl

200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240

28A637 314157

605101 604688

28753f 31305

6n510 6047n5

P6n05 619131 1193I6fl4

2897n0 i 6

65103 An311206

p4tr5 n-ins

6n9168 An4746

5nptSn A

-tpo Anq1 n AA0471

260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340

365150 3Q0628 416096 441554

6n4036 603773 6n3543 603330

364044 389521 41407 440445

6n4048 603784 603592 613348

363031 388780 41P4t5

UIQ0f

6n4nti f 61370 6n3590

An315A

3876A7 414j31n 43q41U

A1u1AOtq Aen 60n60 A1A62

IAJ61o R866P4

u1pnrq u37T 4 a

6n4n8 6fl1I 6ndeg9 A370

16un 3A611 41I-Afln

41in1

AnflnAA Anfnlp sMIn 71 6n3A

360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa

380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480

568742 594162 619579

602594 6024A3 602382

56762P 5P3o5 618466

6n29q 6n2408 6n2386

566p8f 9inf deg17719

6112603 6fn2qj6n2980

966qq 5011j9616P7

Anp6np 6P406 AnPQI

R645n 58o53 e135i

An2613

69Rn9109

R65hn qnoA=IA

6fn9613 Annl 6m Q

o 500 520

644991 67039q

602P88 61 22Nt

643R77 66q0R2

e0P2QP 6n22n9

641126 66A533

A6p295 6129oA

641035 6673140

A62paq AnP1

64degnr 666145

612311 6npois

Aqnq4n 6egna

An1 An1 7

-J 0

540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n

721206 746605

60207 601)77

720092 749412

602050 6O10O

71031R 744736

6npn0p 601ORP

71140 743S35

60n15 Anlpq

7164P7 74P31

A9nq 69t1A0

716455 74 17I

6nn6n 6nlno

600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640

707394 822784

601851 601704

79627A 82166q

601A54 6n17q7

705p4 n2024

61n186 611708

7q4 p07fl7

n 6I0t85q Anln01

70368 lP46

601n61 A1n14

7qP4k7 ct77

6118nl 60inn

660 680

84173 873559

601741 6016q0

847057 872441

6n1743 6n1692

A4Ao AviAv

6n1745 6016qu

A49n 870477

Af1747 An1A06

A4314U pAQP99

snstyn 601AO

A4lll 86R451

An19i 6 17n0

700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760

949706 975004

601559 601514

948580 97096A

60197 601516

9u7983 Q73plO

601558 AnlIr17

046618 071)09

6n11560 An 191 a

45147 07071n

6nlq6 611spl

040MA4A6158 Q68nn finICD3

7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840

1051210 1076583

601405 601372

1050091 1075466

6n1406 6n1373

ln4335 1074707

6nln7 0n1374

1048116 1073487

n14nq tnuARPn An1W76 107105

An1411 611177

10481c7 I071157

Af1012 Aflt1A

860 880

1101954 1127324

601340 601310

1100837 1126206

601342 601311

130007A 11Pq447

601141 6131P

10857 1124PP5

6n1144 6n1314

loq7961ll22q2A

601146 6n1 tq

IQA4A 1121838

An14 eniI7

900 920

1152692 1178060

6012R1 601254

1151579 117694P

6012R3 601255

1150A81 1176183

60128p3 6n1256

1j4q 3 11749qq

6nIP9 60157

11P n 1173653

6IPA6 60158

1147176 117P9916

An1 4 6019 0

940 960

1203426 1228791

601227 601202

1202308 1227673

601228 601203

12019q 12P6013

601P20 60lpo4

12003P4 122i60

601231 An6p125

xo001 12p4376

601039 6n1006

11QT899 1P21t5

6n1943 61nl9

980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O

PRW DATF 011077 PArr Is

V-TNFINITY =600 KMS

S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL

1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql

2400 3053632 600484 3052911 6n0484 30n91746 6n0484 l0fin4QA AiNn44 304010- AnnPS 104710 AftW 2900 3180302 600469 317q1ni 6n0469 1179416 6P046i5 3177167 60fn465 31776q 6noM469 17Nqvl 6nAlA6 2600 3306969 600447 3309846 6n0447 lln n] 6n044 33n183 Ann447 l300441 6n0 44 Al0Wl 6AM44 2700 3433630 6n0410 343o5nA 6n0411 A411743 6n0431 14304ql 6n04ll X4Pqnqi 6n-nAol 14PIP67 6Mnl 2800 3560289 600419 3559167 6n0419 19940P 6nnulq 3597191 Ann416 iq-q74A 6nfn416 is19in Annh16 2c)00 3686944 600401 3685821 6n04n1 36Arin97 6An4nl 368l06 Ann0n01 6AP4ni 6nn4ni1 69n9RP 6nnaop 30-00 3813597 600388 3812476 600i g IR11710 6nnARP 3stn40 Anl03PA 3PoqOiP 6fl0ARq An I01 6 n R shy3100 394n247 600175 393q126 6n0379 3918136n Afl037 3Q37108 Ann3759 T0 67 in3tqqo A n6 shy3200 4066895 6n0363 4065773 6n0i64 4069n07 6n0164 4n63799 6nn364 406P34A 6nnIA4 406m4Aq AnnMmA 4 3300 41g3940 6 00192 4192ulP 6n0353 41q1652 6n0193 419n4no 6n-nlq3 418PqAQ 60nlql 4I871 n fion l Cgt 3400 4320183 6n0342 431Q061 600147 411 95 6n0142 4117n4l 60034P u319611 6nMlu 41117A 6ftnl l 3500 4446824 6n0332 4449i70 600332 44Q36 600133 44416A3 6n0lll 444PP7 6innil 401A 6nnl l 3600 4573462 600323 4572341 6n0123 457t975 6n0121 4-i70321 fi0n03 49fiAgo 6noiP4 4r6AQQA 6mqI0 3700 4700099 6n0314 469R97A 6n0115 46Q9211 An0319 46gfi9Rf AnnII 4699ri41 6nO19 4fqNAOI0 Aftt 15 3800 4826739 6n0106 4829613 6n0306 USP4A46 6n0 0O6 482lqg3 An0WM6 UAP0177 An0IO7 4APnPUq 6nnmn7 3900 4953368 600298 4992246 6n0298 4q91480 A007qq4 Q90226 An04g Uq4PRnn 6nn0Q 404AR74 finnoaq 4000 5080000 600291 507887A 6n0291 n7811p 60091 5076857 An0p t qn943n 60nQt q071400 Annio1 4100 5206630 600284 920950A 6n0P84 Pn474P An0P94 5PO14R7 60nPA4 9pnPO0 6nnI84 900nlll Ann A4 4200 5333259 600277 5332137 600p77 9111371 6n0777 513nI16 60$0P77 3PA6Q6 Anfti77 qlA744 Fnni 8 4300 5459886 600P71 5458769 6n0271 9497998 6nnP71 9456743 6n0p71 r491PI 60ngt71 qKlArfinK ndegoV 1 4400 5586513 600269 5985391 6n0269 9qA4624 60DP6r Sr31An 600PA5 q58194A AnO61K qq7QqA- 6nnAc 4S00 5713138 600P59 571P016 6n0299 r71IP4q 60059 870Q04 O60n~qq $7A577 6nn q -i7nf6nu 6inn-Q 4600 5839761 6n0P53 583863q 6n0293 qA37871 600P3 536617 f0npqi qRj9Iqf 6n09 9PIPPI 6nn o~ 4704 5966364 600248 59)6 1262 60024a 5Q644995 6nnP4S 9503P30 Annp p qO6IRIA An0gt4A qQ9nA4A AnA 4A 480o 6093005 600243 6091881 6n0243 6n91116 6nnP43 6089A6n AnnP4q3 6nA37 66nP4 6na4R6 6nno4N 4900 6219625 600238 621R501 6nn238 6pi7717 60nP3P 6pt6461 6lOnplA Aplqnq 6nno x8 API 071 AftnOle 5000 6346245 600233 6345121 6n0213 6144$6 600P31 614310O 600P11 614167R 6nnoll Al3n6AA fitn0ll 5t00 6472863 6002P8 6471741 6n0228 647nq74 600P2A 646o71A fi00PPS f468Ql 600PQ A46Aino 600g

S 5200 6599481 600224 6998358 6n02P4 6rQ7591l 60024 69q6339 6nnPP4 Ati40na 6noP04 fi9Q9011 Ann4 530 707 606724979 6n0P20 6724P08 60npp0 672PQ91 6nnP 0 67Plr 6n0nln0 671n l~ Aftdegni9 5400 6852713 600216 68q159n 6n02t6 6A9n824 60016 694q567 A00P16 6A4914n 6nn0gt16 6n4At Ann 16 5500 6979327 60023P 697820r 6n02t2 607743A 600pip 6Q76181 6nnP12 -6q7475i4 6n0OgtIP 607p74A 6nplp

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r PUBLICATION 77-70

Page 7: An InterstellarPrecursor Mission

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RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT

FOR EXTRAPLANETARY MISSION

To permit an extraplanetary mission such as that described in this

reportto commence about the year 2000 efforts are recommended on the

following topics In general a study should be initiated first followed

by development effort as indicated by the study

First priority

Starting work on the following topics is considered of first priority

in view of their importance to the mission and the time required for the

advance development

1) Design and fabrication techniques that will provide 50-year spaceshy

craft lifetime

2) Nuclear electric propulsion with operating times of 10 years or more at

full power and able to operate at low power levels for attitude control and

spacecraft power to a total of 50 years

3) Ultralight solar sails including their impact upon spacecraft and

mission design

4) Laser sailing systems including their impact upon spacecraft and

mission design

5) Detailing and application of spacecraft quality assurance and relishy

ability methods utilizing test times much shorter than the intended lifetime

Second priority

Other topics that will require advance effort beyond that likely without

special attention include

6) Spacecraft bearings and moving parts with 50-yr lifetime 2

Neutral gas mass spectrometer for measuring concentrations of 10shy

7)

0-10- atomcm3 with 50-yr lifetime

8) Techniques to predict long-time behavior of spacecraft materials from

short-time tests

v

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

vi

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TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

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Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

viii

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Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

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INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

2

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

77-70

This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

77-70

SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

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reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

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by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

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measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

10

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and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

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and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

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(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

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A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

77-70

around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

77-70

A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

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300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

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hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

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After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

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MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

77-70

assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

77-70

system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

48

77-70

Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

49

77-70

on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

77-70

70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

51

77-70

Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

52

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

53

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

54

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

77-70

RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

59

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

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77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

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own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

82

77-70

APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

r00465 3811414 5lf45 1IA0S075 nn441 U0234

i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln

srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0

g0nn03 snonI

q

fnniAg onnu53

qnnil6 0n0itl

5fnlnrlq 5n014nq tfl030 q

5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839

5100 5200

5403251 5508794

500328 500322

5401959 5507502

9003P8 900322

540I015 S001PR R506r5P 900322

53qq0 5504933

qn0i9g nn0pn

K9q7469 530O

50nnxpQ 900322

59464q 550n187

3n9 5nn39

5300 5400

5614336 5719877

500316 900310

5613044 5718589

500316 500310

5612100 5717641

r00316 500310

r610479 5716016

g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

q6n07l4 5711PAn

5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

90035 5n0p9 090q4 500289 5n024 500270

rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861

500305 g0olqQo RnOq4 500280 50OP4 90027Q

21555 0pflo S826in 6138166 649701 614q239

500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP

50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q

R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4

5nnxnK srn Q gn09Q4 500n0q nnf04

gnnon

PRW flr 03W77 nArr 7

V-INFINITY = 600 KMS

T - YRS 0=

RAn 1AU

VEL q =

RAr) 3 AU

VEL n =

PAn 5 AU

Vft n = 10

PA) Atl

VFL a = PAn

20 MI VEL PAMn

5p fU VVl

00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60

56979 83199

6P5413 617524

55061 8110l

695863 617714 A1477

A61246324q76 A17P00 807 o 0

APA17 AInO

F56o A14l1

6pov7q 617AAe

7r Qt11171

61nnpQ 615RA7

80 100

10910( 134926

61340l 610860

10A043 133R4q

613R2 610047

lo7177 1st3e1

61361 11flnn

tOAgqo 1502c

A1Po n67or 611AI3940611non

e137n i155 13 flW s

AlAq0 AinIft

120 140

160656 186325

609134 607884

15057P 185236

60q2n5607Q30

1S8872 jAlrp7

600opg07aA0

157O014 IPI1r7

6flQO 008113

J-1N IRinfn

n031 6n0S6

Ierl 14Ut

6mnn An7017

160 180

211940 237538

606q36 6n6103

210895 236441

6n6072 6n6p2

Pjn130 PA5710

6n60q5 6n6940

rnnoo P34654

A7nn O9Apt

20A467 p 43Q30

A7nq1 606P7

11fn PAn I

AnSnSn AnAfl

200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240

28A637 314157

605101 604688

28753f 31305

6n510 6047n5

P6n05 619131 1193I6fl4

2897n0 i 6

65103 An311206

p4tr5 n-ins

6n9168 An4746

5nptSn A

-tpo Anq1 n AA0471

260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340

365150 3Q0628 416096 441554

6n4036 603773 6n3543 603330

364044 389521 41407 440445

6n4048 603784 603592 613348

363031 388780 41P4t5

UIQ0f

6n4nti f 61370 6n3590

An315A

3876A7 414j31n 43q41U

A1u1AOtq Aen 60n60 A1A62

IAJ61o R866P4

u1pnrq u37T 4 a

6n4n8 6fl1I 6ndeg9 A370

16un 3A611 41I-Afln

41in1

AnflnAA Anfnlp sMIn 71 6n3A

360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa

380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480

568742 594162 619579

602594 6024A3 602382

56762P 5P3o5 618466

6n29q 6n2408 6n2386

566p8f 9inf deg17719

6112603 6fn2qj6n2980

966qq 5011j9616P7

Anp6np 6P406 AnPQI

R645n 58o53 e135i

An2613

69Rn9109

R65hn qnoA=IA

6fn9613 Annl 6m Q

o 500 520

644991 67039q

602P88 61 22Nt

643R77 66q0R2

e0P2QP 6n22n9

641126 66A533

A6p295 6129oA

641035 6673140

A62paq AnP1

64degnr 666145

612311 6npois

Aqnq4n 6egna

An1 An1 7

-J 0

540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n

721206 746605

60207 601)77

720092 749412

602050 6O10O

71031R 744736

6npn0p 601ORP

71140 743S35

60n15 Anlpq

7164P7 74P31

A9nq 69t1A0

716455 74 17I

6nn6n 6nlno

600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640

707394 822784

601851 601704

79627A 82166q

601A54 6n17q7

705p4 n2024

61n186 611708

7q4 p07fl7

n 6I0t85q Anln01

70368 lP46

601n61 A1n14

7qP4k7 ct77

6118nl 60inn

660 680

84173 873559

601741 6016q0

847057 872441

6n1743 6n1692

A4Ao AviAv

6n1745 6016qu

A49n 870477

Af1747 An1A06

A4314U pAQP99

snstyn 601AO

A4lll 86R451

An19i 6 17n0

700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760

949706 975004

601559 601514

948580 97096A

60197 601516

9u7983 Q73plO

601558 AnlIr17

046618 071)09

6n11560 An 191 a

45147 07071n

6nlq6 611spl

040MA4A6158 Q68nn finICD3

7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840

1051210 1076583

601405 601372

1050091 1075466

6n1406 6n1373

ln4335 1074707

6nln7 0n1374

1048116 1073487

n14nq tnuARPn An1W76 107105

An1411 611177

10481c7 I071157

Af1012 Aflt1A

860 880

1101954 1127324

601340 601310

1100837 1126206

601342 601311

130007A 11Pq447

601141 6131P

10857 1124PP5

6n1144 6n1314

loq7961ll22q2A

601146 6n1 tq

IQA4A 1121838

An14 eniI7

900 920

1152692 1178060

6012R1 601254

1151579 117694P

6012R3 601255

1150A81 1176183

60128p3 6n1256

1j4q 3 11749qq

6nIP9 60157

11P n 1173653

6IPA6 60158

1147176 117P9916

An1 4 6019 0

940 960

1203426 1228791

601227 601202

1202308 1227673

601228 601203

12019q 12P6013

601P20 60lpo4

12003P4 122i60

601231 An6p125

xo001 12p4376

601039 6n1006

11QT899 1P21t5

6n1943 61nl9

980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O

PRW DATF 011077 PArr Is

V-TNFINITY =600 KMS

S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL

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r PUBLICATION 77-70

Page 8: An InterstellarPrecursor Mission

77-7o

9) Compatibility of science instruments with NEP

10) Methods of calibrating science instruments for 50-yr lifetime

11) Optical vs microwave telecommunications with orbiting DSN

12) Stellar parallax measurements in deep-space

FOR STAR MISSION

For a star mission topics which warrant early study include

13) Antimatter propulsion

14) Propulsion alternatives for a star mission

15) Cryogenic spacecraft

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TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

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Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

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Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

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INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

3

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This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

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SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

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reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

77-70

considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

8

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by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

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measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

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and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

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and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

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(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

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A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

77-70

around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

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A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

77-70

300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

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hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

77-70

After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

77-70

MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

77-70

DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

77-70

assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

77-70

system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

48

77-70

Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

49

77-70

on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

77-70

70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

51

77-70

Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

52

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

53

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

54

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

77-70

RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

58

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

59

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

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77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

77-70

own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

82

77-70

APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

r00465 3811414 5lf45 1IA0S075 nn441 U0234

i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln

srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0

g0nn03 snonI

q

fnniAg onnu53

qnnil6 0n0itl

5fnlnrlq 5n014nq tfl030 q

5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839

5100 5200

5403251 5508794

500328 500322

5401959 5507502

9003P8 900322

540I015 S001PR R506r5P 900322

53qq0 5504933

qn0i9g nn0pn

K9q7469 530O

50nnxpQ 900322

59464q 550n187

3n9 5nn39

5300 5400

5614336 5719877

500316 900310

5613044 5718589

500316 500310

5612100 5717641

r00316 500310

r610479 5716016

g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

q6n07l4 5711PAn

5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

90035 5n0p9 090q4 500289 5n024 500270

rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861

500305 g0olqQo RnOq4 500280 50OP4 90027Q

21555 0pflo S826in 6138166 649701 614q239

500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP

50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q

R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4

5nnxnK srn Q gn09Q4 500n0q nnf04

gnnon

PRW flr 03W77 nArr 7

V-INFINITY = 600 KMS

T - YRS 0=

RAn 1AU

VEL q =

RAr) 3 AU

VEL n =

PAn 5 AU

Vft n = 10

PA) Atl

VFL a = PAn

20 MI VEL PAMn

5p fU VVl

00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60

56979 83199

6P5413 617524

55061 8110l

695863 617714 A1477

A61246324q76 A17P00 807 o 0

APA17 AInO

F56o A14l1

6pov7q 617AAe

7r Qt11171

61nnpQ 615RA7

80 100

10910( 134926

61340l 610860

10A043 133R4q

613R2 610047

lo7177 1st3e1

61361 11flnn

tOAgqo 1502c

A1Po n67or 611AI3940611non

e137n i155 13 flW s

AlAq0 AinIft

120 140

160656 186325

609134 607884

15057P 185236

60q2n5607Q30

1S8872 jAlrp7

600opg07aA0

157O014 IPI1r7

6flQO 008113

J-1N IRinfn

n031 6n0S6

Ierl 14Ut

6mnn An7017

160 180

211940 237538

606q36 6n6103

210895 236441

6n6072 6n6p2

Pjn130 PA5710

6n60q5 6n6940

rnnoo P34654

A7nn O9Apt

20A467 p 43Q30

A7nq1 606P7

11fn PAn I

AnSnSn AnAfl

200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240

28A637 314157

605101 604688

28753f 31305

6n510 6047n5

P6n05 619131 1193I6fl4

2897n0 i 6

65103 An311206

p4tr5 n-ins

6n9168 An4746

5nptSn A

-tpo Anq1 n AA0471

260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340

365150 3Q0628 416096 441554

6n4036 603773 6n3543 603330

364044 389521 41407 440445

6n4048 603784 603592 613348

363031 388780 41P4t5

UIQ0f

6n4nti f 61370 6n3590

An315A

3876A7 414j31n 43q41U

A1u1AOtq Aen 60n60 A1A62

IAJ61o R866P4

u1pnrq u37T 4 a

6n4n8 6fl1I 6ndeg9 A370

16un 3A611 41I-Afln

41in1

AnflnAA Anfnlp sMIn 71 6n3A

360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa

380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480

568742 594162 619579

602594 6024A3 602382

56762P 5P3o5 618466

6n29q 6n2408 6n2386

566p8f 9inf deg17719

6112603 6fn2qj6n2980

966qq 5011j9616P7

Anp6np 6P406 AnPQI

R645n 58o53 e135i

An2613

69Rn9109

R65hn qnoA=IA

6fn9613 Annl 6m Q

o 500 520

644991 67039q

602P88 61 22Nt

643R77 66q0R2

e0P2QP 6n22n9

641126 66A533

A6p295 6129oA

641035 6673140

A62paq AnP1

64degnr 666145

612311 6npois

Aqnq4n 6egna

An1 An1 7

-J 0

540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n

721206 746605

60207 601)77

720092 749412

602050 6O10O

71031R 744736

6npn0p 601ORP

71140 743S35

60n15 Anlpq

7164P7 74P31

A9nq 69t1A0

716455 74 17I

6nn6n 6nlno

600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640

707394 822784

601851 601704

79627A 82166q

601A54 6n17q7

705p4 n2024

61n186 611708

7q4 p07fl7

n 6I0t85q Anln01

70368 lP46

601n61 A1n14

7qP4k7 ct77

6118nl 60inn

660 680

84173 873559

601741 6016q0

847057 872441

6n1743 6n1692

A4Ao AviAv

6n1745 6016qu

A49n 870477

Af1747 An1A06

A4314U pAQP99

snstyn 601AO

A4lll 86R451

An19i 6 17n0

700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760

949706 975004

601559 601514

948580 97096A

60197 601516

9u7983 Q73plO

601558 AnlIr17

046618 071)09

6n11560 An 191 a

45147 07071n

6nlq6 611spl

040MA4A6158 Q68nn finICD3

7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840

1051210 1076583

601405 601372

1050091 1075466

6n1406 6n1373

ln4335 1074707

6nln7 0n1374

1048116 1073487

n14nq tnuARPn An1W76 107105

An1411 611177

10481c7 I071157

Af1012 Aflt1A

860 880

1101954 1127324

601340 601310

1100837 1126206

601342 601311

130007A 11Pq447

601141 6131P

10857 1124PP5

6n1144 6n1314

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r PUBLICATION 77-70

Page 9: An InterstellarPrecursor Mission

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TABLE OF CONTENTS

Page

PREFACE ----------------------------------------------------- iii

ABSTRACT ------------------------------------------------------ iv

RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v

First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V

For Star Mission ---------------------------------------------- vi

INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I

STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4

SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5

Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5

Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10

Gravity Waves --------------------------------------------- 12

Advantages of Using Two Spacecraft ------------------------- 12

Simulated Stellar Encounter --------------------------------- 11

Measurements Not Planned ------------------------------------ 12

Candidate Science Payload ------------------------------------- 13

TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14

Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15

Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15

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Page

TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18

Jupiter Powered Flyby ------------------------------------- 25

Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28

Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30

Laser Electric Propulsion -------------------------- 31

Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32

Solar Plus Nuclear Electric -------------------------------- 33

Jupiter Gravity Assist ------------------------------------- 18

Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28

Solar Electric Propulsion ---------------- -- --------- 31

Nuclear Electric Propulsion -------------------------------- 32

Low Thrust Plus Gravity Assist-------------------------- 32

Choice of Propulsion ----------------------------------------- 33

MISSION CONCEPT ---------------------------------------------- 38

MASS DEFINITION AND PROPULSION ------------------------------- 40

INFORMATION MANAGEMENT --------------------------------------- 44

Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46

Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47

Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50

Higher Frequencies --------------------------------------- 53

Selection of Telemetry Option -------------------------------

Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45

The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47

Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50

Larger Antennas and Lower Noise Spectral Density----------- 53

Higher Data Rates ------------------------------------ 55 55

RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59

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Page

TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60

Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and

Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61

Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication

System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69

ACKNOWLEDGEMENT ----------------------------------- ---- 71

REFERENCES ---------------------------------------------- 72

APPENDICES --------------------------------------------------- 75

Appendix A - Study Participants ------------------ 76

Appendix B - Science Contributors ---------------------------- 77

Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81

Appendix D - Solar System Ballistic Escape Trajectories ------ 83

TABLES

1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch

from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter

Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35

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Page

TABLES (continued)

11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary

Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68

FIGURES

1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral

Power Density ------------------------------------------ 51

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INTRODUCTION

BACKGROUND

Even before the first earth satellites were launched in 1957 there

was popular interest in the possibility of spacecraft missions to other

stars and their planetary systems As space exploration has progressed

to the outer planets of the solar system it becomes appropriate to begin

to consider the scientific promise and engineering difficulties of mission

to the stars and hopefully their accompanying planets

In a conference on Missions Beyond the Solar System organized by

L D Friedman and held at JPL in August 1976 the idea of a precursor

mission out beyond the planets but not nearly to another star was

suggested as a means of bringing out and solving the engineering proshy

blems that would be faced in a mission to a star At the same time it

was recognized that such a precursor mission even though aimed primarily

at engineering objectives should also have significant scientific objecshy

tives

Subsequently in November 1976 this small study was initiated to

examine a precursor mission and identify long lead-time technology developshy

ment which should be initiated to permit such a mission This study was

funded by the Study Analysis and Planning Office (Code RX) of the NASA

Office of Aeronautics and Space Technology

STUDY OBJECTIVE

The objective of the study was to establish probable science goals

mission concepts and technology requirements for a mission extending from

outer regions of the solar system to interstellar flight An unmanned

mission was intended

STUDY SCOPE

The study was intended to address science goals mission concepts

and technology requirements for the portion of the mission outward from

the outer portion of the planetary system

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Because of the limited funding available for this study it was

originally planned that the portion of the mission between the earth

and the outer portion of the planetary system would not be specifically

addressed likewise propulsion concepts and technology would not be

included Problems encountered at speeds approaching that of light were

excluded for the same reason In the course of the study it became

clear that these constraints were not critical and they were relaxed

as indicated later in this report

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STUDY APPROACH

The study effort consisted of two tasks Task 1 concerned science

goals and mission concepts Task 2 technology requirements

TASK I

In Task 1 science goals for the mission were to be examined and

the scientific measurements to be made Possible relation of the mission

to the separate effort on Search for Extraterrestrial Intelligence was

also to be considered Another possibility to be examined was that of

using the data in reverse time sequence to examine a star and its surshy

roundings (in this case the solar system) as might be done from an

approaching spacecraft

Possible trajectories would be evaluated with respect to the intershy

action of the direction of the outward asymptote and the speed with the

science goals A very limited examination might be made of trajectories

within the solar system and accompanying propulsion concepts to assess

the feasibility of the outward velocities considered

During the study science goals and objectives were derived by series

of conversations and small meetings with a large number of scientists

Most of these were from JPL a few elsewhere Appendix B gives their

names

The trajectory information was obtained by examination of pertinent

work done in other studies and a small amount of computation carried out

specifically for this study

TASK 2

In this task technology requirements that appear to differ signishy

ficantly from those of missions within the solar system were to be identishy

fied These would be compared with the projected state-of-the-art for

the year 2000 plusmn 15 It was originally planned that requirements associated

with propulsion would be addressed only insofar as they interact with power

or other systems

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This task was carried out by bringing together study team particishy

pants from each of the technical divisions of the Laboratory (Particishy

pants are listed in Appendix A-) Overal-i concepts were developed and

discussed at study team meetings Each participant obtained inputs from

other members of his division on projected capabilities and development

needed for individual subsystems These were iterated at team meetings

In particular several iterations were needed between propulsion and trashy

jectory calculations

STAR MISSION

Many of the contributors to this study both scientific and engineershy

ing felt an actual star mission should be considered Preliminary examshy

ination indicated however that the hyperbolic velocity attainable for

solar system escape during the time period of interest (year 2000 plusmn 15)

was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013

is at a distance of 43 light years or about 4 x 10 km the mission durshy

ation would exceed 10000 years This did not seem worth considering for

two reasons

First attaining and especially establishing a spacecraft lifeshy

time of 10000 years by the year 2000 is not considered feasible Secondly

propulsion capability and hence hyperbolic velocity attainable is expected

to increase with time Doubling the velocity should take not more than

another 25 years of work and would reduce the mission duration to only

5000 years Thus a spacecraft launched later would be expected to arrive

earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable

For this reason a star mission is not considered further in the body

of this report A few thoughts which arose during this study and pertain

to a star mission are recorded in Appendix C It is recommended that a

subsequent study address the possibility of a star mission starting in

2025 2050 or later and the long lead-time technology developments that

will be needed to permit this mission

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SCIENTIFIC OBJECTIVES AND REQUIREMENTS

Preliminary examination of trajectory and propulsion possibilities

indicated that a mission extending to distances of some hundred or pershy

haps a few thousand AU from the sun with a launch around the year 2000

was reasonable The following science objectives and requirements are

considered appropriate for such a mission

SCIENTIFIC OBJECTIVES

Primary Objectives

1) Determination of the characteristics of the heliopause where the

solar wind presumably terminates against the incoming interstellar

medium

2) Determination of the characteristics of the interstellar medium

3) Determination of the stellar and galactic distance scale through

measurements of the distance to nearby stars

4) Determination of the characteristics of cosmic rays at energies

excluded by the heliosphere

5) Determination of characteristics of the solar system as a whole

such as its interplanetary gas distribution and total mass

Secondary Objectives

i) Determination of the characteristics of Pluto and its satellites

and rings if any If there had been a previous mission to Pluto

this objective would be modified

2) Determination of the characteristics of distant galactic and extrashy

galactic objects

3) Evaluation of problems of scientific observations of another solar

system from a spacecraft

TRAJECTORY REQUIREMENTS

The primary science objectives necessitate passing through the helioshy

pause preferably in a relatively few years after launch to increase the

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reliability of data return Most of the scientists interviewed preferred

a mission directed toward the incoming interstellar gaswhere the helioshy

pause is expected to be closest and most well defined The upwind

direction with respect to neutral interstellar gas is approximately RA

250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1

The suns motion with respect to interstellar charged particles and magshy

netic fields is not known) Presumably any direction within say 400

of this would be satisfactory A few scientists preferred a mission

parallel to the suns axis (perpendicular to the ecliptic) believing

that interstellar magnetic field and perhaps particles may leak inward

further along this axis Some planetary scientists would like the misshy

sion to include a flyby or orbiter of Pluto depending on the extent to which

Pluto might have been explored by an earlier mission Although a Pluto flyby

is incompatible with a direction perpendicular to the ecliptic it happens

that in the period of interest (arrival around the year 2005) Pluto will

lie almost exactly in the upwind direction mentioned so an upwind

trajectory could include a Pluto encounter

The great majority of scientists consulted preferred a trajectory

that would take the spacecraft out as fast as possible This would minishy

mize time to reach the heliopause and the interstellar medium Also it

would at any time provide maximum earth-SC separation as a base for

optical measurements of stellar parallax A few scientists would like

to have the SC go out and then return to the solar system to permit

evaluating and testing methods of obtaining scientific data with a

future SC encountering another solar system Such a return would

roughly halve the duration of the outward portion of the flight for

any fixed mission duration Also since considerable propulsive energy

would be required to stop and turn around this approach would conshy

siderably reduce the outward hyperbolic velocity attainable These two

effects would greatly reduce the maximum distance that could be reached

for a given mission duration

As a strawman mission it is recommended that a no-return trajecshy

tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be

6

90 I 11

60 - BARNARDS 380000 AU

30-

STAR

APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS

YEAR 2000 30 AU

z o

1990-30 30 AU

0 CELESTIAL EQUATOR

uj

0

INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)

C

-60 -2

-90 360

2 34 AU

300 240

- a C N A RNaCN UR 270000 AU

180 120 60 0

RIGHT ASCENSION (0)

Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified

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considered with a hyperbolic excess velocity of 40-90 kms or more

Higher velocities should be used if practical Propulsion should be

designed to avoid interference with scientific measurements and should

be off when mass measurements are to be made

A number of scientific observations (discussed below) would be

considerably improved if two spacecraft operating simultaneously were

used with asymptotic trajectories at approximately right angles to

each other Thus use of a second spacecraft with an asymptotic tra3ecshy

tory approximately parallel to the solar axis is worthwhile scientifically

SCIENTIFIC MEASUREMENTS

Heliopause and Interstellar Medium

Determination is needed of the characteristics of the solar wind

just inside the heliopause of the heliopause itself of the accompanying

shock (if one exists) and of the region between the heliopause and the

shock The location of the heliopause is not known estimates now tend

to center at about 100 AU from the sun (As an indication of the uncershy

tainty estimates a few years ago ran as low as 5 AU)

Key measurements to be made include magnetic field plasma propershy

ties (density velocity temperature composition plasma waves) and

electric field Similar measurements extending to low energy levels

are needed in the interstellar medium together with measurements of the

properties of the neutral gas (density temperature composition of atomic

and molecular species velocity) and of the interstellar dust (particle

concentration particle mass distribution composition velocity) The

radiation temperature should also be measured

The magnetic electric and plasma measurements would require only

conventional instrumentation but high sensitivity would be needed Plasma

blobs could be detected by radio scintillation of small sources at a waveshy

length near 1 m Radiation temperature could be measured with a radiomshy

eter at wavelengths of 1 cm to 1 m using a detector cooled to a few

Kelvins Both in-situ and remote measurements of gas and dust properties

are desirable In-situ measurements of dust composition could be made

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by an updated version of an impact-ionization mass spectrometer In-situ

measurements of ions could be made by a mass spectrometer and by a plasma

analyzer In-situ measurements of neutral gas composition would probably

require development of a mass spectrometer with greater sensitivity and

signalnoise ratio than present instruments Remote measurements of gas

composition could be made by absorption spectroscopy looking back toward

the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N

Li Be B and the flow velocity Dust within some size range could be

observed remotely by changes in the continuum intensity

Stellar and Galactic Distance Scale

Present scales of stellar and galactic distance are probably uncershy

tain by 20 This in turn leads to uncertainties of 40 in the absolute

luminosity (energy production) the quantity which serves as the fundashy

mental input data for stellar model calculations Uncertainties in galactic

distances make it difficult to provide good input data for cosmological

models

The basic problem is that all longer-range scales depend ultimately

on the distances to Cepheid variables in nearby clusters such as the

Hyades and Pleiades Distances to these clusters are determined by stashy

tistical analysis of relative motions of stars within the clusters and

the accuracy of this analysis is not good With a baseline of a few

hundred AU between SC and earth triangulation would provide the disshy

tance to nearby Cepheids with high accuracy This will require a camera

with resolution of a fraction of an arc second implying an objective

diameter of 30 cm to 1 m Star position angles need not be measured

relative to the sun or earth line but only with respect to distant

stars in the same image frame To reduce the communications load only

the pixel coordinates of a few selected objects need be transmitted to

earth

Cosmic Rays

Measurements should be made of low energy cosmic rays which the

solar magnetic field excludes from the heliosphere Properties to be

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measured include flux spectrum composition and direction Measurements

should be made at energies below 10 MeV and perhaps down to 10 keV or

lower Conventional instrumentation should be satisfactory

Solar System as a Whole

Determinations of the characteristics of the solar system as a

whole include measurements of neutral and ionized gas and of dust Quanshy

tities to be measured include spatial distribution and the other propershy

ties mentioned above

Column densities of ionized material can be observed by low freshy

quency radio dispersion Nature distribution and velocity of neutral

gas components and some ions can be observed spectroscopically by fluoresshy

cence under solar radiation To provide adequate sensitivity a large

objective will be needed Continuum observation should show the dust

distribution

The total mass of the solar system should be measured This could

be done through dual frequency radio doppler tracking

Observations of Distant Objects

Observations of more distant objects should include radio astronomy

observations at frequencies below 1 kHz below the plasma frequency of the

interplanetary medium This will require a VLF receiver with a very long

dipole or monopole antenna

Also both radio and gamma-ray events should be observed and timed

Comparison of event times on the SC and at earth will indicate the direcshy

tion of the source

In addition the galactic hydrogen distribution should be observed

by UV spectrophotometry outside any local concentration due to the sun

Pluto

If a Pluto flyby is contemplated measurements should include optical

observations of the planet to determine its diameter surface and atmosshy

phere features and an optical search for and observations of any satellites

or rings Atmospheric density temperature and composition should be measured

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and nearby charged particles and magnetic fields Surface temperature and

composition should also be observed Suitable instruments include a TV

camera infrared radiometer ultravioletvisible spectrometer particles

and fields instruments infrared spectrometer

For atmospheric properties UV observations during solar occultation

(especially for H and He) and radio observations of earth occultation should

be useful

The mass of Pluto should be measured radio tracking should provide

this

If a Pluto orbiter is included in the mission measurements should

also include surface composition variable features rotation axis shape

and gravity field Additional instruments should include a gamma-ray

spectrometer and an altimeter

Simulated Stellar Encounter

If return to the solar system is contemplated as a simulation of a

stellar encounter observations should be made during approach of the

existence of possible stellar companions and planets and later of satelshy

lites asteroids and comets and of their characteristics Observations

of neutral gas dust plasma and energetic emissions associated with the

star should be made and any emissions from planets and satellites Choice(s)

should be made of a trajectory through the approaching solar system (recog-_

nizing the time-delays inherent in a real stellar mission) the choice(s)

should be implemented and flyby measurements made

The approach measurements could probably be made using instruments

aboard for other purposes For flyby it would probably be adequate to

use data recorded on earlier missions rather than carry additional instrushy

ments

An alternative considered was simulating a stellar encounter by

looking backwards while leaving the solar system and later replaying

the data backwards This was not looked on with favor by the scientists

contacted because the technique would not permit making the operational

decisions that would be key in encountering a new solar system locating

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and flying by planets for example Looking backwards at the solar system

is desired to give solar system data per se as mentioned above Stellar

encounter operations are discussed briefly in Appendix C

Gravity Waves

A spacecraft at a distance of several hundred AU offers an opportunity

for a sensitive technique for detecting gravity waves All that is needed

is precision 2-way radio doppler measurements between SC and earth

Measurements Not Planned

Observations not contemplated include

1) Detecting the Oort cloud of comets if it exists No method of

detecting a previously unknown comet far out from the sun is recogshy

nized unless there is an accidental encounter Finding a previously

seen comet when far out would be very difficult because the nrbits

of long-period comets are irregular and their aphelia are hard to

determine accurately moreover a flyby far from the sun would

tell little about the comet and nothing about the Oort cloud The

mass of the entire Oort cloud might be detectable from outside but

the mission is not expected to extend the estimated 50000 AU out

If Lyttletons comet model is correct a comet accidentally encounshy

tered would be revealed by the dust detector

2) VLBI using an earth-SC baseline This would require very high rates

of data transmission to earth rates which do not appear reasonable

Moreover it is doubtful that sources of the size resolved with

this baseline are intense enough to be detected and that the reshy

quired coherence would be maintained after passage through inhomoshy

geneities in the intervening medium Also with only 2 widely

separated receivers and a time-varying baseline there would be

serious ambiguity in the measured direction of each source

Advantages of Using Two Spacecraft

Use of two spacecraft with asymptotic trajectories at roughly right

angles to each other would permit exploring two regions of the heliopause

12

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(upwind and parallel to the solar axis) and provide significantly greater

understanding of its character including the phenomena occurring near the

magnetic pole direction of the sun Observations of transient distant

radio and gamma-ray events from two spacecraft plus the earth would permit

location of the source with respect to two axes instead of the one axis

determinable with a single SC plus earth

CANDIDATE SCIENCE PAYLOAD

1) Vector magnetometer

2) Plasma spectrometer

3) Ultravioletvisible spectrometers

4) Dust impact detector and analyzer

5) Low energy cosmic ray analyzer

6) Dual-frequency radio tracking (including low frequency with high

frequency uplink)

7) Radio astronomyplasma wave receiver (including VLF long antenna)

8) Massspectrometer

9) Microwave radiometer

10) Electric field meter

11) Camera (aperture 30 cm to 1 m)

12) Gamma-ray transient detector

If Pluto flyby or orbiter is planned

13) Infrared radiometer

14) Infrared spectrometer

If Pluto orbiter is planned

15) Gamma-ray spectrometer

16) Altimeter

13

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TRAJECTORIES

UNITS AND COORDINATE SYSTEMS

Units

Some useful approximate relations in considering an extraplanetary

mission are

1 AU = 15 x 108km

1 light year = 95 x 1012 km = 63 x 104 AU

1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years

1 year = 32 x 107

- 61 kms = 021 AUyr = 33 x 10 c

where c = velocity of light

Coordinate Systems

For objects out of the planetary system the equatorial coordinshy

ate system using right ascension (a) and declination (6) is often more

convenient than the ecliptic coordinates celestial longitude (X)

and celestial latitude (8) Conversion relations are

sin S = cos s sin 6- sin s cos 6 sin a

cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a

CoS Cos A = Cos amp Cos a

where s = obliquity of ecliptic = 2350

DIRECTIONS OF INTEREST

Extraplanetary

Most recent data for the direction of the incoming interstellar

neutral gas are

Weller amp Meier (1974)

Right ascension a = 2520

Declination 6 = -15

Ajello (1977) deg Right ascension a = 252

Declination 6 = -17

14

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Thus these 2 data sources are in excellent agreement

At a = 2500 the ecliptic is about 200S of the equator so the wind

comes in at celestial latitude of about 4 Presumably it is only

a coincidence that this direction lies close to the ecliptic plane

The direction of the incoming gas is sometimes referred to as the

apex of the suns way since it is the direction toward which the sun

is moving with respect to the interstellar gas The term apex howshy

ever conventionally refers to the direction the sun is moving relative

to nearby stars rather than relative to interstellar gas These two

directions differ by about 450 in declination and about 200 in right

ascension The direction of the solar motion with respect to nearby

stars and some other directions of possible interest are shown in

Fig 1

Pluto

Table 1 gives the position of Pluto for the years 1990 to 2030

Note that by coincidence during 2000 to 2005 Pluto is within a few

degrees of the direction toward the incoming interstellar gas (see Fig 1)

At the same time it is near its perihelion distance only 30-31 AU

from the sun

SOLAR SYSTEM ESCAPE TRAJECTORIES

As a step in studying trajectories for extraplanetary missions a

series of listings giving distance and velocity vs time for parabolic

and hyperbolic solar system escape trajectories has been generated These

are given in Appendix D and a few pertinent values extracted in Table 2

Note for example that with a hyperbolic heliocentric excess velocity

V = 50 kms a distance of 213 AU is reached in 20 years and a distance

of 529 AU in 50 years With V = 100 kms these distances would be

doubled approximately

LAUNCHABLE MASS

Solar system escape missions typically require high launch energies

referred to as C3 to achieve either direct escape or high flyby velocity

15

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TABLE 1

Position of Pluto 1990-2030

Position on 1 January

Distance Right Declination from ascension sun

Year AU 0 0

1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010

3078 3164

26139 27261

-1492 -1820

2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363

16

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TABLE 2

Summary of Solar System Ballistic Escape Trajectories

Initial Condition Circular Orbit at 1 AU

V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =

kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs

0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67

10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600

(See Appendix D for detail)

17

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at a gravity assist planet Table 3 gives projected C3 capabilities

in (kms)2 for the three versions of the ShuttleInterim Upper Stage

assuming net payloads of 300 400 and 500 kg It can be seen that as

launched mass increases the maximum launch energy possible decreases

Conceivably higher C3 are possible through the use of in-orbit

assembly of larger IUS versions or development of more powerful upper

stages such as the Tug The range of C3 values found here will be used

in the study of possible escape trajectories given below

DIRECT LAUNCH FROM EARTH

Direct launch from the Earth to a ballistic solar system escape

trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4

gives the maximum solar system V obtainable (in the ecliptic plane) and

maximum ecliptic latitude obtainable (for a parabolic escape trajectory)

for a range of possible C3

The relatively low V and inclination values obtainable with direct

launch make it an undesirable choice for launching of extra-solar

probes as compared with those techniques discussed below

JUPITER ASSIST

Jupiter Gravity Assist

Of all the planets Jupiter is by far the best to use for gravity

assisted solar system escape trajectories because of its intense gravity

field The geometry of the Jupiter flyby is shown in Figure 2 Assume

that the planet is in a circular orbit about the Sun with orbital

velocity VJh = 1306 kms

The spacecraft approaches the planet with some relative velocity

Vin directed at an angle 0 to VJh and departs along Vout after having

been bent through an angle a The total bend angle

2 a = 2 arcsin [1(I + V r p)]in p

where r is the closest approach radius to Jupiter and v= GMJ the P

gravitational mass of Jupiter Note that VJh Vin and Vout need not all

18

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TABLE 3

Capabilities of Shuttle with Interim Upper Stage

Launch energy C3

(kms) 2

for indicated

payload (kg)

Launch Vehicle 300 400 500

Shuttle2-stage IUS 955 919 882

Shuttle3-stage IUS 1379 1310 1244

Shuttle4-stage IUS 1784 1615 1482

19

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TABLE 4

Sblar System Escape Using Direct Ballistic Launch from Earth

Launch energy C3

(kms)2

1522

155

160

165

170

175

Maximum hyperbolic excess velocity V in ecliptic plane

(kms)

000

311

515

657

773

872

Maximum ecliptic latitude Max for parabolic trajectory

(0)

000

273

453

580

684

774

20

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A

v escape

~VA h

Fig 2 Geometry of Jupiter Flyby

21

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be in the same plane so the spacecraft can approach Jupiter in the

ecliptic plane and be ejected on a high inclination orbit The helioshy

centric velocity of the spacecraft after the flyby Vsh is given by the

vector sum of VJh and Vou If this velocity exceeds approximatelyt

1414 VJh shown by the ampashed circle in Figure 2 the spacecraft

achieves by hyperbolic orbit and will escape the solar system The

hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs

the gravitation mass for the Sun and r is the distance from the Sun

52 astronomical units The maximum solar system escape velocity will

be obtained when the angle between V and Vout is zero This will

necessarily result in a near-zero inclination for the outgoing orbit

Around this vector will be a cone of possible outgoing escape trajecshy

tories As the angle from the central vector increases the hyperbolic

excess velocity relative to the Sun will decrease The excess velocity

reaches zero (parabolic escape orbit) when the angle between VJh and

Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the

maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic

escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin

For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be

1303 kms for an inclination of 100 1045 kms for an inclination of

20 Note that for V s greater than 20 kms it is possible to ejectin

along retrograde orbits This is an undesirable waste of energy however

It is preferable to wait for Jupiter to move 1800 around its orbit when

one could use a direct outgoing trajectory and achieve a higher escape

speed in the same direction

To consider in more detail the opportunities possible with Jupiter

gravity assist trajectories have been found assuming the Earth and

Jupiter in circular co-planar orbits for a range of possible launch

energy values These results are summarized in Table 6 Note that the

orbits with C3 = 180 (kms)2 have negative semi-major axes indicating

that they are hyperbolic With the spacecraft masses and launch vehicles

discussed above it is thus possible to get solar syst6m escape velocities

22

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TABLE 5

Solar System Escape Using Jupiter Gravity Assist

Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300

Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)

(0) for above approach velocity

00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882

100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283

900 1065 1970

Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity

958 3141 5353 7660 10357 14356

Note indicates unobtainable combination of V and anglein

23

TABLE 6

Jupiter Gravity Assist versus Launch Energy

Launch Energy

C3 2 (kns)

Transfer orbit semi-major axis

(AU)

Approach velocity relative to Jupiter Vin (kms)

Angle between approach velocity and Jupiter heliocentric velocitya

((0)

Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for

for flyby flyby at flyby at at 11 R 11 R 11 R

(0) (0)

00 900

1000 1100 1200 1300 1400 1500 1600 1800 2000

323 382 463 582 774

1138 2098

11743 -3364 -963 -571

655 908

1098 1254 1388 1507 1614 1712 1803 1967 2113

14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261

15385

14410 13702 13135 12659 12248 11886 11561 11267 10752 10311

659

1222 1538 1772 1961 2121 2261 2387 2501 2702 2877

1366

2717 3581 4269 4858 5382 5861 6305 6722 7499 8222

D

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on the order of 25 kms in the ecliptic plane and inclinations up to

about 670 above the ecliptic plane using simple ballistic flybys of

Jupiter Thus a large fraction of the celestial sphere is available

to solar system escape trajectories using this method

Jupiter Powered Flyby

One means of improving the performance of the Jupiter flyby is to

perform a maneuver as the spacecraft passes through periapsis at Jupishy

ter The application of this AV deep in the planets gravitational

potential well results in a substantial increase in the outgoing Vout

and thus the solar system hyperbolic excess velocity V This technique

is particularly useful in raising relatively low Vin values incoming

to high outgoing Vouts Table 7 gives the outgoing Vou t values at

Jupiter obtainable as a function of V and AV applied at periapsisin

A flyby at 11 R is assumed The actual Vou t might be fractionally smaller

because of gravity losses and pointing errors but the table gives a

good idea of the degrees of performance improvement possible

Carrying the necessary propulsion to perform the AV maneuver would

require an increase in launched payload and thus a decrease in maximum

launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using

a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a

function of AV capability at Jupiter These numbers may be combined

with the two previous tables to find the approximate V at Jupiter and In

the resulting Vout

Launch Opportunities to Jupiter

Launch opportunities to Jupiter occur approximately every 13 months

Precise calculations of such opportunities would be inappropriate at

this stage in a study of extra-solar probe possibilities Because

Jupiter moves about 330 in ecliptic longitude in a 13 month period and

because the cone of possible escape trajectories exceeds 300 in halfshy

width for V above about 10 kms it should be possible to launch out

to any ecliptic longitude over a 12 year period by properly choosing

the launch date and flyby date at Jupiter With sufficient V the out

25

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TABLE 7

Jupiter Powered Flyby

Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied

at periapsis of 11 R

50 100 150 200 250

60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890

100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224

160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600

26

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TABLE 8

Launched Mass for 300 kg Net Payload

after Jupiter Powered Flyby

AV at Required launched mass Jupiter for SC Is = 370 s

p

(kms) (kg)

0 300

5 428

10 506

15 602

20 720

25 869

Maximum launch energy C3 attainable with shuttle4-stage IUS

(kms) 2

1784

1574

1474

1370

1272

1149

27

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high ecliptic latitudes would be available as described in an earlier

section Flight times to Jupiter will typically be 2 years or less

Venus-Earth Gravity Assist

One means of enhancing payload to Jupiter is to launch by way of

a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2

launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity

assist and AV maneuvers at Venus and Earth to send large payloads to

the outer planets The necessary maneuvers add about 2 years to the

total flight time before reaching Jupiter The extra payload could

then be used as propulsion system mass to perform the powered flyby

at Jupiter An alternate approach is that VEGA trajectories allow use

of a smaller launch vehicle to achieve the same mission as a direct

trajectory

POWERED SOLAR FLYBY

The effect of an impulsive delta-V maneuver when the spacecraft is

close to the Sun has been calculated for an extra-solar spacecraft The

calculations are done for a burn at the perihelion distance of 01 AU

for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy

ly Results are shown in Table 9 It can be seen that the delta-V

maneuver deep in the Suns potential well can result in a significant

increase in V after the burn having its greatest effect when the preshy

burn V is small

The only practical means to get 01 from the Sun (other than with a

super sail discussed below) is a Jupiter flyby at a V relative to

Jupiter of 12 kms or greater The flyby is used to remove angular

momentum from the spacecraft orbit and dump it in towards the Sun

The same flyby used to add energy to the orbit could achieve V of 17

kms or more without any delta-V and upwards of 21 kms with 25 kms

of delta-V at Jupiter The choice between the two methods will require

considerably more study in the future

LOW-THRUST TRAJECTORIES

A large number of propulsion techniques have been proposed that do

not depend upon utilization of chemical energy aboard the spacecraft

28

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TABLE 9

Powered Solar Flyby

AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)

0 5 10

1 516 719 1125

3 894 1025 1342

5 1155 1259 1529

10 1635 1710 1919

15 2005 2067 2242

20 2317 2371 2526

25 2593 2641 2782

29

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Among the more recent reviews pertinent to this mission are those

by Forward (1976) Papailiou et al (1975) and James et al (1976) A

very useful bibliography is that of Mallove et al (1977)

Most of the techniques provide relative low thrust and involve long

periods of propulsion The following paragraphs consider methods that

seem the more promising for an extraplanetary mission launched around

2000

Solar Sailing

Solar sails operate by using solar radiation pressure to add or

subtract angular momentum from the spacecraft (Garwin 1958) The

basic design considered in this study is a helio-gyro of twelve

6200-meter mylar strips spin-stabilized

According to Jerome Wright (private communication) the sail is

capable of achieving spacecraft solar system escape velocities of 15-20

kms This requires spiralling into a close orbit approximately 03 AU

from the sun and then accelerating rapidly outward The spiral-in

maneuver requires approximately one year and the acceleration outward

which involves approximately 1-12 - 2 revolutions about the sun

takes about 1-12 - 2 years at which time the sailspacecraft is

crossing the orbit of Mars 15 AU from the sun on its way out

The sail is capable of reaching any inclination and therefore any

point of the celestial sphere This is accomplished by performing a

cranking maneuver when the sail is at 03 AU from the sun before

the spiral outward begins The cranking maneuver keeps the sail in a

circular orbit at 03 AU as the inclination is steadily raised The

sail can reach 900 inclination in approximately one years time

Chauncey Uphoff (private communication) has discussed the possishy

bility of a super sail capable of going as close as 01 AU from the sun

and capable of an acceleration outward equal to or greater than the

suns gravitational attraction Such a sail might permit escape Vs

on the order of 100 kms possible up to 300 kms However no such

design exists at present and the possibility of developing such a sail

has not been studied

Laser Sailing

Rather et al (1976) have recently re-examined the proposal (Forshy

ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather

than sunlight to illuminate a sail The lasers could be in orbit

30

77-70

around the earth or moon and powered by solar collectors

Rather et al found that the technique was not promising for star

missions but could be useful for outer planet missions Based on their

assumptions a heliocentric escape velocity of 60 Ios could be reached

with a laser output power of about 30 kW 100 kms with about 1500 kW

and 200 Ims with 20 MW Acceleration is about 035 g and thrusting

would continue until the SC was some millions of kilometers from earth

Solar Electric Propulsion

Solar electric propulsion uses ion engines where mercury or

other atoms are ionized and then accelerated across a potential gap

to a very high exhaust velocity The electricity for generating the

potential comes from a large solar cell array on the spacecraft

Current designs call for a 100 kilowatt unit which is also proposed

for a future comet rendezvous mission A possible improvement to the

current design is the use of mirror concentrators to focus additional

sunlight on the solar cells at large heliocentric distances

According to Carl Sauer (private communication) the solar powered

ion drive is capable of escape Vs on the order of 10-15 kms in the

ecliptic plane Going out of the ecliptic is more of a problem because

the solar cell arrays cannot be operated efficiently inside about 06 AU

from the sun Thus the solar electric drive cannot be operated

close iiito the sun for a cranking maneuver as can the solar sail

Modest inclinations can still be reached through slower cranking or the

initial inclination imparted by the launch vehicle

Laser Electric Propulsion

An alternative to solar electric propulsion is laser electric

lasers perhaps in earth orbit radiate power to the spacecraft which is

collected and utilized in ion engines The primary advantage is that

higher energy flux densities at the spacecraft are possible This would

permit reducing the receiver area and so hopefully the spacecraft

weight To take advantage of this possibility receivers that can

operate at considerably higher temperatures than present solar cells will

be needed A recent study by Forward (1975) suggests that a significant

performance gain as compared to solar electric may be feasible

6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed

31

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Nuclear Electric Propulsion

Nuclear electric propulsion (NEP) may use ion engines like solar

electric or alternatively magnetohydrodynamic drive It obtains

electricity from a generator heated by a nuclear fission reactor

Thus NEP is not powertlimited by increasing solar distance

Previous studies indicate that an operational SC is possible

by the year 2000 with power levels up to a megawatt (electric) or more

(James et al 1976)

Preliminary estimates were made based on previous calculations for

a Neptune mission Those indicated that heliocentric escape velocity

of 50-60 kms can be obtained

Fusion

With a fusion energy source thermal energy could be converted to

provide ion or MHD drive and charged particles produced by the nuclear

reaction can also be accelerated to produce thrust

A look at one fusion concept gave a V of about 70 kus The

spacecraft weight was 3 x 106 kg Controlled fusion has still to be

attained

Bussard (1960) has suggested that interstellar hydrogen could be

collected by a spacecraft and used to fuel a fusion reaction

Antimatter

Morgan (1975 1976) James et al (1976) and Massier (1977a and b)

have recently examined the use of antimatter-matter annihilation to

obtain rocket thrust A calculation based on Morgans concepts suggests

that a V over 700 Ions could be obtained with a mass comparable to

NEP

Low Thrust Plus Gravity Assist

A possible mix of techniques discussed would be to use a lowshy

thrust propulsion system to target a spacecraft for a Jupiter gravity

assist to achieve a very high V escape If for example one accelerashy

ted a spacecraft to a parabolic orbit as it crossed the orbit of

Jupiter the V at Jupiter would be about 172 kms One could usein

gravity assist then to give a solar system escape V of 24 kus in the

ecliptic plane or inclinations up to about 63 above the plane

Powered swingby at Jupiter could further enhance both V and inclination

32

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A second possibility is to use a solar sail to crank the spaceshy

craft into a retrograde (1800 inclination) orbit and then spiral out to

encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus

covering the entire celestial sphere Again powered swingby would

improve performance but less so because of the high Vin already present

This method is somewhat limited by the decreasing bend angle possible

at Jupiter as Vin increases With still higher approach velocities

the possible performance increment from a Jupiter swingby continues

to decrease

Solar Plus Nuclear Electric

One might combine solar electric with nuclear electric using solar

first and then when the solar distance becomes greater and the solar

distance becomes greater and the solar power falls off switching to NEP

Possibly the same thrusters could be used for both Since operating

lifetime of the nuclear reactor can limit the impulse attainable with NEP

this combination might provide higher V than either solar or nuclear

electric single-stage systems

CHOICE OF PROPULSION

Of the various propulsion techniques outlined above the only

ones that are likely to provide solar system escape velocities above

50 kms utilize either sails or nuclear energy

The sail technique could be used with two basic options solar

sailing going in to perhaps 01 AU from the sun and laser sailing

In either case the requirements on the sail are formidable Figure 3

shows solar sail performance attainable with various spacecraft lightshy

ness factors (ratios of solar radiation force on the SC at normal inshy

cidence to solar gravitational force on the SIC) The sail surface

massarea ratios required to attain various V values are listed in

Table 10 For a year 2000 launch it may be possible to attain a sail

surface massarea of 03 gm2 if the perihelion distance is constrained

to 025 AU or more (W Carroll private communication) This ratio

corresponds to an aluminum film about 100 nm thick which would probably

have to be fabricated in orbit With such a sail a V of about 120 kms

might be obtained

33

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300

Jg 200-

X= 0

U

Ln

Uj LU

jLU

z 100II U 0

01 0 01 02 03

PERIHELION RADIUS AU

Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal

incidence)(solar gravitational force on SC) From C Uphoff (private communication)

34

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TABLE 10

PERFORMANCE OF ULTRALIGHT SOLAR SAILS

Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea

Vw aFT1 a F

gm2 gm2 AU kms

025 60 08 20 09

025 100 18 085 04

025 200 55 03 012

01 100 06 27 12

01 200 22 07 03

01 300 50 03 014

Notes

X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)

aT = (total SC mass)(sail area)

p = sail efficiency

= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions

of SC Assumed here IF= 05 aT P = 09

Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain

35

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If the perihelion distance is reduced to 01 AU the solar radiashy

tion force increases but so does the temperature the sail must withstand

With a reflectivity of 09 and an emissivity of 10 the sail temperature

would reach 470C (740 K) so high temperature material would have to

be used Further according to Carroll (ibid) it may never be possible

to obtain an emissivity of 10 with a film mass less than 1 gm2

because of the emitted wavelengththickness ratio For such films an

emissivity of 05 is probably attainable this would increase the temperashy

ture to over 6000 C (870 K) Carbon films can be considered but they

would need a smooth highly reflective surface It is doubtful a sail

surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the

025 AU design

For laser sailing higher reflectivity perhaps 099 can be

attained because the monochromatic incident radiation permits effective

use of interference layers (Carroll ibid) Incident energy flux

equivalent to 700 suns (at 1 AU) is proposed however The high

reflectivity coating reduces the absorbed energy to about the level of

that for a solar sail at 01 AU with problems mentioned above Vs up

to 200 kms might be achieved if the necessary very high power lasers

were available in orbit

-Considering nuclear energy systems a single NEP stage using

fission could provide perhaps 60 to 100 kms V NEP systems have

already been the subject of considerable study and some advanced developshy

ment Confidence that the stated performance can be obtained is thereshy

fore higher than for any of the competing modes Using 2 NEP stages or

a solar electric followed by NEP higher V could be obtained one

preliminary calculation for 2 NEP stages (requiring 3 shuttle launches

or the year 2000 equivalent) gave V = 150 kms

The calculation for a fusion propulsion system indicates 30

spacecraft velocity improvement over fission but at the expense of

orders of magnitude heavier vehicle The cost would probably be proshy

hibitive Moreover controlled fusion has not yet been attained and

development of an operational fusion propulsion system for a year 2000

launch is questionable As to collection of hydrogen enroute to refuel

a fusion reactor this is further in the future and serious question

exists as to whether it will ever be feasible (Martin 1972 1973)

An antimatter propulsion system is even more speculative than a

fusion system and certainly would not be expected by 2000 On the other

36

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hand the very rough calculations indicate an order of magnitude velocity

improvement over fission NEP without increasing vehicle mass Also

the propulsion burn time is reduced by an order of magnitude

On the basis of these considerations a fission NEP system was

selected as baseline for the remainder of the study The very lightshy

weight solar sail approach and the high temperature laser sail approach

may also be practical for a year 2000 mission and deserve further

study The antimatter concept is the most far out but promises orders

of magnitude better performance than NEP Thus in future studies

addressed to star missions antimatter propulsion should certainly be

considered and a study of antimatter propulsion per se is also warranted

37

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MISSION CONCEPT

The concept which evolved as outlined above is for a mission outshy

ward to 500-1000 AU directed toward the incoming interstellar gas

Critical science measurements would be made when passing through the

heliopause region and at as great a range as possible thereafter The

location of the heliopause is unknown but is estimated as 50-100 AU

Measurements at Pluto are also desired Launch will be nominally in

the year 2000

The maximum spacecraft lifetime considered reasonable for a year

2000 launch is 50 years (This is discussed further below) To

attain 500-1000 AU in 50 years requires a heliocentric excess velocity

of 50-100 kms The propulsion technique selected as baseline is NEP

using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP

stages are chosen the first takes the form of an NEP booster stage and the

second is the spacecraft itself The spacecraft with or without an NEP

booster stage is placed in low earth orbit by some descendant of the

Shuttle NEP is then turned on and used for spiral earth escape Use of

boosters with lower exhaust velocity to go to high earth orbit or earth

escape is not economical The spiral out from low earth orbit to earth

escape uses only a small fraction of the total NEP burn time and NEP proshy

pellant

After earth escape thrusting continues in heliocentric orbit A

long burn time is needed to attain the required velocity 5 to 10 years are

desirable for single stage NEP (see below) and more than 10 years if two

NEP stages are used The corresponding burnout distance depending on the

design may be as great as 200 AU or even more Thus propulsion may be on

past Pluto (31 AU from the sun in 2005) and past the heliopause To measure

the mass of Pluto a coasting trajectory is needed thrust would have to be

shut off temporarily during the Pluto encounter The reactor would continue

operating at a low level during the encounter to furnish spacecraft power

Attitude control would preferably be by momentum wheels to avoid any disturshy

bance to the mass measurements Scientific measurements including imagery

would be made during the fast flyby of Pluto

38

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After the Pluto encounter thrusting would resume and continue until

nominal thrust termination (burnout) of the spacecraft Enough propelshy

lant is retained at spacecraft burnout to provide attitude control (unloadshy

ing the momentum wheels) for the 50 year duration of the extended mission

At burnout the reactor power level is reduced and the reactor provides

power for the spacecraft including the ion thrusters used for attitude control

A very useful add-on would be a Pluto Orbiter This daughter spacecraft

would be separated early in the mission at approximately the time solar

escape is achieved Its flight time to Pluto would be about 12 years and its

hyperbolic approach velocity at Pluto about 8 kms

The orbiter would be a full-up daughter spacecraft with enough chemical

propulsion for midcourse approach and orbital injection It would have a

full complement of science instruments (including imaging) and RTG power

sources and would communicate directly to Earth

Because the mass of a dry NEP propulsion system is much greater than

that required for the other spacecraft systems the added mass of a daughter

SC has relatively little effect on the total inert mass and therefore relatively

little effect on propulsive performance The mother NEP spacecraft would fly by

Pluto 3 or 4 years after launch so the flyby data will be obtained at least

5 years before the orbiter reaches Pluto Accordingly the flyby data can be

used in selecting the most suitable orbit for the daughter-spacecraft

If a second spacecraft is to be flown out parallel to the solar axis

it could be like the one going toward the incoming interstellar gas but

obviously would not carry an orbiter Since the desired heliocentric escape

direction is almost perpendicular to the ecliptic somewhat more propulsive

energy will be required than for the SC going upwind if the same escape

velocity is to be obtained A Jupiter swingby may be helpful An NEP booster

stage would be especially advantageous for this mission

39

77-70

MASS DEFINITION AND PROPULSION

The NEP system considered is similar to those discussed by Pawlik and

Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation

the dry NEP system should be approximately 30-35 percent of the spacecraft

mass A balance is then required between the net spacecraft and propellant

with mission energy and exhaust velocity being variable For the very high

energy requirements of the extraplanetary mission spacecraft propellant

expenditure of the order of 40-60 percent may be appropriate A booster

stage if required may use a lower propellant fraction perhaps 30 percent

Power and propulsion system mass at 100-140 kms exhaust velocity will

be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy

version efficiency and ion thrusters Per unit mass may decrease slightly

at higher power levels and higher exhaust velocity Mercury propellant is

desired because of its high liquid density - 136 gcm3 or 13600 kgm3

Mercury is also a very effective gamma shield If an NEP booster is to be

used it is assumed to utilize two 500 We units

The initial mass in low earth orbit (M ) is taken as 32000 kg for

the spacecraft (including propulsion) and as 90000 kg for the spacecraft

plus NEP booster 32000 kg is slightly heavier than the 1977 figure for

the capability of a single shuttle launch The difference is considered

unimportant because 1977 figures for launch capability will be only of

historical interest by 2000 90000kg for the booster plus SC would reshy

quire the year 2000 equivalent of three 1977 Shuttle launches

Figure 4 shows the estimated performance capabilities of the propulsion

system for a single NEP stage

A net spacecraft mass of approximately 1200 kg is assumed and may be broken

out in many ways Communication with Earth is a part of this and may trade off

with on-board automation computation and data processing Support structure for

launch of daughter spacecraft may be needed Adaptive science capability is also

possible The science instruments may be of the order of 200-300 kg (including

a large telescope) and utilize 200 kg of radiation shielding (discussed below)

and in excess of 100 W of power Communications could require as much as 1 kW

40

140 140

120 120

- w

0 u

-J0 a W=

LUlt

HV

70

60

_u

gt

--Ve = 100 Msc = 0

Ve = 120 M = 2000

= 140 Mpsc = 4000 e ~V00 FORZ

= =0x 120 Mpc = 2000

e = Vze = 140 Mpsc = 4000

80

-60

U

lt

z 0

LU

z

U o -J

40

20-

LUn

40

- 20

3

0 0 2 4 6

NET SPACECRAFT

8 10 12

MASS (EXCLUDING PROPULSION)

14

kg x 10 3

16 0

18

Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe

Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =

a= = 32000 kg

M O = initial mass (in low Earth orbit)

Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)

Ve = exhaust velocity (kms)

77-70

One to two kWe of auxiliary power is a first order assumption

The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical

propellant This allows a total AV of approximately 3500 ms and should

permit a good capture orbit at Pluto

The reactor burnup is taken to be the equivalent of 200000 hours at

full power This will require providing reactor control capability beyond

that in existing NEP concepts This could consist of reactivity poison

rods or other elements to be removed as fission products build up together

with automated power system management to allow major improvement in adaptive

control for power and propulsion functions The full power operating time

is however constrained to 70000 h (approximately 8 yr) The remaining

burnup is on reduced power operation for SC power and attitude control

At 13 power this could continue to the 50 yr mission duration

Preliminary mass and performance estimates for the selected system are

given in Table 11 These are for a mission toward the incoming interstellar

wind The Pluto orbiter separated early in the mission makes very little

difference in the overall performance The NEP power level propellant

loading and booster specific impulse were not optimized in these estimates

optimized performance would be somewhat better

According to Table 11 the performance increment due to the NEP booster

is not great Unless an optimized calculation shows a greater increment

use of the booster is probably not worthwhile

For a mission parallel to the solar axis a Jupiter flyby would permit

deflection to the desired 830 angle to the ecliptic with a small loss in VW

(The approach V at Jupiter is estimated to be 23 kms)

in

42

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TABLE 11

Mass and Performance Estimates for Baseline System

(Isp and propellant loading not yet optimized)

Allocation Mass kg

Spacecraft 1200

Pluto orbiter (optional) 1500

NEP (500 kWe) 8500

Propellant Earth spiral 2100

Heliocentric 18100

Tankage 600

Total for 1-stage (Mo earth orbit) 32000

Booster 58000

Total for 2-stage (M earth orbit) 90000

Performance 1 Stage 2 Stages

Booster burnout Distance 8 AU

Hyperbolic velocity 25 kms

Time - 4 yr

Spacecraft burnout Distance (total) 65 155 AU

Hyperbolic velocity 105 150 kms

Time (total) 8 12 yr

Distance in 20 yr 370 410 AU

50 yr 1030 1350 AU

43

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INFORMATION MANAGEMENT

DATA GENERATION

In cruise mode the particles and fields instruments if reading

continuously will generate 1 to 2 kbs of data Engineering sensors

will provide less Spectrometers may provide higher raw data rates

but only occasional spectrometric observations would be needed Star

TV if run at 10 framesday (exposures would probably be several hours)

at 108 bframe would provide about 10 kbs on the average A typical

TV frame might include 10 star images whose intensity need be known

only roughly for identification Fifteen position bits on each axis

and 5 intensity bits would make 350 bframe or 004 bs of useful data

Moreover most of the other scientific quantities mentioned would be

expected to change very slowly so that their information rate will be

considerably lower than their raw data rate Occasional transients

may be encountered and in the region of the heliopause and shock rapid

changes are expected

During Pluto flyby data accumulates rapidly Perhaps 101 bits

mostly TV will be generated These can be played back over a period

of weeks or months If a Pluto orbiter is flown it could generate

1010 bday-or more an average of over 100 kbs

INFORMATION MANAGEMENT SYSTEM

Among the functions of the information handling system will be

storage and processing of the above data The system compresses the data

removing the black sky that will constitute almost all of the raw bits

of the star pictures It will remove the large fraction of bits that

need not be transmitted when a sensor gives a steady or almost-steady

reading It will vary its processing and the output data stream to

accommodate transients during heliopause encounter and other unpredicshy

table periods of high information content

The spacecraft computers system will provide essential support

to the automatic control of the nuclear reactor It will also support

control monitoring and maintenance of the ion thrusters and of the

attitude control system as well as antenna pointing and command processshy

ing

44

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According to James et al (1976)the following performance is proshy

jected for a SC information management system for a year 2000 launch

Processing rate 109 instructions

Data transfer rate -i09 bs

Data storage i014 b

Power consumption 10 - 100 W

Mass -30 kg

This projection is based on current and foreseen state of the art

and ignores the possibility of major breakthroughs Obviously if

reliability requirements can be met the onboard computer can provide

more capability than is required for the mission

The processed data stream provided by the information management

system for transmission to earth is estimated to average 20-40 bs during

cruise Since continuous transmission is not expected (see below) the

output rate during transmission will be higher

At heliosphere encounter the average rate of processed data is

estimated at 1-2 kbs

From a Pluto encounter processed data might be several times 1010

bits If these are returned over a 6-month period the average rate

over these months is about 2 kbs If the data are returned over a

4-day period the average rate is about 100 kbs

OPERATIONS

For a mission lasting 20-50 years with relatively little happenshy

ing most of the time it is unreasonable to expect continuous DSN

coverage For the long periods of cruise perhaps 8 h of coverage per

month or 1 of the time would be reasonable

When encounter with the heliopause is detected it might be possible

to increase the coverage for a while 8 hday would be more than ample

Since the time of heliosphere encounter is unpredictable this possishy

bility would depend on the ability of the DSN to readjust its schedule

quickly in near-real time

For Pluto flyby presumably continuous coverage could be provided

For Pluto orbiters either 8 or 24 hday of coverage could be provided

for some months

45

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DATA TRANSMISSION RATE

On the basis outlined above the cruise data at 1 of the time

would be transmitted at a rate of 2-4 kbs

If heliopause data is merely stored and transmitted the same 1 of

the time the transmission rate rises to 100-200 kbs An alternative

would be to provide more DSN coverage once the heliosphere is found

If 33 coverage can be obtained the rate falls to 3-7 kbs

For Pluto flyby transmitting continuously over a 6-month period

the rate is 2 kbs At this relatively short range a higher rate say

30-100 kbs would probably be more appropriate This would return the

encounter data in 4 days

The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday

or 90-150 kbs at 8 hday

TELEMETRY

The new and unique feature of establishing a reliable telecommunicashy

tions link for an extraplanetary mission involves dealing with the

enormous distance between the spacecraft (SC) and the receiving stations

on or near Earth Current planetary missions involve distances between

the SC and receiving stations of tens of astronomical units (AU) at

most Since the extraplanetary mission could extend this distance

to 500 or 1000 AU appropriate extrapolation of the current mission

telecommunication parameters must be made Ideally this extrapolation

should anticipate technological changes that will occur in the next

20-25 years and accordingly incorporate them into the telecommunicashy

tions system design In trying to achieve this ideal we have developed

a baseline design that represents reasonably low risk Other options

which could be utilized around the year 2000 but which may require

technological advancement (eg development of solid state X-band or

Ku-band transmitters) or may depend upon NASAs committing substantial

funds for telemetry link reconfiguration (eg construction of a spaceshy

borne deep space receiver) are examined to determine how they might

affect link capabilities

In the following paragraphs the basic model for the telecommunicashy

tions link is developed Through the range equation transmitted and

received powers are related to wavelength antenna dimensions and

separation between antennas A currently used form of coding is

46

77-70

assumed while some tracking loop considerations are examined A baseline

design is outlined The contributions and effects of various components

to link performance is given in the form of a dB table breakdown

Other options of greater technological or funding risk are treated

Finally we compare capability of the various telemetry options with

requirements for various phases of the mission and identify the teleshy

metry - operations combinations that provide the needed performance

THE TELECOMMUNICATION MODEL

Range Equation

We need to know how much transmitted power is picked up by

the receiving antenna The received power Pr is given approximately by

2 PPr = Ar(R)r i

where

= product of all pertinent efficiencies ie transmitter

power conversion efficiency antenna efficiencies etc

P = power to transmitter

AtA = areas of transmitter receiver antennas respectivelyr

X = wavelength of transmitted radiation

R = range to spacecraft

This received signal is corrupted by noise whose effective power spectral

density will be denoted by NO

Data Coding Considerations

We are assuming a Viterbi (1967) coding scheme with constraint

length K = 7 and rate v = 13 This system has demonstrated quite good

performance producing a bit error rate (BER) of 10- 4 when the informashy

tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable

schemes are developed in the next 20-25 years they should certainly be

used

Tracking Loop Considerations

Because of the low received power levels that can be expected

in this mission some question arises as to whether the communication

47

77-70

system should be coherent or non-coherent The short term stability

of the received carrier frequency and the desired data rate R roughly

determine which system is better From the data coding considerations

we see that

PDIN0 DR 2 RD (2)

where PD is the power allocated to the data Standard phase-locked D 2

loop analysis (Lindsey 1972) gives for the variance a of the phase

error in the loop

2 NO BLPL (3)

where PL is the power allocated to phase determination and BL is the

2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy

table operation so

eL N0 Z 100 BL (4)

The total received power Pr (eq (1) ) is the sum of P L and PD To

minimize PrN subject to the constraint eqs (2) and (4) we see that

a fraction

2D

(5)100 BL + 2

of the received power must go into the data Sincecoherent systems are

3 dB better than non-coherent systems for binary signal detection

(Wozencraft and Jacobs 1965) coherent demodulation is more efficient

whenever

Z 50 BL (6)

48

77-70

Current deep space network (DSN) receivers have BL 110 Hz so for data

rates roughly greater than 500 bitss coherent detection is desirable

However the received carrier frequencies suffer variations from

Doppler rate atmospheric (ionospheric) changes oscillator drifts etc

If received carrier instabilities for the extraplanetary mission are

sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy

quate then data rates greater than 50 bitss call for coherent

demodulation

These remarks are summarized by the relation between PrIN and

data rate R

2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)

This relation is displayed in Figure 5 where PrIN is plotted vs R for

BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the

approach of PrIN to its asymptotic value of 2 R could be made slightly

faster by techniques employing suppressed carrier tracking loops which

utilize all the received power for both tracking and data demodulation

However for this study these curves are sufficiently accurate to

ascertain Pr IN levels necessary to achieve desired data rates

BASELINE DESIGN

Parameters of the System

For a baseline design we have tried to put together a system

that has a good chance of being operational by the year 2000 Conshy

sequently in certain areas we have not pushed current technology but

have relied on fairly well established systems In other areas we

have extrapolated from present trends but hopefully not beyond developshy

ments that can be accomplished over 20-25 years This baseline design

will be derived in sufficient detail so that the improvement afforded

by the other options discussed in the next section can be more

easily ascertained

First we assume that received carrier frequency stabilities

allow tracking with a loop bandwidth BL 1 Ez This circumstance

is quite likely if an oscillator quite stable in the short term is carried

49

77-70

on the SC if the propulsion systems are not operating during transshy

mission at 1000 AU (Doppler rate essentially zero) and if the receiver

is orbiting Earth (no ionospheric disturbance) Second we assume

data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU

are desired From the discussion preceding eq (6) and Figure 5 we

see this implies a coherent demodulation system with PrN to exceed

25 dB

As a baseline we are assuming an X-band system (X = 355 cm) with

40 watts transmitter power We assume the receiving antenna is on Earth

(if this assumption makes BL 11 Hz unattainable then the value of Pr IN

for the non-coherent system only increases by 1 dB) so the system noise

temperature reflects this accordingly

Decibel Table and Discussion

In Table 12 we give the dB contributions from the various parashy

meters of the range eq (1) loop tracking and data coding By design

the parameters of this table give the narrowest performance margins

If any of the other options of the next section can be realized pershy

formance margin and data rate should correspondingly increase

The two antenna parameters that are assumed require some

explanation A current mission (SEASAT-A) has an imaging radar antenna

that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter

spaceborne antenna should pose no difficulty by the year 2000 A 100 m

diameter receiving antenna is assumed Even though the largest DSN

antenna is currently 64 m an antenna and an array both having effecshy

tive area _gt (100 m)2 will be available in West Germany and in this country

in the next five years Consequently a receiver of this collecting

area could be provided for the year 2000

OPTIONS

More Power

The 40 watts transmitter power of the baseline should be

currently realizable being only a factor of 2 above the Voyager value

This might be increased to 05 - 1 kW increasing received signal power

by almost 10-15 dB allowing (after some increase in performance margin)

a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The

problem of coupling this added energy into the transmission efficiently may

cause some difficulty and should definitely be investigated

50

77-70

70

60-

N

50-

NON-COHERENT

COHERENT BL 10 Hz

0 z

L 30shy

---- BL 10 Hz

20shy

10-

10

0

0

I

10

Fig 5

BL = Hz

CO-COHERENTH

BL =1Hz

I II

20 30 40

DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density

I

50 60

51

77-70

Table 12 BASELINE TELEMETRY AT 1000 AU

No Parameter Nominal Value

1 Total Transmitter power (dBm) (40 watts) 46

2 Efficiency (dB) (electronics and antenna losses) -9

3 Transmitting antenna gain (dB) (diameter = 15 m) 62

4 Space loss (dB) (A47R)2 -334

X = 355 cm R = 1000 AU

5 Receiving antenna gain (dB) (diameter = 100m) 79

6 Total received power (dBm) (P r) -156

7 Receiver noise spectral density (dBmHz) (N0 )

kT with T = 25 K -185

Tracking (if BL = 1 H4z is achievable)

8 Carrier powertotal power 9dB) -5

(100 B L(100BL + 2 R))

9 Carrier power (dBm) (6+ 8) -161

10 Threshold SNR in 2 BL (dB) 20

11 Loop noise bandwidth (dB) (BL) 0

12 Threshold carrier power (dBm) (7 + 10 + 11) -165

13 Performance margin (dB) (9 - 12) 4

Data Channel

14 Estimated loss (waveform distortion bit sync

etc) (B) -2

15 Data powertotal power (dB) -2

(2RD(100BL+ 2RD ) )

16 Data power (dBm) (6 + 14 + 15) -160

17 Threshold data power (dBm) (7 + 17a + 17b) -162

-a Threshold PrTN0 (BER = 10 4 3

b Bit rate (dB BPS) 20

18 Performance margin (dB) (16 - 17) 2

If a non-coherent system must be used each of these values are reduced by

approximately 1 dB

52

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Larger Antennas and Lower Noise Spectral Density

If programs calling for orbiting DSN station are funded then

larger antennas operating at lower noise spectral densitites should beshy

come a reality Because structural problems caused by gravity at the

Earths surface are absent antennas even as large as 300 m in diameter

have been considered Furthermore assuming problems associated with

cryogenic amplifiers in space can be overcome current work indicates

X-band and Ku-band effective noise temperatures as low as 10 K and 14 K

respectively (R C Clauss private communication) These advances

would increase PrN by approximately 12-13 dB making a link at data

rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible

Higher Frequencies

Frequencies in the Ku-band could represent a gain in directed

power of 5-10 dB over the X-band baseline but probably would exhibit

noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers

Also the efficiency of a Ku-band system would probably be somewhat less

than that of X-band Without further study it is not apparent that

dramatic gains could be realized with a Ku-band system

Frequencies in the optical or infrared potentially offer treshy

mendous gains in directed power However the efficiency in coupling

the raw power into transmission is not very high the noise spectral

density is much higher than that of X-band and the sizes of practical

antennas are much smaller than those for microwave frequencies To

present these factors more quantitatively Table 13 gives parameter conshy

tributions to Pr and N We have drawn heavily on Potter et al (1969) and

on M S Shumate and R T Menzies (private communication) to compile

this table We assume an orbiting receiver to eliminate atmospheric

transmission losses Also we assume demodulation of the optical signal

can be accomplished as efficiently as the microwave signal (which is

not likely without some development) Even with these assumptions

PrN for the optical system is about 8 dB worse than that for X-band

with a ground receiver

Pointing problems also become much more severe for the highly

directed optical infrared systems Laser radiation at wavelength 10 Pm

6from a 1 m antenna must be pointed to 5 x 10- radians accuracy

The corresponding pointing accuracy of the baseline system is 10- 3 radians

53

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Table 13 OPTICAL TELEMETRY AT 1000 AU

Nominal ValueParameterNo

461 Total Transmitter power (dBm) (40 watts)

2 Efficiency (dB) (optical pumping antenna losses -16

and quantum detection)

3 Transmitting antenna gain (dB) (diameter = 1 m) 110

Space loss (dB) (A4r) 2 4

X =lO pm r =1000 AU -405

5 Receiving antenna gain (dB) (diameter = 3m) 119

6 Total Received power (dBm) (P ) -146

7

-

Receiver noise spectral density (dBmHz) (N0) -167

(2 x 10 2 0 wattHZ)

54

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Higher Data Rates

This mission may have to accommodate video images from Pluto

The Earth-Pluto separation at the time of the mission will be about 31

AU The baseline system at 31 AU could handle approximately 105 bs

For rates in excess of this one of the other option enhancements would

be necessary

SELECTION OF TELEMETRY OPTION

Table 14 collects the performance capabilities of the various

telemetry options Table 15 shows the proposed data rates in various

SC systems for the different phases of the mission In both tables 2

the last column lists the product (data rate) x (range) as an index

of the telemetry capability or requirements

Looking first at the last column of Table 15 it is apparent that

the limiting requirement is transmittal of heliopause data if DSN

coverage can be provided only 1 of the time If DSN scheduling is

sufficiently flexible that 33 coverage can be cranked up within a

month or so after the heliosphere is detected then the limiting

requirement is transmittal of cruise data (at 1 DSN coverage) For

these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2

tively2-40 x 10 and 5-10 x 10 (bs) AU

Looking now at the last column of Table 14 to cover the cruise

requirement some enhancement over the baseline option will be needed

Either increasing transmitter power to 05-1 kW or going to orbiting DSN

stations will be adequate No real difficulty is seen in providing the

increased transmitter power if the orbiting DSN is not available

If however DSN coverage for transmittal of recorded data from

the unpredictable heliosphere encounter is constrained to 1 of the

time (8 hmonth) then an orbital DSN station (300-m antenna) will be

needed for this phase of the mission as well as either increased transshy

mitter power or use of K-band

55

TABLE 14

TELEMETRY OPTIONS

(Data Rate) Data Rate (bs) x (Range)

Improvement OPTIONS Over Baseline

dB At

1000 AU At

500 AU At

150 AU At 31 AU (bs) bull AU2

Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108

More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109

Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109

K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)

Both more power and orbiting DSN

X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010

TABLE 15

PROPOSED DATA RATES

Tele-Communi- Estimated Data Rate bs (Data

cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2

Phase AU Data Average Data Transmitting bs Au2

Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108

Heliopause 50- 112-15 x 10 31-2

1-2 x 103 x 105 001 2-40 x 108

150 033 08-15 x 107

l SI5 x 105 033 1 x 108

Pluto Flyby -31 1-2 x 10 3-5 x 104

1 11 (10 total

I bits)

10 (3 x 10 bits)

3x10100 x 10

3 x10

15 4 9-15 x 104 033 9-15 x 107

Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0

To return flyby data in 4 days

77-70

RELATION OF THE MISSION TO

SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE

The relation of this mission to the search for extraterrestrial

intelligence appears to lie only in its role in development and test

of technology for subsequent interstellar missions

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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS

LIFETIME

A problem area common to all SC systems for this mission is that of

lifetime The design lifetime of many items of spacecraft equipment is now

approaching 7 years To increase this lifetime to 50 years will be a very

difficult engineering task

These consequences follow

a) It is proposed that the design lifetime of the SC for this mission

be limited to 20 years with an extended mission contemplated to a total of

50 years

b) Quality control and reliability methods such as failure mode effects

and criticality analysis must be detailed and applied to the elements that

may eventually be used in the spacecraft so as to predict what the failure

profile will be for system operating times that are much longer than the test

time and extend out to 50 years One approach is to prepare for design and

fabrication from highly controlled materials whose failure modes are

completely understood

c) To the extent that environmental or functional stresses are conceived

to cause material migration or failure during a 50-year period modeling and

accelerated testing of such modes will be needed to verify the 50-year scale

Even the accelerated tests may require periods of many years

d) A major engineering effort will be needed to develop devices circuits

components and fabrication techniques which with appropriate design testing

and quality assurance methods will assure the lifetime needed

PROPULSION AND POWER

The greatest need for subsystem development is clearly in propulsion

Further advance development of NEP is required Designs are needed to permit

higher uranium loadings and higher burnup This in turn will require better

control systems to handle the increased reactivity including perhaps throw-away

control rods Redundancy must be increased to assure long life and moving

parts will need especial attention Development should also be aimed at reducing

system size and mass improving efficiency and providing better and simpler

thermal control and heat dissipation Simpler and lighter power conditioning

59

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is needed as are ion thrusters with longer lifetime or self-repair capability

Among the alternatives to fission NEP ultralight solar sails and laser

sailing look most promising A study should be undertaken of the feasibility

of developing ultra-ltght solar sails (sails sufficiently light so that the

solar radiation pressure on the sail and spacecraft system would be greater

than the solar gravitational pull) and of the implications such development

would have for spacecraft design and mission planning Similarly a study

should be made of the possibility of developing a high power orbiting laser

system together with high temperature spacecraft sails and of the outer planet

and extraplanetary missions that could be carried out with such laser sails

Looking toward applications further in the future an antimatter propulshy

sion system appears an exceptionally promising candidate for interstellar

missions and would be extremely useful for missions within the solar system

This should not be dismissed as merely blue sky matter-antimatter reactions

are routinely carried out in particle physics laboratories The engineering

difficulties of obtaining an antimatter propulsion system will be great conshy

taining the antimatter and producing it in quantity will obviously be problems

A study of possible approaches would be worthwhile (Chapline (1976) has suggested

that antimatter could be produced in quantity by the interaction of beams of

heavy ions with deuteriumtritium in a fusion reactor) Besides this a more

general study of propulsion possibilities for interstellar flight (see Appendix

C) should also be considered

PROPULSIONSCIENCE INTERFACE

Three kinds of interactions between the propulsionattitude control

system and science measurements deserve attention They are

1) Interaction of thrust and attitude control with mass measurements

2) Interaction of electrical and magnetic fields primarily from the

thrust subsystem with particles and fields measurements

3) Interactions of nuclear radiation primarily from the power subsystem

with photon measurements

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Interaction of thrust with mass measurements

It is desired to measure the mass of Pluto and of the solar system as

a whole through radio tracking observations of the spacecraft accelerations

In practice this requires that thrust be off during the acceleration obsershy

vations

The requirement can be met by temporarily shutting off propulsive

thrusting during the Pluto encounter and if desired at intervals later on

Since imbalance in attitude control thrusting can also affect the trajectory

attitude control during these periods should preferably be by momentum wheels

The wheels can afterwards be unloaded by attitude-control ion thrusters

Interaction of thrust subsystem with particles and fields measurements

A variety of electrical and magnetic interference with particles and fields

measurements can be generated by the thrust subsystem The power subsystem can

also generate some electrical and magnetic interference Furthermore materials

evolved from the thrusters can possibly deposit upon critical surfaces

Thruster interferences have been examined by Sellen (1973) by Parker et al

(1973) and by others It appears that thruster interferences should be reducshy

ible to acceptable levels by proper design but some advanced development will

be needed Power system interferences are probably simpler to handle Essenshy

tially all the thruster effects disappear when the engines are turned off

Interaction of power subsystem with photon measurements

Neutrons and gamma rays produced by the reactor can interfere with

photon measurements A reactor that has operated for some time will be highly

radioactive even after it is shut down Also exposure to neutrons from the

reactor will induce radioactivity in other parts of the spacecraft In the

suggested science payload the instruments most sensitive to reactor radiation

are the gamma-ray instruments and to a lesser degree the ultraviolet

spectrometer

A very preliminary analysis of reactor interferences has been done

Direct neutron and gamma radiation from the reactor was considered and also

neutron-gamma interactions The latter were found to be of little significance if

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the direct radiation is properly handled Long-lived radioactivity is no problem

except possibly for structure or equipment that uses nickel Expected

flux levels per gram of nickel are approximately 0007 ycm2-s

The nuclear reactor design includes neutron and gamma shadow shielding

to fully protect electronic equipment from radiation damage Requirements

are defined in terms of total integrated dose Neutron dose is to be limited

to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is

assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma

shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is

included in the 8500 kg estimate for the propulsion system

For the science instruments it is the flux that is important not total

dose The reactor shadow shield limits the flux level to 16 x 103 neutrons

or gammascm22 This is apparently satisfactory for all science sensors except

the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22

cm -s and 01 gammacm -s Such reduction is most economically accomplished by local

shielding The gamma ray transient detector should have a shielded area of

2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten

thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of

this shielding is approximately 235 kg and is included in the spacecraft mass

estimate It may also be noted that the gamma ray transient detector is probshy

ably the lowest-priority science instrument An alternative to shielding it

would be to omit this instrument from the payload (The gamma ray spectrometer

is proposed as an orbiter instrument and need not operate until the orbiter is

separated from the NEP mother spacecraft) A detailed Monte Carlo analysis

and shield development program will be needed to assure a satisfactory solution

of spacecraft interfaces

TELECOMMUNICATIONS

Microwave vs Optical Telemetry Systems

Eight years ago JPL made a study of weather-dependent data links in

which performance at six wavelengths ranging from S-band to the visible was

analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy

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independent) should determine which wavelengths are the most advantageous

The work of this report indicates X-band or K-band are prime candidates but

a more thorough effort is required that investigates such areas as feasibility

of constructing large spaceborne optical antennas efficiency of power convershy

sion feasibility of implementing requisite pointing control and overall costs

Space Cryogenics

We have assumed cryogenic amplifiers for orbiting DSN stations in order

to reach 4-5 K amplifier noise contributions Work is being done that indicates

such performance levels are attainable (R C Clauss private communication

D A Bathker private communication) and certainly should be continued At

the least future studies for this mission should maintain awareness of this

work and probably should sponsor some of it

Lifetime of Telecommunications Components

The telecommunications component most obviously vulnerable to extended

use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies

have demonstrated 11-12 year operating lifetimes (H K Detweiler private

communication also James et al 1976) and perhaps their performance over

20-50 year intervals could be simulated However the simple expedient

measure of carrying 4-5 replaceable TWTs on the missions might pose a

problem since shelf-lifetimes (primarily limited by outgasing) are not known

as well as the operating lifetimes A more attractive solution is use of

solid-state transmitters Projections indicate that by 1985 to 1990 power

transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few

wattsdevice respectively with lifetimes of 50-100 years (J T Boreham

private communication) Furthermore with array feed techniques 30-100

elements qould be combined in a near-field Cassegrainian reflector for

signal transmission (Boreham ibid) This means a Ku-band system could

probably operate at a power level of 50-200 watts and an X-band system

could likely utilize 02 - 1 kW

Other solid state device components with suitable modular replacement

strategies should endure a 50 year mission

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Baseline Enhancement vs Non-Coherent Communication System

The coherent detection system proposed requires stable phase reference

tracking with a closed loop bandwidth of approximately 1 Hz Of immediate

concern is whether tracking with this loop bandwidth will be stable Moreover

if the tracking is not stable what work is necessary to implement a non-coherent

detection system

The most obvious factors affecting phase stability are the accelerations

of the SIC the local oscillator on the SC and the medium between transmitter

and receiver If the propulsion system is not operating during transmission

the first factor should be negligible However the feasibility of putting on

board a very stable (short term) local oscillator with a 20-50 year lifetime

needs to be studied Also the effect of the Earths atmosphere and the

Planetary or extraplanetary media on received carrier stability must be

determined

If stability cannot be maintained then trade-off studies must be

performed between providing enhancements to increase PrIN and employing

non-coherent communication systems

INFORMATION SYSTEMS

Continued development of the on-board information system capability

will be necessary to support control of the reactor thrusters and other

portions of the propulsion system to handle the high rates of data acquishy

sition of a fast Pluto flyby to perform on-board data filtering and compresshy

sion etc Continued rapid development of information system capability to

very high levels is assumed as mentioned above and this is not considered

to be a problem

THERMAL CONTROL

The new thermal control technology requirement for a mission beyond the

solar system launched about 2000 AD involve significant advancements in thershy

mal isolation techniques in heat transfer capability and in lifetime extension

Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken

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of it for passive cooling of detectors in scientific instruments and also

for the operation of cryogenic computers If cryogenic computer systems

and instruments can be developed the gains in reliability lifetime and

performance can be considered However a higher degree of isolation will

be required to keep certain components (electronics fluids) warm in extrashy

planetary space and to protect the cryogenic experiments after launch near

Earth This latter is especially true if any early near-solar swingby is

used to assist escape in the mission A navigational interest in a 01 AU

solar swingby would mean a solar input of 100 suns which is beyond any

anticipated nearterm capability

More efficient heat transfer capability from warm sources (eg RTGs)

to electronicssuch as advanced heat pipes or active fluid loops will be

necessary along with long life (20-50 years) The early mission phase also

will require high heat rejection capability especially for the cryogenic

experiments andor a near solar swingby

NEP imposes new technology requirements such as long-term active heat

rejection (heat pipes noncontaminated radiators) and thermal isolation

NEP also might be used as a heat source for the SC electronics

Beyond this the possibility of an all-cryogenic spacecraft has been

suggested by Whitney and Mason (see Appendix C) This may be more approshy

priate to missions after 2000 but warrants study Again there would be a

transition necessary from Earth environment (one g plus launch near solar)

to extraplanetary environment (zero g cryogenic) The extremely low power

(-1 W)requirement for superconducting electronics and the possibility of

further miniaturation of the SC (or packing in more electronics with low

heat dissipation requirements) is very attractive Also looking ahead the

antimatter propulsion system mentioned above would require cryogenic storage

of both solid hydrogen and solid antihydrogen using superconducting (cryo)

magnets and electrostatic suspension

Table 16 summarizes the unusual thermal control features of an extrashy

planetary mission

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TABLE 16

T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS

Baseline Mission

1 Natural environment will be cryogenic

a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary

space bull i Can equipment take slow cooling

ii Well insolated near sunt iii Cryogenic control needed near Eartht

2 NEP

a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design

Not Part of Baseline Mission

3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC

a) Requires high isolation b) Could be used as source of heat for warm SC

i Fluid loop - active devices will wear - lifetime problem

ii Heat pipes c) Must provide means of cooling RTGs

4 Close Solar Swingby - 01 AU

a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU

Significant technology advancement required

Not part of baseline mission

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COMPONENTS AND MATERIALS

By far the most important problem in this area is prediction of long-term

materials properties from short-term tests This task encompasses most of the

other problems noted Sufficient time does not exist to generate the required

material properties in real time However if in the time remaining we can

establish the scaling parameters the required data could be generated in a

few years Hence development of suitable techniques should be initiated

Another critical problem is obtaining bearings and other moving parts with

50 years lifetime Effort on this should be started

Less critical but also desirable are electronic devices that are inherently

radiation-resistant and have high life expectancy DOE has an effort undershy

way on this looking both at semiconductor devices utilizing amorphous semishy

conductors and other approaches that do not depend on minority carriers and

at non-semiconductor devices such as integrated thermonic circuits

Other special requirements are listed in Table 17

SCIENCE INSTRUMENTS

Both the problem of radiation compatibility of science instruments with NEP

propulsion and the problem of attaining 50-year lifetime have been noted above

Many of the proposed instruments have sensors whose lifetime for even current

missions is of concern and whose performance for this mission is at best uncershy

tain Instruments in this category such as the spectrometers and radiometers

should have additional detector work performed to insure reasorvable-performance

Calibration of scientific instruments will be very difficult for a 20-50 year

mission Even relatively short term missions like Viking and Voyager pose

serious problems in the area of instrument stability and calibration verificashy

tion Assuming that reliable 50-year instruments could be built some means

of verifying the various instrument transfer functions are needed Calibration

is probably the most serious problem for making quantitative measurements on a

50-year mission

The major problems in the development of individual science instruments

are listed below These are problems beyond those likely to be encountered

and resolved in the normal course of development between now and say 1995

or 2000

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77-70 TABLE 17

TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS

1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator

2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator

3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation

4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System

5 Wear and Lubrication 55 Bearings

6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels

7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects

8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels

9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture

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Neutral Gas Mass Spectrometer

Designing a mass spectrometer to measure the concentration of light gas

species in the interstellar medium poses difficult questions of sensitivity

Current estimates of H concentration in the interstellar medium near the

solar system are 10 --10 atomcm and of He contraction about 10 atomcm

(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974

Freeman et al 1977 R Carlson private communication Fahr et al 1977

Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic

relative abundances the corresponding concentration of C N 0 is 10 to

- 410 atomcm3 and of Li Be B about 10-10 atomcm3

These concentrations are a long way beyond mass spectrometer present

capabilities and it is not clear that adequate capabilities can be attained

2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy

siderable development effort Included in the effort should be

a) Collection Means of collecting incoming gas over a substantial

frontal area and possibly of storing it to increase the input rate

and so the SN ratio during each period of analysis

b) Source Development of ionization sources of high efficiency

and satisfying the other requirements

c) Lifetime Attaining a 50-year lifetime will be a major problem

especially for the source

d) SN Attaining a satisfactory SN ratio will be a difficult

problem in design of the whole instrument

Thus if a mass spectrometer suitable for the mission is to be provided

considerable advanced development work-will be needed

Camera Field of View vs Resolution

Stellar parallax measurements present a problem in camera design because

of the limited number of pixelsframe in conventional and planned spacecraft

cameras For example one would like to utilize the diffraction-limited resoshy

lution of the objective For a 1-m objective this is 012 To find the

center of the circle of confusion accurately one would like about 6 measureshy

ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad

(Note that this also implies fine-pointing stability similar to that for earthshy

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orbiting telescopes) But according to James et al (1976) the number of

elements per frame expected in solid state cameras by the year 2000 is 106

for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000

the field of view for the case mentioned would be 30O0 x 002 = 1 minute of

arc At least five or six stars need to be in the field for a parallax

measurement Thus a density of 5 stars per square minute or 18000 stars

per square degree is needed To obtain this probably requires detecting

stars to about magnitude 26 near the galactic poles and to magnitude 23

near galactic latitude 45 This would be very difficult with a 1-m telescope

A number of approaches could be considered among them

a) Limit parallax observations to those portions of the sky having

high local stellar densities

b) Use film

c) Find and develop some other technique for providing for more

pixels per frame than CCDs and vidicons

d) Sense the total irradiation over the field and develop a masking

technique to detect relative star positions An example would be

the method proposed for the Space Telescope Astrometric Multiplexing

Area Scanner (Wissinger and McCarthy 1976)

e) Use individual highly accurate single-star sensors like the Fine

Guiding Sensors to be used in Space Telescope astrometry (Wissinger

1976)

Other possibilities doubtless exist A study will be needed to determine

which approaches are most promising and development effort may be needed to

bring them to the stage needed for project initiation

The problems of imaging Pluto it may be noted are rather different than

those of star imagery For a fast flyby the very low light intensity at Pluto

plus the high angular rate make a smear a problem Different optical trains

may be needed for stellar parallax for which resolution must be emphasized

and for Pluto flyby for which image brightness will be critical Besides this

image motion compensation may be necessary at Pluto it may be possible to provide

this electronically with CCDs It is expected that these needs can be met by

the normal process of development between now and 1995

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ACKNOWLEDGEMENT

Participants in this study are listed in Appendix A contributors to

the science objectives and requirements in Appendix B Brooks Morris supplied

valuable comments on quality assurance and reliability

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REFERENCES

0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)

interplanetary emission observations submitted to Astrophysical Journal

J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217

R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194

G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA

H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR

R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28

R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085

R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632

J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86

R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190

J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42

J W Layland (1970) JPL Space Programs Summary 37-64 II 41

W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J

E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California

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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25

A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10

G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23

P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57

P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California

W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944

D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL

D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111

D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722

R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641

E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525

P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392

J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA

J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559

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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference

D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58

J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)

G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232

G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science

A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260

C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476

A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center

A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center

J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York

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APPENDIX A

STUDY PARTICIPANTS

Participants in this study and their technical areas were as follows

Systems

Paul Weissman

Harry N Norton

Space Sciences

Leonard D Jaffe (Study Leader)

Telecommunications

Richard Lipes

Control amp Energy Conversion

Jack W Stearns

Dennis Fitzgerald William C Estabrook

Applied Mechanics

Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage

Information Systems

Charles V Ivie

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APPENDIX B

SCIENCE CONTRIBUTORS

The following individuals contributed to the formulation of scientific

objectives requirements and instrument needs during the course of this

study

Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)

Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright

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APPENDIX C

THOUGHTS FOR A STAR MISSION STUDY

The primary problem in a mission to another star is still propulsion

obtaining enough velocity to bring the mission duration down enough to be

of much interest The heliocentric escape velocity of about 100 kms

believed feasible for a year 2000 launch as described in this study is

too low by two orders of magnitude

PROPULSION

A most interesting approach discussed recently in Papailou in James

et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system

The antimatter is solid (frozen antihydrogen) suspended electrostatically

or electromagnetically Antimatter is today produced in small quantities

in particle physics laboratories Chapline (1976) has suggested that much

larger quantities could be produced in fusion reactors utilizing heavy-ion

beams For spacecraft propulsion antimatter-matter reactions have the great

advantage over fission and fusion that no critical mass temperature or reacshy

tion containment time is required the propellants react spontaneously (They

are hypergolic) To store the antimatter (antihydrogen) it would be frozen

and suspended electrostatically or electromagnetically Attainable velocities

are estimated at least an order of magnitude greater than for fission NEP

Spencer and Jaffe (1962) showed that multistage fission or fusion systems

can theoretically attain a good fraction of the speed of light To do this

the products of the nuclear reaction should be used as the propellants and

the burnup fraction must be high The latter requirement may imply that

fuel reprocessing must be done aboard the vehicle

The mass of fusion propulsion systems according to James et al (1976)

is expected to be much greater than that of fission systems As this study

shows the spacecraft velocity attainable with fusion for moderate payloads

is likely to be only a little greater than for fission

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CRYOGENIC SPACECRAFT

P V Mason (private communication 1975) has discussed the advantages

for extraplanetary or interstellar flight of a cryogenic spacecraft The

following is extracted from his memorandum

If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions

1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years

2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation

3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)

4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below

I have been able to think of the following functions

I SENSING

A Magnetic Field

Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field

B High Energy Particles

Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies

C Microwave and Infrared Radiation

It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions

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II SPACECRAFT ANGULAR POSITION DETECTION

We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information

III DATA PROCESSING AND OTHER ELECTRONICS

Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way

IV DATA TRANSMISSION

Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode

V SPACECRAFT POINTING

We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields

It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years

Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion

VI POWER

We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power

First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules

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This will be enough for a lifetime of 60 years

If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD

LOCATING PLANETS ORBITING ANOTHER STAR

Probably the most important scientific objective for a mission to

another star here would be the discovery of planets orbiting it What

might we expect of a spacecraft under such circumstances

1) As soon as the vehicle is close enough to permit optical detection

techniques to function a search must begin for planets Remember

at this point we dont even know the orientation of the ecliptic planet

for the system in question The vehicle must search the region around

the primary for objects that

a) exhibit large motion terms with respect to the background stars and

b) have spectral properties that are characteristic of reflecting

bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be

visable in the field of view and that at most only about a dozen of

these can be reasonably expected to be planets the magnitude of

the problem becomes apparent

Some means of keeping track of all these candidate planets or some

technique for comprehensive spectral analysis is in order Probably a

combination of these methods will prove to be the most effective

Consider the following scenario When the vehicle is about 50 AU from

the star a region of space about 10 or 15 AU in radius is observed Here

the radius referred to is centered at the target star This corresponds

to a total field of interest that is about 10 to 15 degrees in solid angle

Each point of light (star maybe planet) must be investigated by spectroshy

graphic analysis and the positions of each candidate object recorded for future

use As the vehicle plunges deeper into the system parallax produced by its

81

77-70

own motion and motion of the planets in their orbits will change their

apparent position relative to the background stars By an iterative

process this technique should locate several of the planets in the system

Once their positions are known then the onboard computer must compute the

orbital parameters for the objects that have been located This will result

in among other things the identification of the ecliptic plane This plane

can now be searched for additional planets

Now that we know where all of the planets in the system may be found a

gross assumption we can settle down to a search for bodies that might harbor

life

If we know the total thermal output of the star and for Barnard we do we

can compute the range of distances where black body equilibrium temperature

ranges between 00 C and 1000C This is where the search for life begins

If one or more of our planets falls between these boundaries of fire and

ice we might expect the vehicle to compute a trajectory that would permit

either a flyby or even an orbital encounter with the planet Beyond obsershy

vation of the planet from this orbitanything that can be discussed from this

point on moves rapidly out of the range of science and into science fiction and

as such is outside the scope of this report

82

77-70

APPENDIX D

SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES

The listings which follow give distance (RAD) in astronomical

units and velocity (VEL) in kms for ballistic escape trajectories

with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy

bolic excess velocities (V) of 0 1 5 10 20 30 40 50

and 60 kms For each V output is given at 02 year intervals for

time (T) less than 10 years after perihelion and one year intervals

for time between 10 and 60 years after perihelion

For higher V and long times the distance (RAD) can be scaled as

proportional to V and the velocity VEL V

83

PRW nATr 03in77 nA1 I

V-TNFINITY 0 KMS

0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl

00

20 On0 60 80

100 12n 140 160 180 200

1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47

131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794

30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330

76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399

rnl0n

7Ap F14 39666 4306 9166 8Q

A7P3 7P94fl 7A45 Pq2A

ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1

innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o

u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17

P0nn pIfls P6410 3P1 A466

4u7jn -0P39) -70n 6PQ~P 6A7o 7414r

po7aI47 PA41I

95rQn05 45

P1476M 100149 1866 176115 167019 16m067 1544An

qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7

CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7

220 24o 260 280 300 320 34n 360 380 400 420

94100 q077q

115302 110684 115940 121081 126115 131052 135898 140660 145343

117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487

02186 07860 1337A 101757 114010 11014A 12417q 120114 33998

13S717 143308

1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234

n6p Q6n95

10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411

14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107

A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1

14496 iIOflnO 3n3 1314A7 12A971

saol ippes 190fllP 11743 1157AC5 137Al

7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371

12nfn Ip473A1196 iP311

14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191

117135

77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n

jCnpq3 I(9t tamn1n

j~fl0nm7f j8n~f) j3 0Ann

1S1 97750 11

I9r

0 O

O 4

440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900

149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232

106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223

Q1380 Q0968 9784

896P6 88203 A7583 8l6898 A6230 R5584

148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269

1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934

146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P

110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p

30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3

1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650

l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141

131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e

1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn

01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1

11gt01109

jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA

fao6 InI14 iAlnp2 onfol 08ij

0Cfl7 06fnq

074f

0U40 obtnA9 01A

920 940 960 980

1000

245822 249386 252925 256440 259931

84957 84347 83755 83179 82619

24385c2474lq 250957 254471 257962

A599 84692 84083 83500 82934

241021 249484 2490n2 252934 256024

Aq63080n1 84400 83A20 83247

217P34 40791 24U326 247A35 251320

81618 8583q P16

R4611 840P2

22ASA 23P064 23t570 P39fl7fl 24253A

88113 A7430 A6784 8614 830

po p71090A pj1qf 2IMP4 P20680

s0e oIn7 OInA5 Qf 4 A462

2 PRW nAT 0I3077 PArF

V-INFINITY 0 KMs

0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I

1000 1100

25Q931 277048

82619 AoOn26

25796P 275077

82q34 80312

256024 P73139

83P47 A0qq7

PS1120 p6A41P

84022 82303

24P51P pqq5j

R5930 AP67Q

Ppn6n p36031

m6fp At36

1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi

1300 1400 1500 1600 1700

30Q803 329544 340914 355946 370667

75677 7382572142 70602 69186

307820 3P3568 338937 353g68368680

79o20 74no0 72352 707qQA937j

305ARt 101619 316989 392 4 366733

76161 74P74 7261 70oq969556

1011pq 116893 33P2n9 3T7P22 36103Q

767I 74A31l 73Al 714A3 70019

pqP14 3fl7M 9 3P31PO 33pl93P77q

7701 79021t 74101 7P441 7ft018

P64A PR611 2qp6n0 31p327603

0ItQQ ftqA77fA4 75001 303

1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7

t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300

440370 453645

63475 62519

438388 45166

61618 62676

416425 411960Q

63761 62813

431 R 444R66

64116 631C3

4P01 41q94n

64818 A3n2r

3Onin 4nQ0l7

seoq 6CnAI

2400 2500

466730 479633

61696 60821

464747 477690

61797 60947

4APA1 479684s

62I1 An73

497n44 47n842

6PP49 6 I6

44A6n7 6124r6

AIQAO 6Pn09

-4p101i 41t690

91147 6900

2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0

517353 529622

58962 57880

51r36S 527637

98674 979A8

91314a qP9A6A

98787 98007

5OP947 92fl 11

99q67 83A7

4q0141 t133q

rqAp1 9ofl

47 3I 4A4046

oi 17 Anr43

0 3000 3100

541751 593746

97p2a96605

53Q766 551761

r7V3 96706

5377q6910790

9749 560nA0

S3Q36 r44Q7

7e6qr706t

SAs0 9394RI

sRagt17 S796P

4q6007 r n

qpr6 913

3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -

3300 3400

577357 588983

55435 548A8

579371 586996

55531 94q7

571 QQ 9n503

r5626 5n71

96A30 98019p

590A64 9532

q5qn6e 9r70674

r635 99790

r913nA 94R

p77 8 0 i1

3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700

611898 623196

53848 53398

60q9ll 6P1209

93Q36 93443

607q37 61q959

94023 392A

603061 614356

5424 r1740

5q3561 60484Q

94671 r4161

99s96 57676R

6n1 t44

3800 3400

634393 645491

528A5 r2428

630409 641504

9296A r2509

63 0431 641929

93052 92990

699590 636646

93p7 997Pj

616014 Ap 7 1pi

9ils66 5110o

9A7817 qA8Q9

q4fl97 944l0

4000 4100 4200

656496 667409 67A233

51987 51560 51147

694508 669421 676245

52066 91617 9122

652q3 66344q 674269

92144 91714 9IpW7

647648 698958 660381

9P141 91oo 914R4

618115 64OIA 6q39

52730 5ppA9 519i9

6009p 6pn661 631419

C fn3q ga6 9Im0q

4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500

6q9629 710204

50359 49982

697640 70A216

90430 90052

605661 706238

50902 90122

6Q0771 701345

906A1 nn7

6Pl0O 6q1776

9In35 5n644

69gt617 66X1P

iq C1794

4600 4700 4800

720702 731124 741472

49617 49262 48917

718713 72Q135 739483

49686 4932q 48983

7t6736 7P7157 737905

4q54 49396 49049

71I41 72P61 712607

4QQ5 4Q963 4021P

70P2e9 71P67q 723fll

9064 4qQ98 4qWi7

671697 6A000 694p

9 A C103 1 g09 9

4900 5000

751749 761956

48582 48255

749760 75P966

48646 4A318

7477R1 7q7087

48710 408381

748RP 7930N7

48871 48R548

733288 7434A8

40lg 48R91

7n494 71e60

n 04 4qnA6

5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500

802123 812007

47031 46744

800133 810017

4700 46802

798153 808037

47148 46P85

7q3P47 803130

47PO4 47n02

78162A 793906

4793 4706

7r463 76443

a014q O0176

560n 5700 5800 5900

821832 831599 841309 850963

46464 46190 45923 45662

8184P 820609 83q318 849972

46520 46246 pound5077 45715

817A62 SP7628 S37137 846092

46977 4601 46032 45760

qt1qS4 827tq 932427 A40080

46717 4643q 46167 49Q02

80133 813n6 P2P7q0 38143

46q6 4613 46437 461A7

774P9 7R39fnl 7q1640 80j32I4

U707(0 Tg72 7R2

O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671

3 PRW n rlp njiN77 rArr

V-INFINITY 10 KMS

q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl

00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp

1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711

140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n

AP273 SA357

14719IP IIt2074t

A037P A64Pq

1411919 1436P6

7A974 A0IlF17

19OAII 11 91 4A

74q6p P03n

Io ip 1A767

6A7ar 7 111411n

16Mqn3 I 47n r

7noP7 744i

1=Af7 I M400

P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117

340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7

480 500

159255 IL65684

In6023 1045Q2

157306 161734

1n6672 109pIr

lqtLnq 19QA34

in711f InrA 3

l nqn4 15r-1t

inAnop 1n7149R

14P960 171pi

11l[PWI 11010A

1PP17A 1 Oq ii74g

l

52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700

201234 20518l9

94429 9395

lcl027q 20122C)

qRA 7 n597n

19719f PnI Rn

q9 4P 0441

19P74q Iof660n

Q64Ai Q-n

IR 197 1sA26Q

ag ti Q79Q1

16q817 16o444

1mqn14 In9016

720 740

209107 21P989

026r5 911116

20714A 2110vt

OAnR7 Q2217

pn9pps 21101I05

q5qt7 Op655

pOntqo 204472

o477 00 647

10Pl47 lqqn O

06A10 00f7

17 )n 170261

a1 jnnll

76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00

220651 224434

902P7 A9473

211688 22P470

006gt7 A9862

P36763 Pp 541

q10Pk qOIP4Q

P10117 piqsot

QPnn3 Qtpnc

pnlrpn pn3po

Q1RQn oIn7

1P1741 11170A7

OR775 0pri

820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40

246508 250092

n5426 94820

244941 248125

Ft5764 P5191

24 P609 2961q1

A6100 85480

237q24 241tin3

86942 A6P94

2202PR 2IPA6

AFtr49 A774

P0p0nn 21i3on

GAOA 0911Mq

960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6

IATF 031077 PArr 4 PRW

V-INFINTTY = 10 KMS

0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt

a 1 AU a = 3 AU 0 = 5 AU a = 10 AU

T - YRS RAO VEL RAt VEL RA

R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q

pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5

A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7

00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135

1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97

1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0

1500 342229 72694 340251 72(91 338301 73107 33199q

1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44

3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4

1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47

_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo

2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401

2200 44P561 64102 44058 64242 47901 6439 411466 AU 3

2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377

2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43

2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153

Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461

2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43

545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A

3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19

9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp

57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32

3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$

3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr

3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ

627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7

641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544

64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178

66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1

rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673

4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0

4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR

4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR

4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46

768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95

787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462

79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q

8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044

80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo

46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016

467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383

PRW lAir 6114177 nAf~r O

V-TNFINITY 50 KMS

0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA

00 20 40

1000 1A394 CI814

132q90 101660 P49010

3000 165 28103

770661 328300 2561l

5n00 lA91 P607

q7789 33-8296 P62P

IOnnn l9A7 17 247 0

4P4176 NI047P PPas7

2n0n P1I0q7 26750

3nPnl9 PpAPp7 P6p05

gi nn svi014 r1fl1

101F4 iQnn6 1lo14

60

80 10r

3q465 48124 96110

P17847 108414 194706

376Ak 463nr 5427

PP2671 2n2nl2 I8t75q1

3618l 4467A 59q=

P2714P pp 547 10p53

31109 41919 40166

P35PSQ P1PAOP InA4 7

380 npao

43A p1A901 nno06

r 1 M sO6tP

0Th76m4q4jO i7 OnO

120 140

63624 70750

174317 166066

61761 68875

176711 1681n

Ann47 67112

17flnjQ 17onsA

5A431 6017R

j8IRttOMa3O 17469P 5P645

0 4 Ip0anp

6P614 lAgnftl 1A711

160 180

77567 84127

1592Q2 15351

7568p A234

161070 1q5163

73l7 A04P

16P7 P 1q6606

70n-6 76905

16681P Irn0p6

64AFv 7002

17274 16587A

6n4A 721 -

jA7TFL igiS06

200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq

220 240

96621 102607

144440 140683

p4716 1006q7

145714 14144

fP 0Pf70

165 142081

PA$n ot751

1j 0alP 14A6A

Q26a4 lPRS

54784 1jSfo

A11111 8g)

qAnac 191A77

260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07

500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340

125221 130602

129108 126R28

123297 128675

1p2q96p 1976P7

jP244q 1P6891

13nfnP 1P2414

117176 1PP2P1

l3Pp8P 1n12

1107n0 l15940n

136109 133o

7099 ItSIVl

n0nnQ 0q

360 380

135891 141096

I47P6 IP2780

133961 139164

1P5477 2P3480

13P101 137301

1P6217 1P417

Ip7770 113gt99

1Ann5 jPsA76

Ipnrr n

1P56uo 1391913 1P OP9

Ill~na ll1iq

16nR I kqiA

400 420

146222 151276

120)71 1102A4

1442A8 14034n

1P1641 11q19

14P4PP l747n

iP2nP 12P046

13A055 143085

I23oA2 1PP66

130656 1Ij606

1PAnn9 IP4Ao

1104A7 Ip7A6

Ij191 iOM9

440 460

156261 161183

117705 116223

1543P4 1244

1183nO 116740

15210n 157167

11Ao05 117365

14804 500

1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7

lpPOo t 1p A

jV7ofl7 A 3

480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4

540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580

184954 189562

009q68 108903

183000 187619

31043t in9148

181114 1S57P3

110PA 10Q797

1166i 1A121

11pnn 11n60

16871tn 171Pa

1 Unn 26

I on 26771

600 620

104125 108647

107318 106910

1q2178 19669q

1n8316 107332

1on8 q48n0

20S740 10774A0

A978P 1qp2

10n773 10738

1A8n 1RPP7

j117n7 11060n

613A8 16A O n

I no1 1nI46

640 660

203130 207574

10593 105107

201181 205624

I063qP 1n54q2

1q9p2p Pn03P4

106786 109P73

104761 IOnIQ7

In7740 6n

10671 191111

10cR6 101qq4

17n010 174208

11171 111060

680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800

233528 237747

100487 Q9814

231574 23579P

10j009 1001P

PPA65 P3388P

1011P 1004f30

ap59 PPQn6

01803 In11Ai

- 21683 2p1ol0

1n37 10PAn4

10944A 904949

InA l IAl7

820 840 860

24193A 24610 250240

09164 q8537 q7930

23998P 24414c 248283

q)465 q8029 qS15

211071 P42P33 2u6370

Q9763 40110 Q8t07

P3349q 237646 P4177

Inn0f0 QQ30 Q0189

PP917n pp43lp 2 334PP

101p87 10118 inO01

20A3nQ9 3nAI

giu2pq

iot14 1nuT4 1nIP

880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920

258442 262507

96774 96223

256484 26054)

Q7044 96487

PR4569 2R8631

0731p 9674S

40Q67 254026

o070AQ Q738q

P4156n 2456n0

oappO Q61n

Pp2058 2p=Q0 6

|nP4 l 749

940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000

270571 274570 278549

95171 Q4668 94179

268612 272610 276588

Q54PP 04913 04418

P66691 270691 P74660

q5670Q5155 Q4655

262n78 P66071 270045

96PR1 5791

02P38

2R3614 257601 P61557

C7445 06o0 96351t

231644 23747e 14P1P

A

1104R8 GA 6 00063

6 fArE 0V077 PAFPRW

V-INFINITY 50 KMS

0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI

1000 1100 1200 1300

278549 298149 317306 336074

Q4179 91929 89993 A8201

27658A 296187 315343 334104

q441A Q243 90147 n8377

274669 Pq4P63 913416 332l7q

q-46r Qp1 90338 A8551

p7O49 2nq6l 3nRAA9 127s08

Q9P3 Q677 90810 ARqO

p61S7 P81097 30f170 31AAP

Q6121 03n77 q171rAQon5

P41PQf P6nlFP 27oAAnq 29A931

Q63 o~q9 04161 OonA2

1400 1900 1600 1700 1800

354493 372600 390423 407989 425318

86632 A5216 83931 82797 81680

350527 370633 388459 406020 42334A

P67q9 A5965 84068 92A99 81799

3509Q9 368698 3A65l4 u04AR1 4P1408

86Q92 89512 84pO4 A3011 A1016

14q0ij 364n04 981815 399370 416689

R73-49 89874 8k491 n33P3 8207

33717A 35527r 373000 9n51q 407807

RAtfl9 8657P RqI6 83925 A27A9

314RPI 33P978 fn0o 36P71 9pen307

0nqp PAr 5 A3nq Pg 1 Ai1t$

190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4

2000 2100 2200 2300 2400

459341 476066 492616 50Q00 525242

79766 78911 78113 77368 76668

457370 474q094 490644 50703P 52326Q

79870 790fq 78206 77495 76791

4994p7 4P14q 488690 rn9086 9P1321

70974 7 noe 78248 77r4p 76833

45n64 467411 49I9K0 0 fl37

q16561

802pq 703147 70P9 77797 77n17

44175 498491 47497l 4qI335 S07947

8nP4 7q413 78065 7A173 7710

41v81t 434110 45n69 466865 4p8 f

IA7 01 rs ftnol 7oT75 Dqs

2500 2600

541337 557297

76010 75390

539363 555322

-16089 5465

917414 51373

76167 795c40

932697 4 6t

76361j 757P4

99361Q 530991

636 7608

4ofl857 914665

77804 nq

270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5

0

2800 2900 3000 3100 3200

588844 604444 619936 635326 650618

74250 73725 732P6 72751 72298

586868 60046A 61796Q 633350 64864P

74319 737q0 73p88 7211 72196

9A4ql 6n017 616n0 631397 64668

743A6 7385 73ilg 7P87 724t3

9A0149 iqi744 61P133 62661q6410n7

74954 74019 7353 73017 75r4

571064 986647 6nt1 p 6174q661077N

74879 74376 7Afnl 73903 7PAPA

54 tq97 96141 R7677 599066 6oP4

7Cn58 1 71A73 74t4 I9S93

3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC

699954 710898 729765

71059q 70681 70319

691977 708g21 723787

71110 7070 7066

6Qr)02 7f606-721 A1

71161 7f)770 70411

687233 70174 717n03

71296 7nqn9 70530

67R06A 6Qinni 70795v

7Ist 71139 707 7

69p30n 66716A 6g199

7V04q 71a9 q

7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71

c c V

4000 4100 4200

769927 784512 7Q9032

69314 69004 68706

767944 7A2533 7Q7053

6q397 69046 69746

76509P 7Pn76 79S9nqs

690Aq 6Qn87 6876

76110 779774 7qflP

6Qr5 6q189 688811

751986 766560 7A1072

6qfl 6937 66477

7pr5o3 7Tn410 754A66

70t5 AQ04 6nr 9

0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008

bull

4400 4500

4600

827890 842232 856518

68I40 67872 67613

829911 84025P 894538

6817A 67909 67648

823Q09 838P94 R257q

68215 67049 67683

81q146833486 847770

6R3fl8 6A0vS 67771

gn09tp 824245 83A5p4

6A480 61gtn 67Q04

7A3603 7976m7 81P211

g93 AA9 6tjU

0 4700 4800 490O

870750 884931 899061

6736a 67119 66884

86R77 882951 897081

C67306 67153 66016

86611 RRfQqP s99121

67431 67186 66q49

6ao0 R76179 R9008

(7515 67p68 6702o

9A971 a6q5p 881045

67681 674P9 6718A

RPApaq R4nP 854q0

6oil7 Af 6764q

5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400

941166 995110 969010

66221 66012 65810

939189 95312q 967030

66251 66042 65899

9372 Q91168 069069

66780 66n72 69S67

q3P407 Q46190 q6024q

6614 66143 65-07

9231p4 Q37n6 Q506

66tq4R 66983 66074

946 fllAI7 9P417

es6 6670 6A491

5900 5600

982860 996687

65614 65423

980880 9Q4707

65642 65490

978q27 qQ749

65669 65477

974107 qR7923

67I8 A943

0648t5 q7A6p7

65871 65671

q3n055 Q1R35

AA$f FlVdegn6l

5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq

7 PRW nATP 033077 PArr

V-INFINITY = 100 KMS

0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY

00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4

20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941

40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070

60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R

209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1

OATw 01307 OArr aPRW

V-INFINITY = 100 KMS

Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU

T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI

1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000

328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311

124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315

32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368

1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361

3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P

1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409

lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6

104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911

31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7

lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06

QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56

6

4601

1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9

2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909

2200 2300 2400 2500 2600

626307 650151 673901 6q7565 72114

113PS2 112B3 11fV96 111998 111626

624364 64R0 671957 695621 719201

113Nt 1128q 11 0 11030 111696

6P2475 64631 670067 69379 717111

111ra 1Pp2q8 110463 1161 11o168

617qAO 64181A 669=6 680 p2

71PI1

1l14 1jdegPQ0 1142P 1115

11179

6fo0Q71 63A6F04 6742p 6fl6A

70463

1110 l1I6 1lpisq 11097

1ilnq4

Ron2 4109R7

61971 611

6deg4 74

1 10043 1lArN4 1o6l 11

111i

2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100

760ql 791461 814767 838014

110950 110642 110352 110078

766146 78Q519l 810821 83606A

1i0O77 110667 110376 110101

764P9P 7R7A2 81nq6 A14171

11103 11n69P 1l09q 110121

7qq7l6 783101 A06404 AP0648

111065 l1791 i14r5 110179

791941 774898 7a1qn 8214pt

11117) iifnn9 j nls 1127

71l n3 745-7 77 717fl ef0 9 9

11413 11116

lfnfl 1099 I

3200 3300 3400

861205 884343 907430

109819 109573 109340

85925A 880396 905483

In9840 ij9593 10939Q

A97163 S8Oro0 p03987

10n961 I19613 Io979

R5PA6 879q71 pqon9R

in9o11 in9661 tq43

A4460 p677PO 890l0q

1ifln3 I0q4q

io9ro7

npnAo 8471A A7MIOM

l1nl9I O0959 00703

3500 3600

930470 953464

I09118 108908

92P523 951516

1n9137 108Q09

q96p6 Q49619

10q199 10804P

qpPfQ2 045084

nQIA lnRQA

q1389 9361

1nQP77 I09nq

8q3lp2 qlO1r

fnnflA3 n06

3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n

3800 3900

99324 1022194

108515 108332

997376 1020246

108r91 108347

4q9479 1018148

108 46 10816P

q0nq9q 1013R07

1085 4 inslOR

9661 loo99p2

Ri IA464

q6702 9860n7

foqh 4 nQA67

C

lab

C 4000 4100 4200

1045027 1067823 I0Q0584

108156 107Q89 107899

1043078 1065874 1089636

In8171 10W3 107A4

1041179 106l975 10R67A6

108185 I18n17 I17P-S

1036637 109Q43P 108Pi91

InPPf2 InR050 nI7F7

I0lA346 105135 101NR88

l0o894 108111 in7n4

10071n7 Ifl0u40 l1j nI1

0o2847 jOR08

o 4300 4400

1113313 1136009

107674 107526

1111364 1134060

107687 1o753a

1109464 11N216n

107700 107q91

1104qt1 1127613

1f7713 in717Rn

noe61n 113nn

ln77PS I07634

1079910 1nqA1AP

jO7n04

In7776

4500 4600 470o

1158676 115131 1203921

107384 10747 107116

1156726 1179361 1201971

107396 107259 1071P7

1194R26 1177463 lP00071

1n740o in770 I07138

11i0277 117q13 119920

lfl746 1np97 107164

1141990 1164900 118710

In7ua8 lo74A I 07 9

11nn 1144n 1169Q7P

in7t4 l7479 i0711Q

4800 4q00 5000

1226502 1249057 171587

106989 106867 106749

1224551 1247108 1269637

107000 106877 1067Q

1P2652 1249P06 3267736

107010 106P87 106760

I1flAnq IP40693 1P63182

i 7039 I6912 067Q2

1po076A P1i3317 lpSt449

1070 1A1M 106097 1pIl0A

In696 193deg31

1n7n9 l0n 5 In6oO

5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin

5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400

1339034 1361471

106419 106316

1337084 135P521

1064P8 ln635

113518P 1557619

In6437 106334

1330624 111060

In6458 i061q

I32PP7 1344706

0640A 1o613o

1300RPI 133P29

106f n6103

5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7

5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00

1451014 1473351

105q38 105e09

1449061 1471400

if9945 1o585

1447160 14694q97

1nR3S 109A6S

14429~9 1464q9

io9071 jO98A3

1434P3 14669

i06n05 l09016

1l11gt 1413 04

I60n4 jOnp

6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739

PRW DAP 0130l77 nArr q

V-INFINITY = 200 KMs

0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri

00 20 40 60

1000 1 005 33546 4575q

1146943 159357 304778 PA0667

30(0 18471 31945 44004

70461q 368R97 3n0006 203263

Onn 17ROA 9fl7P 4273Q

6P8A7P 17q61 11265P PSSns

t0nno 17614 p0177 40nq7p

hA6pe

17g06 P2O363

20Nnn PTq10 3ItR 4lr0

AA7AA 1340n3(40200 11177 P9A3A

cpnnn ) l9A7 o00o9

p0in p11n4 pAIn pA177

0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140

68217 78875 89283

P96922 249n89 944688

66499 77137 87534

p28230 25180W 2454CA

651i24 75636 6O0q

pqq06 P5I00Q 246P2Q

603rno 7p774j 830q

261A77 p5171 P477p9

60211 701 7Qqpl

P63t540 6

24966

7l 7n qu AA7r

pt r104 pbni4 915n06

160 180 200 P20 240

Qa497 jo0q554 119481 12929Q 13q023

p404A3 797495 214200 231780 pP97o0

97730 107780 117710 127921 137241

P4114q 217614 P14677 pl21Q2 210061

Q6196 106931 115141 IP5044 139696

4175P Pl81P1 710110 p22968 p301n

q3143 10311p 110067 IP7P tIPfoo

943nn PiOjRn P npl 133361 PI1Of6l

AQ763 0047A

jnlp ]P 7np pA2 c

24U471 P4001

214fl7 p3P2P6

011665 I98PI ll A IA F

lp2pn

pl2AA olfA1 236C61 P14t1 2nA4

260 280 300 320

148667 1524n 167751 177207

pP7R01 226302 224s03 P23634

146883 19645 16596P 179419

2282n9 P6qA4 2P5146 PP363

145PA l4A3 164156 173P04

P8Qo 2P6A04 PPgT37f P24072

I4Inno 19 913 t6In13 17043o

990117 pp7Aq vp9PS7710 P245pp

13771n 1471A 15 o 168s6n

ppnA9 PP0164 96574

16AAU 14A5l tRpol t516116ngp

pIM143 990ftg 29OAm p9Mo5

340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380

jQ5973 205293

221480 2205I

194177 2004q90

221669 PPnTP7

lqpqrA P20IP73

22843 pp02

100155 IOS4 4

22216 nplpn

1043 103670

pP22275 pp172p

t1A069A 1n01n

ppAIf7 ao

400 420

214576 223825

P19701 pt9

21P776 222024

P19A6n 210q06Q

211151 Pn30q

PPO06 pIfl 04

20771A P96ouo

pp0lp2 Ptj4or

PnAl p12062

PP117A3 pl P4

10011 20110

291939 pPni

44o 46o 480

233043 242231 251393

218205 p17542 216928

23124n 240427 249580

P18341 217660 2170145

2PA00 39704 2705

28O66 t17714

P17191

22615n P3r34 24471

1 61 P90036 2i719R

P21A 2303q0 p39450

10136 PtAttn0 P17717

1gt1goo 2pAt P6

loc7p 010-t p10PAJ

900 520 540 560 580 600 620 640

260531 269645 278737 287810 296863 305899 314918 323921

p16357 715824 219326 214860 214422 214o10 213621 213254

258729 26783A 276q2O

286001 299054 30408A 313107 322100

216466 219Q27 215423 P14050 21407 214090 213697 213327

P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460

216q67 216021 p2511 215034 P14q86 21416S 213768 213191

Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn

2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530

24854A p5761 26666 A

p7q9 nl pR471A p0371 38270A 1167p

217114 216R34 P25004 P150p9 219njS P14971 210i t

p1317qq

94q9l l519i4 260101 P6onq 27Rn6 P9A60

s55 loP

213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn

660 680 700 720 740

33290Q 341883 350844 359791 368727

212907 P12579 212267 211970 2116A8

3310q7 340070 349030 357977 36691p

212q76 212644 22232q 212029 211744

529146 31R1A 147177 356p3 369057

213n30 212704 71018 212n8 211706

3P qOn 314f67 34AP1

2P76P 361602

P11176 P1PA0 P12ifl P12202 211000

3P2n63A 30OAtf 93Rqp 347441 196156

213386 PI314 P127o0 IPII

PIP2n6

31X1I7 p10 lp7qp 33S 3434A

PI06 p43n3 p1ogtnpq p19f62 p1pqp

760 780 800 A20 840

377651 386564 395467 404359 413242

pl1419 P11163 210ooa 210684 P10460

375836 384748 391691 402543 411425

211473 211P14 210Q67 210731 210505

374i0 3P9fl2o 3QIq3 10nAA4 4n4766

P11922 211261 211p 210774 PI0947

1706j1 370918 1P841R 30733 406181

P11610 2111AS p1111t p1)RA6q P10637

365p2q 37411S 383033 3010 ufln771

211706 21123 211963 211 21077

js713o 36 Q0A 37U7fl8 3p340A 3QP2

9n57 V1175 2i11)7 211R0 21100

860 880 900 920 940

422116 430981 439837 448685 457526

P10246 210040 OQS43 209653 PO9471

420pq8 420163 43801q 446867 455707

210p89 21OO8 209882 2096q] 209508

41q630 427502 436358 44N05 454044

210120 P10120 p29Olq

lPAQ727 pl-q4p

41sflO 4P300 412763 441607 45fl444

21n416 p1023

1no 2flQ804 p0616

4nq6pn 419476 427316 41615n 444Q~7

pl0ql 21033 PIfllP4 POQQP4 P0QVP

40102PA 4n07o0 41A5 p7 f3o

4360A1

2101 p1n056 p90i3 p101p2

lan096 960

1000

466359 490475185 484003

209295 209126 208964

464540 473365 482184

20331 209161 208997

462876 471701 480519

2fql64 89tp 209027

45P73 4A80o5 476910

pM0439 P0o262 P8904

453704 462607 47141p

pOq47 200169 Pfl9j98

441t9i1 4S3T54 46204

pR3 pfalP 2f075

0A1 011077 PA9W InPnW

= 200 KMSV-NFNTY

T - YRS Q =

RAD 1 AU

VEL G = RAD

3AU VEL

RAn

5AU VEL

0 = 10 AU RA VEL

0 = 20 AU PAD VEL PAn

52 AU VrL

0

1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400

484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603

1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863

208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367

4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031

2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360

460911 5P4513 r6366 lnqR

69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79

130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344

PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172

47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634

poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276

471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q

1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761

PnqlqA 6ppa

P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)

6338 Ant 4P7 p09074 819610

po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p

pn3190n 116k066c nl05 Q14i0A

4Q

pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6

202P25 166136 202q60 171nO6 P02409 1527R

Po2P4 17oF4P0 pflpA4 1I3An0

IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7

6t6 pnq6 P4 o pft At0 pf 4tL 4

pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A

n10

-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ

4300 4400 4500 460n 4700 4800 4900

1905546 194821g 1990881 2033533 2076179 2118809 2161434

202314 202264 202216 P02169 202125 202083 02042

1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601

202317 20PP66 202218 202271 2n2197 202084 P02n43

1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13

2021q p0P6p p02220 P00171 20212n 202(86 20Pn4

18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q

P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4

89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307

pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4

1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596

p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6

0 5000 5100 5200 5300 54O0 5500 5600 5700

2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152

pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765

220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319

202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766

2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630

2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767

2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t

Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770

plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq

2001n4 201076 P0lo3q pqjo4 nl 7fl

p0tA37 pninqo pnt74

17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P

PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3

5800 5900

2544711 2587264

201736 701707

P942878 2585431

201717 201708

941189 2981742

20173A 2nt70Q

2537469 2580022

pn1740 01712

23156P 2974111

pn745 P01716

PSin6fA PS6pna

pm17r3 Pnj9 4

6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6

fATP Olin0 nAr 11PRW

V-NFINITY = 300 KMS

4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)

00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7

20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA

40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13

60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104

80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02

16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260

177226 190541

516P46 1335138

179601 188QtA

31632 1192A9

1714P94 1A76

316 lq 3153I72

171714 R150

3167M qt~7A

1689 317n2 IP23j(6F 319~1fI

17n 310n1I 3 isrl9A111

280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0

32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq

360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l

480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1

500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034

540 560

374010 386900

1078n5 307546

37236 38534P

37835 307578

37n075 383q93

3n7A6p 10760

36AP74 381246

flx7oo 307659

361$A84 377777

3f70o0

077p8 161400 17a0qn

IVAnM7 307 o

580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71

680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740

400500 50340

905069 105818

488848 501751

0lqRg 3n5837

4A7451 5003n

A6n6 3n5891

4A4713 4q7613

3n6040 inq5A5

4R11P8 40401r

IOnOS Anop7

147r887 4A068n

In1IR jm n00

760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840

554066 567843

3n528 305163

553313 56619n

3n5pq8 305178

991013 5A478

3n9311 3M91C01

r4016n 56p033

3nq337 n5916

9452P1 998388

09373 3050s

940017 917

30SulR 3f 04

860 880

580715 5q3583

305050 304q41

570061 591q28

305064 304Q95

577660 ffl26

30507A 314066

974qnp 987766

Tnq1nn if490f

970P47 P41n

30i33 3f90nl

69P6 570132

3 n9q5 30nAp

Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980

632159 649009 657856

3n4642 304550 304462

630504 643394 656200

304654 304562 304471

62OIOO 641q50 654796

304664 304972 304483

6P6334 63Q1P 602026

n046R5 104liql ft4501

622640 634n 648 3PA

3047 304818 304-27

6117P4 63091Q 6411I

n41q 3n4054 1Ane6p

1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474

nATF 011077 PArr 12PRW

V-INFINITY = 300 KMS

0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU

T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl

1000 110n 120n

670699 7341165 79997

904377

3039q7 303619

6690q3 73320A 797300

304398 30406 I03696

66763 731101 7c589A2

3fl419q7 I04014 I03649

664867 7Q0pp 7Q1fl

Ift44195 A46q fl1fl

661162 79PRQ 78cflSn

104140 mn4nnn Inpl

6RA1nfA 2nou 783941-

Af474 rftn~q

I140

1300 1400 1500 1600 1700

86298R 926965 990897 1054788 1lL864

303407 103173 902970 302791 30263

86132c 925306 989237

1053128 1116984

303414 3n317q 302Q79 3027q5 302636

P5Q0O Q1896 q7826 101716 1119971

103410 303184 I027Q A027qQ 30269q

857Pq q100 qqRnP6 104913 1112764

3ll4fll AnI10 3 9NqR7 nfnn6 30n646

89 X ql79l7 QoII 104900Q 1j00939

0144q 3onN7 Iflpoo 30Pq16 3065

847l 0116r6 q7-4A7 1030259 110o16

304A6 IftN5 1016 90p29 Inq

1800 1q00

11R2468 1246264

3024q0302363

118080 1244604

3O244 3n2367

117qq4 1243t10

30P4o7 30p6Q

1176585 120377

30P03 inPI75

1170741 12369PA

30211 3npipp

1l6A 7 13nQ

I n9Ifl9

2000 2100

1310035 1373783

30224q 302145

1308374 137212P

3n225 302147

1306q5 1370706

np254 902150

1304145 1167AQ0

30n22pq I0 54

13flflR 1164n5

n2566 in2160

1904191 13570

3096 3091l

2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07

2300 2400

1501218 1564908

90Iq63 n1884

149q556 1563246

31066 3NA8n6

1499t40 156lnpq

301o67 3n1887

14Q5320 15a0A

301071 inIACl

14Q1410 isSlPl

101n76 AnIn06

14F10A 14A4P

nlnA4 inn10n

Un

25-00 2600 2700 200 2900 3000 t00

162A589 1692241 1759887 181 Q519 183140 1946750 P010349

101811f 30174 I0167) 301621 301566 301515 301467

162600 16n057q 1754224 1817857 1881477 194q087 200A0A6

I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67

I0I124 I0174A In1682 0624 ois6q 30191A An1470

16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437

In1817 In1748 ln1695 in1626 Nolq7 in0If In147

i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl

I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np

301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7

n1475 Ia10i

Ift~ 0S 0 nt0

3n 65 301635 301~0 30nhI A 0it 17q

3200 3300

p073939 P137518

n01422 3013n0

2072279 2135855

n1424 3n1381

2070n57 P13437

In145 0j8

P06806 21316A5

in147 n0 13 4

20641n6 912765

01p 9nliP7

2n76n P12lA0

I 1fh414 9nI1 0

3400 3500

2201090 2264654

301340 A01303

2190427 2262990

I01341 301304

PlqRfl0R P261571

3014P If013l

2195175 2298738

in1944 301306

21012c5 2254810

n1146 30tinq

PlaA709 P421

3fl13 90

3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6

3700 3800 3900

2391758 2455300 2518835

301234 3n1202 3n1172

23q00q4 2453636 2517171

301235 301P03 301172

P198675 4P216 P915751

in1p2q 101203 I01173

28840 P44qI31 2512n15

301297 i01905 901174

P381008 P44S446 P08q7A

90l39 nln7 3n1176

P375315 P3D030 P2O5q6

Inlo4p nn sl0 301t q

4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110

4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153

4200 4300 4400

270q404 2772916 283642

301089 301065 301041

2707740 27712)2 2834758

301fl0 3n1069 301041

27n692n 76q9j1 283333R

901OQI I01066 10104P

P70342 2769Q03 PA304qq

Inl0QP In1067 3n1043

PAQQF30 91690n4 P2A655

l01no3 untceR I01044

26Q9877 975 g975 Pl0A06

1o06 In107i 9nl047

4500 4600

289c924 296342

301018 3009q6

2898260 2961757

301flQ 30oqo7

28q6840 P6ni37

i0jO11 9n30097

Po40o01 P57407

i01000 InOqR

PA80059 9O5394A

30i021 nolno

gAn33R7 PQ46819l

3ntnI4 Nnlfnp

4700 4800 4900 5000 5100

3026914 3090403 3153887 3217367 3280844

300975 300q55 300q36 300918 300900

3025290 308873A 315P223 3219703 327Q179

300q76 300956 300937 300q18 3n0on

IOA829 3087328 3150o0P 32142P 327798

900076 30056 ln037 30Ooq In0c0I

3gp qAa 3084477 147961 3P11441 3974Q17

nOa7 innq07 00q9 900lq i00nP

3017n3n 908ln5p5 1junon 3p074AA 9P7n96n

90079l 9nno5 3n0a9

300lot 3n90n9

3010n12P 9nT7Q

9137p79 99fl740 99609n

9fnnnl Rnn6 98nn t 380QP9 3fntn

5200 5300

3344317 3407786

300183 300866

3342652 3406121

InO83 300867

3341231 9404700

300084 100867

3930Aq 3401~qR

f00nA4 300A86

134439 I9Q7qQ

30flAS 9mA6q

9927671 A991131

nnn7 90n71

5400 5500

3471252 3534714

00851 300815

346q07 3533090

300i51 300636

3460166 I91162q

900851 300A36

946324 3528716

m00852 14613611 90037 91P4PR

i00n 3 nnAA

3q4490q 351A0ll9

0nnqRS Ifnel q

5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095

5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo

5800 5900

3725084 37A8534

300793 30070

3723419 3786970

3n0793 300790

372lqq 37P5448

300719 90070

371I914 318P604

3fl0704 f7pi

9715190 9flm7ns

l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi

6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l

PRW MATP 1111171 OA r 13

V-INFINITY 400 KMS

0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai

T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl

00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl

20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp

60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA

80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490

100 120

98201 119922

421981 418695

q6793 114504

4P22Q2 418021

9579A 11440

4PPq6 41nnQ

0416Q iii71

UPPP06 uj0173

a347 jt1171n

p1n6q 1Q1

toP4A IInn

41111 41ntoIA

140 160 180

133527 151049 168493

416278 414423 412093

13P101 14061P 167056

41641 4j4qqQ 413063

1103 148931 169065

841691P 414663 413147

120on0 146741 1641AI

II6A0 1aAQ

4101

ipPOtA 14920 I e540

416065 414nA4 1411

134 14Af 166nl1

16o7 4 g=4 41ftlt

200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n

203234 22nr44

410768 409933

201790 21QOQ7

4l0O04 4n9QQA

2nnA6 p1TnRq

u(100 41O04A

108A80 PIAA

411nnq i1 I115

1 7nn P142P2

u1tin3 1100p3

lonlI vj70a

u1oonA 1011 o

260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06

280 300

255072 272298

408602 408064

253620 27085

408651 4881n6

PqP904 260729

4n8AAA 408l4n

29nq64 P6777p

0A7 uoglnP

P4Pr7 p6131

40nqpq 40OA1

4M P601114

a0shyunfi

32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP

340 360

30668A 323898

407167 406740

309230 3P40n

4n72n1 406R 1

3n4105 3PIP7

4f7P25 406n4q

10PI12 31QPAR

4077 4n6Ap7

30ngn 317139

4n7115 i6nv3

ponA 3167ql

40t00

Mrt601

380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -

480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520

443692 460774

404q68 404789

44223n 450310

404q84 44800

4deg102 4rA171

4049q7 Uf4A1P

43qn6l 456136

ao5np0 4483

436741 498flIn

4sSrn46 In4095

413F2 45I11

4nflA=n bIeAI oW

540 560

477847 494914

(04619 404496

476383 493450

4O46PQ 4n4470

475944 unplOq

404640 4041180

473pn4 400266

(04660 Uo44 A

470093 4870n1

naAAN 1n49p0

4601PO 4pAnn

40o00 404917

580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8

60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720

57194 614223 631240

403697 403505 403498

505727 612756 620781

403706 403605 4n19n6

9949AP 611611 rPOA5

403711 40361n 4ntq11

9qp9tp 604146 62656A

aon376 416P2 u1094

rnnfn 6071oq 61iA

4n141 403637 4n01q

R09t An4757 Ap111

4 0199 4nitn1

MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98

760 780 800

665288 682302 609312

403320 403237 403159

661810 60833 697844

403327 403p44 403166

66267P 679686 6Q6606

413133 4n3290 4n1171

6n601 677612 6q4620

1n1141 403260 4nl3180

6 5n10 67514n 692141

40l396 ii07P 4ni10o

65qA2n A7974 61095q

tjOk3q 4A3o84 gnRAL4

820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7

840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4

860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb

880 900

767324 784320

4n2880 402818

765859 782890

402885 4n2823

764705 781700

4OPpgo 402127

76P63 770617

40AC8 402839

760110 7771nP

uOPon7 unPnU4

75136 774P87

4AfIfl 40094

920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73

940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73

PRA WA1033077 PAGr 14

V-INFINTTY = 400 KMS

0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI

1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3

1100 1200 1300 1400 1500 1600 1700 1800

954159 103003 1123814 1208593 t293346 1378075 1462784 1547474

402318 402129 401969 401831 401711 401606 401513 401431

95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000

402321 402132 40171 40133 4n1713 4A160R 401515 401432

q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P

402924 402134 40Q173 4013q 40171= 40160Q 401916 401433

94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724

40P29 40219q 4l077 41100 U01717 401612 4n118 401435

q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q

40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417

Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q

411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441

1900 2000 2100

1632147 1716806 I001451

401357 401290 401229

1630671 1715331 1799976

4013ql 4012 1 401210

162 154 1714173 17q817

401159 40pq 40131

1627309 171pnsp 1796695

401360 002 q2 4n I1PP

1624758 1709nAn0 70447

401163 40125 40t14

l6pin0g 7056n 17Q0p7

40166 4f1 oR 4n1117

2200 2300 2400

1886084 1070706 2055318

401174 401124 401078

188460q 1960231 053843

4n1175 4n1125 4f107

1AP1490 IsRn7i P90683

401 76 40112s 40070

18813P6 2q9q47 P050557

4n1177 unI1P7 4fn0l0

1877 IQAIPR9 PA478q6

4n1179 fl1jq

4flnRP

287UR66 lq4Ki P04ilnl0

4n1101 4f110 40InA4

2500 2600 2700

213q920 2224514 230Q100

4n1035 4n0906 400959

2138449 2223039 2307624

401036 40Oqq6 400960

P1370P5 PPP170 P236464

401036 400q7 400Q60

2119158 Ptq790 P304335

Un01037 40nqnn uo0Q61

Pj3P43 Ppl7 04 P01664

4flInO 4009o 4006l9

PlpM60 P-19A4 Po758

4AonUT inlnnl 4nn004

2800 2900

2393678 247A250

40M025 400894

23q2201 2476774

4000q6 4008Q4

239104 P479613

400926 408O9S

2388q91 247 4 3

4nlOQ7 4008q6

P386P9 470n06

4n0oa 40oqQ7

2IR9PRO P466 1

4nlnn 4000o0

3000 3100 3200 3300 3400 3500 3600

P562815 2647374 2731928 2816476 P9o3Og 985558 3070092

400864 400837 400811 400787 400764 400742 400722

256133q 2645898 273049P 2815000 2890543 298408P 3068616

400865 400817 400P11 400797 4007A4 400743 4n07

2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454

40O6q 40083P 40081P 40087 4n0764 400743 400722

255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq

400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI

255361 400867 P9116 963Qql 4o0nQq P63c0IQ

747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri

4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74

3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900

3239148 1323670

400684 400667

3237671 332q14

400614 400667

3P3650Q 1031

40068r 400667

3p34 74 3318806

400689 40n668

IP31670 316109

4006P6 4n0668

250f 3311000

4ftn87 4nnA

44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg

M 4100 420n 4300

31492704 5577216 3661725

400634 400620 400605

34q1227 357573n 366024A

400635 4006P0 400609

3490065 3974577 365Q86

40063q 400620 400606

3487928 397p440 3656948

n0695 4n06P0 4006n6

14R92p0 56q79n 9654P46

4n0696 348l1(I 40n062196A9609 4nn606 169noi

4nnA7 4ftnA9 4nnn7

4400 45O0 4600

3746231 3830734 3915234

4005q2 400579 400566

3744754 382q257 3913758

40059q 400570 400566

374391 3828094 3o1P799

4005Q9 4ffl70 400966

3741454 3AP597 391047

unnr59p 4fln07Q anO767

171R751 382292 l97751

Un0503 4n0580 4Anse6

3714907 9N0On 03lap

4nng l 4nnFno 400W68

Pgt 4700 4800 4900

39qq732 4084228 4168721

400554 400543 400532

39q8256 4082751 4167244

400554 400S43 440512

300Q793 4081588 4166081

400n54 400O43 40053P

39Q40r5 407q44q 41634P

400999 400543 Lonl52

IQQPP4 407674P 4161214

4059 400q44 4nnl0l

93AA0 9 4q7Pq5q 41544

4ftflR6 4nn44 4fnq3

5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300

4422187 4506671

400501 400492

4420710 4505194

400501 4n049P

041q947 4504031

400502 40n4gP

4417U07 45011

40fn2 ao0402

4414606 44q017Q

40050 40qhiQ3

44jA40Q 449406A

4f0t09 40fi93

5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4

5500 5600

4675635 4760114

400474 400466

4674158 4758636

4n0474 400466

467pqq4 47q7471

400474 400466

4670854 479911

400479 40n466

466814n 4756 8

4n0479 40466

466917 474890

4nnilS 4nA7

5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ

5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416

PRW 0ATF 011077 pAr 15

V-NFINITY 500 KMS

T - YRS 0

RAO 1 AU

VEL 0 =

PAD 3 AU

VEL 0 =

PAn 5 All

VFI A PAn

1n AUl VEL

0 = pAf

20 All VEt RAO

02 AU Vrl

00

20 1000

27095 14P2764 961678

o300n 2604A

qo7po RAU417

non P V5R

77772P t65173

1n000 pqn5R

i177A 964461

nn0nn i0poi

rn0n Ssqno4

r9nnn A-

qo n0o on 16

40

60

an 100

S0041 72315 94283 116073

34281 235Q61 1518477 15059

411870 71111 0cs0A0 114816

9An6q 5P43S7 918716 51510

4A176 7n133 9P941

11100

939q64 5P46Pn r1AP70 S 93

47q77 6n408k 01147 11706

FJQ0a6 qp44 -9tclfl1 1Of

4q314 70014 0114Sp 1jP4PP

9477n 9P471n 51010 5155R41

67An R94117

ln1o9m9 lpnPnq

90rlt 9~tfnA 9 rl4ft

120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06

160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260

20P344 223786 2451C7 266581 287943

5fl8603 507866 1)07194 90661P 506124

2010AI 22252 24303n 26531P 286671

9118747 9n7011 qf7221 5n6643 5n61r1

PnOIQ6 pp1A20 P43o3 264411 PQc76A

g7F8 5n704p q07P48 g06666 5n6171

tg8ln PPAPIQ v141603 P6P0AU PA41fl7

nR8S n70fj 9n7p0 1 PrmAn 506209

1Q775f P10071 p4n3Ao Pfl21684 8p2q7A

q0A8AO r0ArnA4 tn7i7 cn6i1 56931

Pni11 VP17n 4PUI P614P9 IRJAfn

q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl

280 300 320 340 360 380

300287 3301614 351926 373226 394514 4157)3

$i057q4 5n5338 505016 504731 504477 qn4249

508019 329340 350651 371950 39323 41at5l

5fl57P7 qn5359 n5s35

904748 5n44q2 5n4p62

1fl7ff7 1Rln tq770 371036 Aop39 41r5qA

RO9744 5fl57i 0R048 904790 n4511P qnq4pp

In9614 326047 34AP47 360519 3n0814 41pnS4

mn577P t505AQ8 05n6q rn477A Ao419q s(42A7

30429An 3p5SVA 34670n 36A058 38031in 410556

905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3

3n=119 lpAlft9 147171 301A49 30401 41n n

9M91V7 nnn nl=qn2

qnn3 90495 At4inA

40f) 420

437062 498323

504045 53856

435784 457044

5n4095 c03867

434A69 496124

9n464 5fl3t7

43034 440qq

gn4f7R eo3P8A

41706 41 in11

904 50nn0l

4Alf16F 4RP79A

Ffftlf4 fvnw4

440 460 480 500 520

479577 500824 522064 54399 564528

9036A6 q03530 503387 50525 903113

478297 4Q9941 50783 54P018 563p47

-503606 n339 qn33q5 0n3263 9n31n

477376 4qA621 939n6n 45In4 693pp

qn3703 rn3546 rnf 1 0 ofl36A r0314c5

47R4A 4070A6 518P2 5301 r6f776

tn715 Cfl3 7 rn11t 1 n3lp7l

C014

474P6n 40949c 167nq 931

q5al3

gn17p7 5fn36A

n398 Rn316o

47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA

940 560 580 600

585753 606973 62188 640400

rn3Oo i02q15 902816 5027P5

584471 609690 626009 648117

5n3097 902)21 502Ap2 5n2730

r8lq45 604764 62078 6471A9

00ft3 50202q 5n21P6 clP734

581006 603911 6244PI 645631

Mftno 02l 3 9f02P3 nP71t

9ASn141 611194A 6pP74T 64011

n3n4 I6nPi4no1 nWot

9n2-4

5704o1f 6 0 6p1791 64A9A

nflnl3 0 n046 5n1006 n5fIqp

620 640 660 680 700 720 740 760

670608 691812 713013 734211 755406 776599 797788 818975

502635 502558 5024A2 502411 502343 502279 902219 502162

66032u 690529 711720 732q27 754129 775314 79650A 8176911

512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S

66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q

qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A

66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185

n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172

66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44

526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76

A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80

1iOU4

o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl

780 800 820

840160 861343 882523

502107 502056 502006

838975 860057 88123A

502111 5112059 5f2000

83704 P9Q12 A90305

c02113 rn2061 K02011

83616rR RT754q 8787P7

502117 nfl5 qOP015

89u690 AR57q6 s76Q6o

Kno1p9 n2n6q So2Iq

83nRnfl A94918cP A753K7

100n19 qnfl 9n0no3

840 860 880 900

903702 92487c 946053 967226

501a5q 90t1i5 50172 501831

902416 92359P 944767 969941

501962 501ot7 5011 7 4 501P33

Q002I4 OP265q 943834 (69f006

501064 01c1 501876 50135

8QqqP4 02107q 0422nP 9634P3

50I16 q01093 Knfln7q fOIAIA

Rq141 ot01311 n4n0480 961647

n17P n10P6 R1p03 oI 44P

9649 Ql611 q3A771 95qonq

80l10 5 5fl 0 1010A6 9f1our

920 940 960

988397 1000567 1030735

901792 501754 501718

987111 1008210 1029448

5017q4 t01797 501721

9A6177 1007146 1121514

50176 017158

501722

0945Q3 1005761 1026928

If17n9 sn1761 9f017P5

Q8211 100 347 7 1025140

q0I102 901764 n172P

081046 100p1 102313

Ifvs A177 5A11

980 1000

1051902 1073067

501684 501651

1050619 1071780

501686 501653

1049680 1070845

501687 501694

1048093 1069257

901600 so16q7

104630P 1067461

01603 901699

1f4b4g 1069504

qfIKa6 If1A62

9ATF 033077 DArr 16PRW

V-INFINITY = 500 KMS

Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU

T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri

IDO0 1100 1200 1300 1400 1500 1600 1700 1800

1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918

901651 501503 q01379 501274 501184 901106 901038 900978 900924

10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628

501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24

1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680

rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029

1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA

rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040

nIq08 gs0QP6

1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P

90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17

501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9

9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo

1900 2000 2100 2200 2300

2024583 2130237 2235883 2341521 2447152

500876 900832 r007Q3 500757 r00725

20232Q9 2120947 2214593 2340231 244586

5f0R76 5f0833 gn07q3 9O07q8 90075

PO0P353 218007 PP33659 233q2gO P444021

500877 gflOfP3 I90-q4

079P 0fl7

P220743 212636 2P22040 P937677 441 07

snA77 FO0R14 F0l74 K0f7RI r0n726

P01807n 212 5gI Pin15 957Q9 2441418

5088A7A qffA14 Kdegf70 g0050 Ko0A

201A446 7IPfl4 pp777 P13pat 741AAR 7

5nnq nfnn

degnfn6 sfn6A 9nn7

h

2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000

55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706

rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335

2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414

50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335

Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A

4478828 50P4377 5gqQ2p5 9P5471

SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980

90017P 500364 509(05650O340 500342 50033-5i

P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846

50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP

(06A6 PS4nu4A rnn668 p6qnnl

fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144

nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710

5(0it4p 360o207 7 8A 7 05 9

r00465 3811414 5lf45 1IA0S075 nn441 U0234

i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln

srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0

g0nn03 snonI

q

fnniAg onnu53

qnnil6 0n0itl

5fnlnrlq 5n014nq tfl030 q

5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839

5100 5200

5403251 5508794

500328 500322

5401959 5507502

9003P8 900322

540I015 S001PR R506r5P 900322

53qq0 5504933

qn0i9g nn0pn

K9q7469 530O

50nnxpQ 900322

59464q 550n187

3n9 5nn39

5300 5400

5614336 5719877

500316 900310

5613044 5718589

500316 500310

5612100 5717641

r00316 500310

r610479 5716016

g50n16 nn2n

W0R549 r714n85

5n0316 qnOxAl1

q6n07l4 5711PAn

5nn116 Fnn 11

5500 5600 5700 5800 5)00 6000

5829416 5930955 6036492 614P028 6247563 6353098

rn0304 50029 5002q4 50028q 500284 500279

5824124 5920663 6035200 6140736 6246271 6351805

90035 5n0p9 090q4 500289 5n024 500270

rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861

500305 g0olqQo RnOq4 500280 50OP4 90027Q

21555 0pflo S826in 6138166 649701 614q239

500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP

50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q

R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4

5nnxnK srn Q gn09Q4 500n0q nnf04

gnnon

PRW flr 03W77 nArr 7

V-INFINITY = 600 KMS

T - YRS 0=

RAn 1AU

VEL q =

RAr) 3 AU

VEL n =

PAn 5 AU

Vft n = 10

PA) Atl

VFL a = PAn

20 MI VEL PAMn

5p fU VVl

00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60

56979 83199

6P5413 617524

55061 8110l

695863 617714 A1477

A61246324q76 A17P00 807 o 0

APA17 AInO

F56o A14l1

6pov7q 617AAe

7r Qt11171

61nnpQ 615RA7

80 100

10910( 134926

61340l 610860

10A043 133R4q

613R2 610047

lo7177 1st3e1

61361 11flnn

tOAgqo 1502c

A1Po n67or 611AI3940611non

e137n i155 13 flW s

AlAq0 AinIft

120 140

160656 186325

609134 607884

15057P 185236

60q2n5607Q30

1S8872 jAlrp7

600opg07aA0

157O014 IPI1r7

6flQO 008113

J-1N IRinfn

n031 6n0S6

Ierl 14Ut

6mnn An7017

160 180

211940 237538

606q36 6n6103

210895 236441

6n6072 6n6p2

Pjn130 PA5710

6n60q5 6n6940

rnnoo P34654

A7nn O9Apt

20A467 p 43Q30

A7nq1 606P7

11fn PAn I

AnSnSn AnAfl

200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240

28A637 314157

605101 604688

28753f 31305

6n510 6047n5

P6n05 619131 1193I6fl4

2897n0 i 6

65103 An311206

p4tr5 n-ins

6n9168 An4746

5nptSn A

-tpo Anq1 n AA0471

260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340

365150 3Q0628 416096 441554

6n4036 603773 6n3543 603330

364044 389521 41407 440445

6n4048 603784 603592 613348

363031 388780 41P4t5

UIQ0f

6n4nti f 61370 6n3590

An315A

3876A7 414j31n 43q41U

A1u1AOtq Aen 60n60 A1A62

IAJ61o R866P4

u1pnrq u37T 4 a

6n4n8 6fl1I 6ndeg9 A370

16un 3A611 41I-Afln

41in1

AnflnAA Anfnlp sMIn 71 6n3A

360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa

380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480

568742 594162 619579

602594 6024A3 602382

56762P 5P3o5 618466

6n29q 6n2408 6n2386

566p8f 9inf deg17719

6112603 6fn2qj6n2980

966qq 5011j9616P7

Anp6np 6P406 AnPQI

R645n 58o53 e135i

An2613

69Rn9109

R65hn qnoA=IA

6fn9613 Annl 6m Q

o 500 520

644991 67039q

602P88 61 22Nt

643R77 66q0R2

e0P2QP 6n22n9

641126 66A533

A6p295 6129oA

641035 6673140

A62paq AnP1

64degnr 666145

612311 6npois

Aqnq4n 6egna

An1 An1 7

-J 0

540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n

721206 746605

60207 601)77

720092 749412

602050 6O10O

71031R 744736

6npn0p 601ORP

71140 743S35

60n15 Anlpq

7164P7 74P31

A9nq 69t1A0

716455 74 17I

6nn6n 6nlno

600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640

707394 822784

601851 601704

79627A 82166q

601A54 6n17q7

705p4 n2024

61n186 611708

7q4 p07fl7

n 6I0t85q Anln01

70368 lP46

601n61 A1n14

7qP4k7 ct77

6118nl 60inn

660 680

84173 873559

601741 6016q0

847057 872441

6n1743 6n1692

A4Ao AviAv

6n1745 6016qu

A49n 870477

Af1747 An1A06

A4314U pAQP99

snstyn 601AO

A4lll 86R451

An19i 6 17n0

700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760

949706 975004

601559 601514

948580 97096A

60197 601516

9u7983 Q73plO

601558 AnlIr17

046618 071)09

6n11560 An 191 a

45147 07071n

6nlq6 611spl

040MA4A6158 Q68nn finICD3

7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840

1051210 1076583

601405 601372

1050091 1075466

6n1406 6n1373

ln4335 1074707

6nln7 0n1374

1048116 1073487

n14nq tnuARPn An1W76 107105

An1411 611177

10481c7 I071157

Af1012 Aflt1A

860 880

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900 920

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PRW DATF 011077 PArr Is

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S 5200 6599481 600224 6998358 6n02P4 6rQ7591l 60024 69q6339 6nnPP4 Ati40na 6noP04 fi9Q9011 Ann4 530 707 606724979 6n0P20 6724P08 60npp0 672PQ91 6nnP 0 67Plr 6n0nln0 671n l~ Aftdegni9 5400 6852713 600216 68q159n 6n02t6 6A9n824 60016 694q567 A00P16 6A4914n 6nn0gt16 6n4At Ann 16 5500 6979327 60023P 697820r 6n02t2 607743A 600pip 6Q76181 6nnP12 -6q7475i4 6n0OgtIP 607p74A 6nplp

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S 6000 7612390 6n0194 7611267 600104 76|A900 6n0194 760OP43 A0njQ4 76n7814 fi0n1o4 76n971) Annin4

r PUBLICATION 77-70

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