Page 1
DECLASSIFIED UNDE R AUTHORITY OF THE INTERAGENCY SECURITY CLASSIFICATION APPEALS PANEL EO 13526 SECTION 53(b)(3)
ISCAP APPEAL NO 2009-068 document no 2 DECLASSIFICATION DATE November 13 2014
I SECRET
CIAL HANDLING REQUIRED
RELEAS
U) LUNAR EXPlORATiON SYSTEM (LES) LAND AREA _RECOVERY R~NGlE AND ASSOCIATED COMMAND AND
CONTROL SYSTEMS SEPTEMBER 1963
TASKS 618207(24) 61820180)
~ AUl FORCE MBSSill
DEVELOPMENT CENTER DEPUVY fOR FOREIGM TECHNOlOGY
SECRli f (Thle page is unclaesiied)
l Information confl1cting w1th or pertinently affecting that con tained in this publi_cation should be forwarded by the rec1pient
directly to
AFMDC (MDFB) Holloman AFB New Mexico 88330
This in no way abbrogates or alters responsibility fat sending such information or any pertinent intelligence data through already established intelligence collection chan n e 1 s of the various services or agencies of the US Government
2 WARNING This document containe inpoundonn3tion affecting the national defense of the US within the meanmg of the Espionage Law Title 18 US C Sections 793 and 794 Its transmission or the revelation of its contents in any manner to an unauthorized
person is prohibited by law
3 Copies have not been placed in the D DC collection Address all requests for copies to AFMDC (MDFC)
4 Do not return this copy When not needed destroy in accordshyance with pertment security regulations
5 This publlcation has been designd to mlt~t the ~ ~1c aoJerl e of the r~cipit ~ for inte)h -middotltc~ Further dissemination by the recipient of parts or the wnole to subordinate elements must be based on the specific need-to-know of the recipient to perform his assigned mis~ions (Authority AFCLN Policy Lett~- lt05 - ~ dated ZO February 1959)
SECRET FOREIGN TECHNOLOGY REpORT
AFMDC-TR-b3middotl
(Title Unclassified) LUNAR EXPLORATION SYSTEM (LE[i LAND AREA RECOVERY RANGE AND
ASSOCIATED COMMAND AND cONTROL SYSTEMS
September 1963
Task b 18207(24 Task 618207(80)
Prepared by
Mr Michael E Cason Jr Captain WilHam J Barlow
This is a Foreign Technology document prepared and published by AFMDC for use primarily within AFSC lt has not been coordinated within AFSC or the Office of the ACSIntelligence Headquarters USAF bull and does not necessarily represent an agreed Air Force
position
DEPUTY FOR FOREIGN TECHNOLOGY AIR FORCE MISSILE PEVELOPMJNl CENER
AIR FORCE SYSTEMS COMMAND HOLLOMAN AIR FORCE BASE NEW MEXJo
SECREf AFMDC 63-3772(This page is unclassified)
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I
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-------- middot- -----middot-middot-middot- ---- -middot-middot- ---- - ~ amp-----middot-middot __
j
-middot- shy
S~GRET (U) PREFACl
The information reflected in this Technical Report has b en
prepared primarily or the use of Foreign Technology personnel
engaged in the analysis of the Soviet space effort This is an
Air FoTce Systems Command project and this contribution
will be of interest to those analysts concerned with Soviet land
recovery areas and their associated requi rements This report
serves as a technical support document for P1middotoject 6182 Tasks
618207(24) and 61820780) assigned to the Air Force Missile
Development Center ~
(U) PUBLICATION REVIEW
This Foreign Technolo~y documeri as t en -ravtebullved -C o
approved for tOltribuiot middotvtbull Lin the Air Force Systems Command (TJ bull
FOR THE COMMANDER
~~1-middotr Lt Col USAF Deputy for Foreign Technology
AFMDC 6~-37-72
middot middot ~ _ __ middot _--~~ ----~- --middot(
bull bull bull - middot--~- bull bull - - c - bull bull -- -middot
bull bull bull bull bullJ bull bull bull bullbullbull bull bull bull bull
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__
SECRET (U) TABLE OF CONTENTS
Preface
Summary iii
SECTION I (U) Lunar Re-Entry Vehicle
SECTION II J21 USSR Lunar Vehicle Recovery Site Selection bull bull bull bull bull bull bull bull 6
SECTION Ill 1-Bf Model of USSR Lunar Vehicle Recovery Range bull bull 26
30Bibliography
32Distribution bull
(U) LIST OF ILLUSTRATIONS
Figure 1 (U) Entry Corridors bull 4
Figure 2 (U) Range and Lateral Displacement fori Lifting Body Re-Entry 5
Figure 3 (U) General Population Density 10
Figure 4 (U) Optimum Recovery Staging Areas 16
Figure 5 kBf Krug Sites 20
Figure 6 (U) Recovery Tracking Network 21
Figure 7 (U) Search Recovery Network 25
Figure 8 (U) Optimum Lunar Recovemiddoty Area~ 28
Figure 9 (U) Miss ion Control Network 29
ii
SECRET AFMDC 63-3772
~ -middot-middot -middot----middot ---- middotmiddot-shymiddotmiddot
SECRET (U) SUMMARY
Purpose
This Technical Report was prepared in accordance with
requirements established by the Foreign Technology Division
Technical Operational Project Specilication (TOPS) Requireshy
ments are reflected on pages 28 and 91 of the Soviet Lunar
Exploration Program TOPS The results i n this report fulfill
the AFMDC portion of Tasks 618207(24) and 618207(80) pertaining
to lunar exploration vehicle land recovery range bull LS)
Conclusions
a The design characteristics of a lunar return vehicle its
guidance capabilities and geometrical mission constrairts
middotj I
determine the final geographic boundaries of any recovelY range j
j (U)
best suited for the establishment of a Soviet lun~- rr11rn vehicle
recovery range j8)
c Logistic support bases search recovery staging areas)
which would provide the most timely recovery o f a downed vehicle
are lo cated i n the northern sector of this are3 T U s sector i s
iii
SEGRtJ AFMDC 63-3772
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 2
l Information confl1cting w1th or pertinently affecting that con tained in this publi_cation should be forwarded by the rec1pient
directly to
AFMDC (MDFB) Holloman AFB New Mexico 88330
This in no way abbrogates or alters responsibility fat sending such information or any pertinent intelligence data through already established intelligence collection chan n e 1 s of the various services or agencies of the US Government
2 WARNING This document containe inpoundonn3tion affecting the national defense of the US within the meanmg of the Espionage Law Title 18 US C Sections 793 and 794 Its transmission or the revelation of its contents in any manner to an unauthorized
person is prohibited by law
3 Copies have not been placed in the D DC collection Address all requests for copies to AFMDC (MDFC)
4 Do not return this copy When not needed destroy in accordshyance with pertment security regulations
5 This publlcation has been designd to mlt~t the ~ ~1c aoJerl e of the r~cipit ~ for inte)h -middotltc~ Further dissemination by the recipient of parts or the wnole to subordinate elements must be based on the specific need-to-know of the recipient to perform his assigned mis~ions (Authority AFCLN Policy Lett~- lt05 - ~ dated ZO February 1959)
SECRET FOREIGN TECHNOLOGY REpORT
AFMDC-TR-b3middotl
(Title Unclassified) LUNAR EXPLORATION SYSTEM (LE[i LAND AREA RECOVERY RANGE AND
ASSOCIATED COMMAND AND cONTROL SYSTEMS
September 1963
Task b 18207(24 Task 618207(80)
Prepared by
Mr Michael E Cason Jr Captain WilHam J Barlow
This is a Foreign Technology document prepared and published by AFMDC for use primarily within AFSC lt has not been coordinated within AFSC or the Office of the ACSIntelligence Headquarters USAF bull and does not necessarily represent an agreed Air Force
position
DEPUTY FOR FOREIGN TECHNOLOGY AIR FORCE MISSILE PEVELOPMJNl CENER
AIR FORCE SYSTEMS COMMAND HOLLOMAN AIR FORCE BASE NEW MEXJo
SECREf AFMDC 63-3772(This page is unclassified)
~- middot middotmiddot middot bullmiddot bull middotmiddot bull-middotmiddotmiddot middot middotbull middot tr ~_ bullmiddot bull ~ _ middotbullbullmiddotmiddot -~middotmiddot middotmiddotbull -middotmiddot bullmiddotmiddot bullmiddot middotmiddotbullmiddot bullbullmiddotmiddotmiddot - -
I
middotmiddot ~~----~middotmiddotmiddot --~~--~ ~____ shy
- __ -- - ~ middotmiddot ---shy
~----~-=-~--~=-=--~-==---=~--=-- ~--~- bull-_middot~ ~~~ -_------ --=-lt --_- --=---shymiddot~ bull - ltn middot bull bullbullbull middot
-------- middot- -----middot-middot-middot- ---- -middot-middot- ---- - ~ amp-----middot-middot __
j
-middot- shy
S~GRET (U) PREFACl
The information reflected in this Technical Report has b en
prepared primarily or the use of Foreign Technology personnel
engaged in the analysis of the Soviet space effort This is an
Air FoTce Systems Command project and this contribution
will be of interest to those analysts concerned with Soviet land
recovery areas and their associated requi rements This report
serves as a technical support document for P1middotoject 6182 Tasks
618207(24) and 61820780) assigned to the Air Force Missile
Development Center ~
(U) PUBLICATION REVIEW
This Foreign Technolo~y documeri as t en -ravtebullved -C o
approved for tOltribuiot middotvtbull Lin the Air Force Systems Command (TJ bull
FOR THE COMMANDER
~~1-middotr Lt Col USAF Deputy for Foreign Technology
AFMDC 6~-37-72
middot middot ~ _ __ middot _--~~ ----~- --middot(
bull bull bull - middot--~- bull bull - - c - bull bull -- -middot
bull bull bull bull bullJ bull bull bull bullbullbull bull bull bull bull
middotmiddot - middot _ ~ middot ~~-- lt_-middot middotgt - middot - -_ - - ) - ~middot -middot middot
- bullbull middot--- -middot --------~-~----middot -middot- middotmiddot - middot middot _ _ __ bull bull bull bullbull ______ bull _ ______ ~--middot - -_- middot middot middot -middot middot bullbullbullbullbull -- -middotmiddot middot shy
__
SECRET (U) TABLE OF CONTENTS
Preface
Summary iii
SECTION I (U) Lunar Re-Entry Vehicle
SECTION II J21 USSR Lunar Vehicle Recovery Site Selection bull bull bull bull bull bull bull bull 6
SECTION Ill 1-Bf Model of USSR Lunar Vehicle Recovery Range bull bull 26
30Bibliography
32Distribution bull
(U) LIST OF ILLUSTRATIONS
Figure 1 (U) Entry Corridors bull 4
Figure 2 (U) Range and Lateral Displacement fori Lifting Body Re-Entry 5
Figure 3 (U) General Population Density 10
Figure 4 (U) Optimum Recovery Staging Areas 16
Figure 5 kBf Krug Sites 20
Figure 6 (U) Recovery Tracking Network 21
Figure 7 (U) Search Recovery Network 25
Figure 8 (U) Optimum Lunar Recovemiddoty Area~ 28
Figure 9 (U) Miss ion Control Network 29
ii
SECRET AFMDC 63-3772
~ -middot-middot -middot----middot ---- middotmiddot-shymiddotmiddot
SECRET (U) SUMMARY
Purpose
This Technical Report was prepared in accordance with
requirements established by the Foreign Technology Division
Technical Operational Project Specilication (TOPS) Requireshy
ments are reflected on pages 28 and 91 of the Soviet Lunar
Exploration Program TOPS The results i n this report fulfill
the AFMDC portion of Tasks 618207(24) and 618207(80) pertaining
to lunar exploration vehicle land recovery range bull LS)
Conclusions
a The design characteristics of a lunar return vehicle its
guidance capabilities and geometrical mission constrairts
middotj I
determine the final geographic boundaries of any recovelY range j
j (U)
best suited for the establishment of a Soviet lun~- rr11rn vehicle
recovery range j8)
c Logistic support bases search recovery staging areas)
which would provide the most timely recovery o f a downed vehicle
are lo cated i n the northern sector of this are3 T U s sector i s
iii
SEGRtJ AFMDC 63-3772
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
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-36 37
__ - w~c o3-3772
-middotshybull bull
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bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
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middot __
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-middotmiddot~ middot middot~
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- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 3
SECRET FOREIGN TECHNOLOGY REpORT
AFMDC-TR-b3middotl
(Title Unclassified) LUNAR EXPLORATION SYSTEM (LE[i LAND AREA RECOVERY RANGE AND
ASSOCIATED COMMAND AND cONTROL SYSTEMS
September 1963
Task b 18207(24 Task 618207(80)
Prepared by
Mr Michael E Cason Jr Captain WilHam J Barlow
This is a Foreign Technology document prepared and published by AFMDC for use primarily within AFSC lt has not been coordinated within AFSC or the Office of the ACSIntelligence Headquarters USAF bull and does not necessarily represent an agreed Air Force
position
DEPUTY FOR FOREIGN TECHNOLOGY AIR FORCE MISSILE PEVELOPMJNl CENER
AIR FORCE SYSTEMS COMMAND HOLLOMAN AIR FORCE BASE NEW MEXJo
SECREf AFMDC 63-3772(This page is unclassified)
~- middot middotmiddot middot bullmiddot bull middotmiddot bull-middotmiddotmiddot middot middotbull middot tr ~_ bullmiddot bull ~ _ middotbullbullmiddotmiddot -~middotmiddot middotmiddotbull -middotmiddot bullmiddotmiddot bullmiddot middotmiddotbullmiddot bullbullmiddotmiddotmiddot - -
I
middotmiddot ~~----~middotmiddotmiddot --~~--~ ~____ shy
- __ -- - ~ middotmiddot ---shy
~----~-=-~--~=-=--~-==---=~--=-- ~--~- bull-_middot~ ~~~ -_------ --=-lt --_- --=---shymiddot~ bull - ltn middot bull bullbullbull middot
-------- middot- -----middot-middot-middot- ---- -middot-middot- ---- - ~ amp-----middot-middot __
j
-middot- shy
S~GRET (U) PREFACl
The information reflected in this Technical Report has b en
prepared primarily or the use of Foreign Technology personnel
engaged in the analysis of the Soviet space effort This is an
Air FoTce Systems Command project and this contribution
will be of interest to those analysts concerned with Soviet land
recovery areas and their associated requi rements This report
serves as a technical support document for P1middotoject 6182 Tasks
618207(24) and 61820780) assigned to the Air Force Missile
Development Center ~
(U) PUBLICATION REVIEW
This Foreign Technolo~y documeri as t en -ravtebullved -C o
approved for tOltribuiot middotvtbull Lin the Air Force Systems Command (TJ bull
FOR THE COMMANDER
~~1-middotr Lt Col USAF Deputy for Foreign Technology
AFMDC 6~-37-72
middot middot ~ _ __ middot _--~~ ----~- --middot(
bull bull bull - middot--~- bull bull - - c - bull bull -- -middot
bull bull bull bull bullJ bull bull bull bullbullbull bull bull bull bull
middotmiddot - middot _ ~ middot ~~-- lt_-middot middotgt - middot - -_ - - ) - ~middot -middot middot
- bullbull middot--- -middot --------~-~----middot -middot- middotmiddot - middot middot _ _ __ bull bull bull bullbull ______ bull _ ______ ~--middot - -_- middot middot middot -middot middot bullbullbullbullbull -- -middotmiddot middot shy
__
SECRET (U) TABLE OF CONTENTS
Preface
Summary iii
SECTION I (U) Lunar Re-Entry Vehicle
SECTION II J21 USSR Lunar Vehicle Recovery Site Selection bull bull bull bull bull bull bull bull 6
SECTION Ill 1-Bf Model of USSR Lunar Vehicle Recovery Range bull bull 26
30Bibliography
32Distribution bull
(U) LIST OF ILLUSTRATIONS
Figure 1 (U) Entry Corridors bull 4
Figure 2 (U) Range and Lateral Displacement fori Lifting Body Re-Entry 5
Figure 3 (U) General Population Density 10
Figure 4 (U) Optimum Recovery Staging Areas 16
Figure 5 kBf Krug Sites 20
Figure 6 (U) Recovery Tracking Network 21
Figure 7 (U) Search Recovery Network 25
Figure 8 (U) Optimum Lunar Recovemiddoty Area~ 28
Figure 9 (U) Miss ion Control Network 29
ii
SECRET AFMDC 63-3772
~ -middot-middot -middot----middot ---- middotmiddot-shymiddotmiddot
SECRET (U) SUMMARY
Purpose
This Technical Report was prepared in accordance with
requirements established by the Foreign Technology Division
Technical Operational Project Specilication (TOPS) Requireshy
ments are reflected on pages 28 and 91 of the Soviet Lunar
Exploration Program TOPS The results i n this report fulfill
the AFMDC portion of Tasks 618207(24) and 618207(80) pertaining
to lunar exploration vehicle land recovery range bull LS)
Conclusions
a The design characteristics of a lunar return vehicle its
guidance capabilities and geometrical mission constrairts
middotj I
determine the final geographic boundaries of any recovelY range j
j (U)
best suited for the establishment of a Soviet lun~- rr11rn vehicle
recovery range j8)
c Logistic support bases search recovery staging areas)
which would provide the most timely recovery o f a downed vehicle
are lo cated i n the northern sector of this are3 T U s sector i s
iii
SEGRtJ AFMDC 63-3772
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 4
I
middotmiddot ~~----~middotmiddotmiddot --~~--~ ~____ shy
- __ -- - ~ middotmiddot ---shy
~----~-=-~--~=-=--~-==---=~--=-- ~--~- bull-_middot~ ~~~ -_------ --=-lt --_- --=---shymiddot~ bull - ltn middot bull bullbullbull middot
-------- middot- -----middot-middot-middot- ---- -middot-middot- ---- - ~ amp-----middot-middot __
j
-middot- shy
S~GRET (U) PREFACl
The information reflected in this Technical Report has b en
prepared primarily or the use of Foreign Technology personnel
engaged in the analysis of the Soviet space effort This is an
Air FoTce Systems Command project and this contribution
will be of interest to those analysts concerned with Soviet land
recovery areas and their associated requi rements This report
serves as a technical support document for P1middotoject 6182 Tasks
618207(24) and 61820780) assigned to the Air Force Missile
Development Center ~
(U) PUBLICATION REVIEW
This Foreign Technolo~y documeri as t en -ravtebullved -C o
approved for tOltribuiot middotvtbull Lin the Air Force Systems Command (TJ bull
FOR THE COMMANDER
~~1-middotr Lt Col USAF Deputy for Foreign Technology
AFMDC 6~-37-72
middot middot ~ _ __ middot _--~~ ----~- --middot(
bull bull bull - middot--~- bull bull - - c - bull bull -- -middot
bull bull bull bull bullJ bull bull bull bullbullbull bull bull bull bull
middotmiddot - middot _ ~ middot ~~-- lt_-middot middotgt - middot - -_ - - ) - ~middot -middot middot
- bullbull middot--- -middot --------~-~----middot -middot- middotmiddot - middot middot _ _ __ bull bull bull bullbull ______ bull _ ______ ~--middot - -_- middot middot middot -middot middot bullbullbullbullbull -- -middotmiddot middot shy
__
SECRET (U) TABLE OF CONTENTS
Preface
Summary iii
SECTION I (U) Lunar Re-Entry Vehicle
SECTION II J21 USSR Lunar Vehicle Recovery Site Selection bull bull bull bull bull bull bull bull 6
SECTION Ill 1-Bf Model of USSR Lunar Vehicle Recovery Range bull bull 26
30Bibliography
32Distribution bull
(U) LIST OF ILLUSTRATIONS
Figure 1 (U) Entry Corridors bull 4
Figure 2 (U) Range and Lateral Displacement fori Lifting Body Re-Entry 5
Figure 3 (U) General Population Density 10
Figure 4 (U) Optimum Recovery Staging Areas 16
Figure 5 kBf Krug Sites 20
Figure 6 (U) Recovery Tracking Network 21
Figure 7 (U) Search Recovery Network 25
Figure 8 (U) Optimum Lunar Recovemiddoty Area~ 28
Figure 9 (U) Miss ion Control Network 29
ii
SECRET AFMDC 63-3772
~ -middot-middot -middot----middot ---- middotmiddot-shymiddotmiddot
SECRET (U) SUMMARY
Purpose
This Technical Report was prepared in accordance with
requirements established by the Foreign Technology Division
Technical Operational Project Specilication (TOPS) Requireshy
ments are reflected on pages 28 and 91 of the Soviet Lunar
Exploration Program TOPS The results i n this report fulfill
the AFMDC portion of Tasks 618207(24) and 618207(80) pertaining
to lunar exploration vehicle land recovery range bull LS)
Conclusions
a The design characteristics of a lunar return vehicle its
guidance capabilities and geometrical mission constrairts
middotj I
determine the final geographic boundaries of any recovelY range j
j (U)
best suited for the establishment of a Soviet lun~- rr11rn vehicle
recovery range j8)
c Logistic support bases search recovery staging areas)
which would provide the most timely recovery o f a downed vehicle
are lo cated i n the northern sector of this are3 T U s sector i s
iii
SEGRtJ AFMDC 63-3772
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 5
- bullbull middot--- -middot --------~-~----middot -middot- middotmiddot - middot middot _ _ __ bull bull bull bullbull ______ bull _ ______ ~--middot - -_- middot middot middot -middot middot bullbullbullbullbull -- -middotmiddot middot shy
__
SECRET (U) TABLE OF CONTENTS
Preface
Summary iii
SECTION I (U) Lunar Re-Entry Vehicle
SECTION II J21 USSR Lunar Vehicle Recovery Site Selection bull bull bull bull bull bull bull bull 6
SECTION Ill 1-Bf Model of USSR Lunar Vehicle Recovery Range bull bull 26
30Bibliography
32Distribution bull
(U) LIST OF ILLUSTRATIONS
Figure 1 (U) Entry Corridors bull 4
Figure 2 (U) Range and Lateral Displacement fori Lifting Body Re-Entry 5
Figure 3 (U) General Population Density 10
Figure 4 (U) Optimum Recovery Staging Areas 16
Figure 5 kBf Krug Sites 20
Figure 6 (U) Recovery Tracking Network 21
Figure 7 (U) Search Recovery Network 25
Figure 8 (U) Optimum Lunar Recovemiddoty Area~ 28
Figure 9 (U) Miss ion Control Network 29
ii
SECRET AFMDC 63-3772
~ -middot-middot -middot----middot ---- middotmiddot-shymiddotmiddot
SECRET (U) SUMMARY
Purpose
This Technical Report was prepared in accordance with
requirements established by the Foreign Technology Division
Technical Operational Project Specilication (TOPS) Requireshy
ments are reflected on pages 28 and 91 of the Soviet Lunar
Exploration Program TOPS The results i n this report fulfill
the AFMDC portion of Tasks 618207(24) and 618207(80) pertaining
to lunar exploration vehicle land recovery range bull LS)
Conclusions
a The design characteristics of a lunar return vehicle its
guidance capabilities and geometrical mission constrairts
middotj I
determine the final geographic boundaries of any recovelY range j
j (U)
best suited for the establishment of a Soviet lun~- rr11rn vehicle
recovery range j8)
c Logistic support bases search recovery staging areas)
which would provide the most timely recovery o f a downed vehicle
are lo cated i n the northern sector of this are3 T U s sector i s
iii
SEGRtJ AFMDC 63-3772
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 6
~ -middot-middot -middot----middot ---- middotmiddot-shymiddotmiddot
SECRET (U) SUMMARY
Purpose
This Technical Report was prepared in accordance with
requirements established by the Foreign Technology Division
Technical Operational Project Specilication (TOPS) Requireshy
ments are reflected on pages 28 and 91 of the Soviet Lunar
Exploration Program TOPS The results i n this report fulfill
the AFMDC portion of Tasks 618207(24) and 618207(80) pertaining
to lunar exploration vehicle land recovery range bull LS)
Conclusions
a The design characteristics of a lunar return vehicle its
guidance capabilities and geometrical mission constrairts
middotj I
determine the final geographic boundaries of any recovelY range j
j (U)
best suited for the establishment of a Soviet lun~- rr11rn vehicle
recovery range j8)
c Logistic support bases search recovery staging areas)
which would provide the most timely recovery o f a downed vehicle
are lo cated i n the northern sector of this are3 T U s sector i s
iii
SEGRtJ AFMDC 63-3772
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 7
d Assuming the use of a semi-ballistic lunar re-entry
vehicle the northeastern sector bounded nominally by 48degN-o8degE
number of existing staging areas The use of this sector could
minimize the search and recovery time by using of a number of
nominally equidistant staging area$ fir
e The recovery range currently being used for Soviet
earth orbit recovery operations appears to fall within this sector
and would serve equally well without modification for the recovery
of a semi-ballistic lunar return vehicle ~
f The recovery range for a lifting lunar return vehicle would
most suitably be located in the low level arid southern sectors
The use of this type vehicle would aho require the development of additional facilities for ternuna tracking anc --dOwe llcluliramp
(1) A complex terminal range tracking network
2) Terminal range command and control middot strurrcntaticn
(3) Terminal range control and logistics complex
(4) Primary and secondary landing sites J8l
Background Highlights
Due to a void in available information concerJ~ middot E p~-gtnned site
iv
SECRET
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 8
- ------- - -- middot middot -- -- -- ___ ___ ___ ---~ ------- -------middot---- middot- ~ middot ~ -
SECtkt se le ctio_n for a Soviet lunar return mission informahon used in
the preparation of this study consisted primarily of a review of
current Soviet range recovery areas and their utity or use as
lunar vehicle recovery sites Although source material does
suggest that the Soviets plan earth-moon-earth recovery operashy
tions little or no information is available as to the type of vehicle
to be used or what preparations may be underway to establish a
land-based recovery range specifically designed for a lunar return
mission 8r
The types of re-entry vehiclebull which are discussed briefly in
-this report stem from studies conducted in support_of the US
lunar program and are used only as an aid in the site selection
criteria (U)
-~ i
v
SECRET AFMDC 63-3772
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 9
middot-middotmiddot- -middotmiddot -middotmiddot---middot- -- ~ -middot- middotmiddotmiddot--middot- middotmiddot- -~-- middot middot middot -middotmiddot ---- - middot middot-----middot--middotmiddot-middot middotmiddot -middot
SECRff SECTION 1
U) LUNAR RE-ENTRY VEHICLE
In order to determine what site selection criteria should be
used in selecting an optimum lunar recovery range the design
characteristics of the proposed re-entry vehicle must be defined U
US design studies related to the development of a lunar
1middoteturn re-entry vehicle have pomted out the complexity in the
overall systems design for this type of mission Ultimate vehicle
design will be largely dependent on the supercrbital velocities
enccunte1middoted upon re-entry into ~e earths atmosphere Velocities
encountered will be near 36000 fps as opposed to the nominal
25000 poundps encoUntered by a low earth orbit vehicle The
inaccuracy in tracking vehicles at auperorbital velocities over long
distances also becomes a sfgtrious problem during the return leg of
the lunar trajecto-y as well cs iurirg enrv into --gt -bull rtigt
atmosph middota (TT)
All space vehicles entering the earths atmosphere at ltgtupershy
orbital velocities can be classed into two broad groupe --those
with no lift (ie ballistic) and these whose lift-to-drag ratio
(L ) ) 0 Re-entry vehicles in the latter group also fall into0
two classes -- those of a fixed design with a constant lift
SECREf AFMDC 63-377Z
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 10
-~ -----~middot middot --- middot middot-middot---middot middotmiddotmiddot------ middotmiddotmiddotmiddotmiddot-middot ---middot-middot- middot middot~-middot-middot --middotmiddot-middot --middot----middotmiddotmiddotmiddot--middot-middot---- --
middot
SECRff coeifirient CL for any given angle of attack and a second class
with a variable-geometry configuration Fixed CL designs have
been tested in ihe US however the variable -geometry concept
has not received any appreciable study One such variable-geomshy
etry design calls for folded wing$ on the leeward side of a
relatively compact vehicle Aiter the vehicle has slowed down and
reached a low altitude the wings are unfolded to provide control
and stability required for a soft landing (81
In the design opound a vehicle which re middotenters the atrnogphere
from the moon it is assumed that the objective of re-entry is to
arrive at a particular point on the earth1 s surface If it has no
guidance system the vehicle will depend entirely on the forces that
act upon it during its precalculated trajectory Thue it may be
best that the vehicle has no lift since unexpected variations in
auch parameters as density and wind velocity will more severely
affect the trajectory of a lifting vehicle than they wbullll oi a bilistbull ~
or a serri-ballistic (LD~ bull S) type On the other hand_ a
guidance and control system can cor~~ct for any middot- middotnmiddotP-Cted
deviation of the vehicle from the prescribed descetbullbull path (U)
Until a vehicle e maximum re middotentry velocity ar-i trajectory
are specified the exact form of the lifting suriaca middotmiddot ~_net be
2
SECRET AFMDC 63-3772
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 11
-amp -bull bull bull -- ~ - - -- -middotmiddot - -middot-middotmiddot middot - middot ~ middot - middot -- middotmiddot ~ - - -middot ___ __ _ __ middotmiddotmiddot middotmiddotmiddotmiddot middot- middot~
SECRpoundr accurately defined As the velocity mounts it becomes incr eas ingly
difficult to provide suitable lift because of the severity of heating
conditions In these circumstances it is necessary to comp-romise
cont~al requirements and design a more compact vehicle with a
lowe-r Lf D ratio (U
I I Due to the tolerance li~tations placed on the re-entry vehicle
~ by the boundaries of a smalL lunar retu1middotn re-entry corridor it
has been fourtd that a lift vehi cle with a small LtD (on the order of i
I ) l bull 5) can enter the atmosphere a t a steeper angle and lower trajectory
approach than a ballistic vehicle ltgtnd therefore increase the
I corridor depth by extending both the ove-rshoot anlti undershoot~
boundaries (Figure 1) bull (8)
Inasmuch as the semi-ballistic (LID~ bull 5) re-entry vehicle
provides atructural simplicity compactness and relative lightshy
nesa with respect to the entire lunar mission it is as11umed for the
purposes of thia report that this type of venicle wiibull be used middottythe
Soviets for 1unar return missions Figure 2 shows the range and
lateral displacement for a lifting body e-entry (rr~xigt-1-rt Ln 0 5
auuming return veloci ty deceleration to ZSOOO fps ~
3
SECRET
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 12
bullbull---middot ~middot r -- middotmiddotmiddotmiddotmiddot
0ERSHLOi BOUNDARY ~~NDE~SHOOT BOUNDARt WITH NEGATIVE LIFT __ WITH PoSITIVE LIFl
r middot - G-UMITED --shy
(II) BALLISTIC CORRIDOR
(b) LIITIlc DRRIOOR
rlG l (U) ENTRY CORRiDORS
UNCLASSIFIED
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 13
e ~c c e
bullJgt middot ~ shyco iS rs 61 j
20
1
1
I A l+n -at lnitial
OfmlJclevbulllcdlttllOcgtnn from hlgtmiddot
~
~
~pproach bull
300 000 ft 250000 225000
000 0 ~
ILu n
ei~ h0 bull Joo ooo It
~middot J
ICLD)max bull 0 5 VImiddot -bull~ middotshy bank 6
L0 01
middot ~
Basic approach
~ (LO)max and ero ri bank angleshy
~ ~~~ ~ ~middot
~I=~~= ~~~ -1 ~~~~
A~~~~
1000 2vbull)O middotmiddotzsoo JOJO
Range (naut rni ) UNCLASSl FE 1
Fji[ z Range and Lateral Oisplacem~ middotmiddot bull-middot tbg Body Remiddot Entry
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 14
~ --- middot middotmiddot middot--~~- ~ ~ _-shy- --middot-middotmiddot - middot--middotmiddot- - ___ __ __________
SECRH SECTION U
(S1 USSR LUNAR RECOVERY SITE SELECTION
Pnor to asses Bing the op~ratioral characteristics of a land
a1middotea recovery range for returning Soviet lunar exploration
vehicles it is necessary to define the external parameters which
influence site selection (81
Problems which affect the earth entry of a returning lunar
vehicle are inherent_ in the entire system beginning with the powered
flight phase of the trajectory Accurate preprogrammed trajectory
calculations which best fit the mission are initially controlled by
geometrical constrainta such as the location of the launch and
recovery sites azimuth of fire declination o( the moon time
elements involved and velocity requil-ed to achieve the proper
trajectory Assuming that the prelaunch calculations can be
vehie can foil~middot middot lamp programmed trajectory an accurat~ error
analysis is necessary throughout the entire flight By using
inertial or ground radio command guidance syJtems the vehicle
can then be corrected along its trajectory making it possible to
hit a precalculated earth re-entry window Thi~lt window constrains
the allowable tolerances of the re-entry vehicle and governs the
6
SECRET AFMDC 63-3772
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 15
SECRET boundaries of the vehicle d1splacernent with respect to the calculated
landing site
As discussed in Section I a pure ballistic re-entry vehicle
design for lunar return missions necessitates the use of a narrow
re-entry corridor with low tolerances on guidance accuracy The
use of such a system would require an extremely accurate ground
based tracking network providing finite data during the terminal
leg of flight (U)
The lifting vehicles LID ) 1 although ofiering a wider
re-entry corridor and more maneuverability necessitates a more
complex design criteria and mission control system (U)
The use of a semi-ballistic lunar re-entry vehicle (nominal
Lfo bull 5 would offer a mean re-entry corridor provide adequatel I
range accuracy and still incorporate design simplicity Assuming
that this type of re-entry vehicle wiU be chosen by the Soviets and
that they will continue to utilize a ~aouth to n~gtl th re- atry ccrr~Jcr
a slte selection criteria can be defined and used to project the most
likely recovery area within the USSR ~
Lunar Recovery Range Criteria
a Security
In the USSR as in the US toleraHe seurir constraints
should be maintained during the re-entry and recovery gt-1 tee of a
7
SECRET AFMDC b3-377Z
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 16
middot-- - ~ ~_ ____ __middot--- ----- - -a__ bullbull bull middot -middotmiddot - middot - middot -- ~-middot -bull middot middot -bullbullbullbull bull--middot bull
lunar return miss ion
SECRET The recovery area chosen should m inimize
the opportunity lor unauthorized persons to locate and examine the
re~entry vehicle prior to exploitation by trained recovery forces
In order to accomplish this the recovery area should either be
j 11parsely populated or under continuous security control bull (8f
A review of current Soviet earth orbit recoveries indicates
-I that the re-entry corr idor lies between the longltudinal boundaries
of the Tyura Tam and Sary Shagan rangehead areas with impact
occurring just north of the range boundaries The Soviet range
areas lend themselves well to middotthe maintenance of tight security
during recovery operations without necessitating full-time security
personnel Due to the relatively low population density in the
area overshoots into the northern latitudes would require only
I ~
~
minimal additional security restrictions ~
Use of air or ground mobile forces could also provide the
Soviets with a relatively lowcoat security for c~ when bull ~~deo
Gro11nd mobile forces could be air transported to the planned
recovery area prior to re-entrybull fS)
b Safety
A primary consideration in laying out a land rec-gtvery range
for a lunar re~entry vehicle is the safety and control of bullc populashy
tion residing in the area The site selected should ideaLmiddot middot-abulll a
8
SECRET AFMDC 63-3772
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 17
- -- middotmiddot- middotmiddot- -----middot- ---- -- -- middot-middot bullmiddotmiddot ---~----middot middot-- --~- middot -middot~---middotmiddotmiddot ~ ___
SECRET sparse population commensurate w1th the predicted accuracy and
controllability of thP spacecraft ln order to avoid a serious
mishap during re-entry the close supervision of the ClVllian and
military population in the area is a necessary factor (U)
Use of Soviet missile test range areas for recovery
purposes would be well suited for such supervision cf personnel
Military and civilian personnel located in the proposed recovery
area could be alerted or removed during the recovery exercise
and all air I ground movement could be controlled fST
Population densities at latitudes under approximately
50degN on the existing range areas are almost exclusively under
one person per square kilometer Even at latitudes slightly north
of the middotrange areas to approximately 56deg the population density
increases only slightly poundrom one to ten middotpersons per square
known tc- middotampe a pop leoicn over 200000 people The remainiu~
widely scattered cities in this region are a ll between 5COOgt and
ZOOOOO in population (Figure 3) (S1
c Terrain
One of the most critical facto r s asaociated w ith land recovery
range planning is the general terrain characteriogttics In order to
9
-SECRETshy AFMDC 63-3772
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 18
-middot--middotmiddotmiddot-middot __ middotmiddotmiddotmiddotmiddot middotmiddot -----middot- middot- middot- ---- middotmiddot----middot-middotmiddot~-middotmiddotmiddotmiddot - -
- middot1 i
j
i I i
i l
l
-
~ECRfr optimize locat10n and recovery of a downed vehicle the landing site
should offer the least number of hazards to the incoming vehicle
as well as the recovery force If possible mountc~nous areas
heavy forest treae and water areas should be avoided Use of a
lifting type re-entry vehicle would require an expansive flat terrain
area suitable for an aerodynamic type land1ng This type of re-entry
would also require add1tional latbed areas for abort and overshoot
conditions The use of a semi-ballistic re-entry vehicle employing
parachute ltlrag devices would ideally also require a large flatbed
area for impact This type of vehicle however could suitably
land on relatively low flat or rolling hill type terrain with negligible
effects on the re-entry vehicle This type of terrain would also
still offer good accessibility by helicopter poundor expeditious physkal
recovery The extent of the area needed ior a semi-ballistic lunar
re-entry vehicle ia dependent largely on tracking and guidance
accuraci~e achieved prior to and during le-entry iU)
Assuming that the Soviets will continue to use the current
recogtrery range in the development oi a lunar pr~grco th3 area
should prove quite adequate The range area boumled by the Tyura
Tam and Sary Shagan rangeheads is an arid low~anmiddot ~S region The
area on the northeastern border of the Sltgtry Shagltgt -nge ia an arid
11
AFMDC 63 - 3772
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 19
~ __~
SECRET plains type region with low rolling hills to the southeast and northshy
west o the city o Karaganda Assummg that a laterai re -etltry
dispersion opound between 60deg und 80degE was possilc~ the Ural mountain
range to the northwest a nd the mountain range directly east of 80deg
should present no problem in landing or recovery ~
Since terrain surround ing the current recovery area is one
of the most suitable areas (if not the most) in the USSR for landing
and recovery it seems likely that this area would be projected for
use in a programmed lunar mission ~
The southern boundaries of the available rarge area would
probably be the 44degN latitude providing entry well within the USSR
The northern boundary would be restricted to an area generally
below 56degN latitude due to population densUy and higher elevation~
in the middot terrain ~
d Cliznatology
The general weather conditiols of a proposed recovery
range play an important role in site selection Since visualmiddot
observation is an important factor in search bull ecvvery operations
the area cnosen bullhould be relatively free from overcast ground
fog rain and snow during as much of the y ar ~ possible (U)
Although the recovery orCe5 ~hgtUld b =-~ middotlipped to handle
searchrecovery operations duling bad or hazardos WEather the
12
SECRH AFMDC 63-3772
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 20
- ____- --middot middotmiddotmiddot -middotmiddotmiddot -----~ ___ middotmiddot--middotmiddot- - middotmiddot-- -shy
efficiency with which the operation is carried out is dependent on
the generaL weather characteristics of the area (U
Climatic conditions at the nom_~al Sl 0 N range now being
used for recovery ha full seasonal weather varying rom middotmiddotl0degF
in January to 90degF in July The 6lOW lin dips down into the
recovery zone in the winter months but is much less critical than at
any opound the more northern latitudes The present recovery range
and its areas toward the southern boundaries a the USSR make
use of one of the best climatic regions in the USSR Sf
e Logistic Support
Functions of the recovery support bases located on or
near the recovery range for a lunar mission are again dependent
011 the type vehicle utilized By using a semi-ballisticre-entry
vehicle with guidancp accu~middotacies on the order of t_ ~00 NM in
doWltranie and late10al displac~ ments Ound suFgtort facilities
could be hr 11 to a rnbimum 81
Ground mobile recov(ry teams could be staged poundrom bases
around the recovery area with little additjonal workload on the
exisoting bases Primary considerations would be the housing of
personnel and vehicle maintenance (Ui
If expeditious physical recovc ) a~ the downed lWJar vehicle
is a requirement in the USSR (as in mann~lt flights) helicopter
13
SECltET AFMDC 63-3172
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 21
-----shy middot -middotmiddot middot----shymiddotmiddot ---middotmiddot _ ___ shy -middotmiddot-----shymiddotmiddotmiddotmiddotmiddotmiddotmiddot-middot -shy middot middotshy
SECRfl recovery teams equipped with spcca~ piclltup gear would be the
best recovery method to use H this type recovery is deaigned
or the pickup of a lunar vehicle the prime logistics problem would
be staging areas in close proximity to the planned impact area which
would be capable oi hmdling refueling ope rations The northeast ern i
i and northwestern sectors of the remiddotentry range currently being
used would appear to have airfields l arge enough to handle
refueling operations for this type of craft Due to limited range
and speed capabilities of helkopters staging would probably be
programmed from three or iour areas on the recovery range The
exact numbebull of helicopters staged from each location would be
dependellt on the accuracy of the search aircraft in locating the
downed vericle )$)The search aircraft located in or near the recovery range
presents a more complex logistics problem Assuming that light
cargo tygte ailcrat will be llsed for search operltgtolons lariing
strips and refueling points_will have to be established on or near
the planned impact area Having e~ablished th r az a hounded by
of the most suitable areas in the USSR for re=overy airfield
I
J
i ~
I
i
A
middot
14
SfCRpoundT
1
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 22
-middot -middot-middotmiddotshy middot-shy middot bull bullbull4bull _ _ _ - middot middotmiddot middot middot-middotshy ---shy - middot - middot middot-shy - --shy - shy _ _ - bullbullbullbullbullbull_ _
SECREa and ale most strat~gically located in the northeastern sector of
the range Based on the Tass-announced recovery points poundor
Vostoks V and vr this general recovery sector was usee poundor
these operations Utilization of this area provided the Soviets
with the most suitable aircraft and helicopter staging sector on
the recovery range The northwestern sector combined with
the sectors along the northern border appear to ofer the second
best aircraft staging area for recovery within the range
boundalies tFigure 4) ~
f Recovery Associated Command and Control
An essential element in the success of any recovery operashy
tion is the eflectiveness of its conunand and control network As
noted earlier the scope of instrumentation required for this phase
o the lunar tnission is a direct function of the type of re-entry
vehicle utilized (U)
(1~ ~i-Ballietic v~~~=
(a) US Program
The current proposals for the Apollo l na paceshy
craft point up the plans to incorporate the semi-ballistic design
in the us moon program us intention5 for comman cond
control equipment for Apollo currently call for ~he use o f lt~
Deep Space Instrumentation Facilities (DSIF) network with attiona
15
SEMl AFMDC 63-3772
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 23
____ ~~ __ ~ ~~~~__C7f-=-~J
middot-middotmiddot middotmiddotmiddot--middotmiddot ----shy --middotmiddotmiddotmiddot - ~
i
1
I j
- _middot -
--~
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 24
----middot~bullbullbull bull-bull bullbull-bullbullbull --- bull bull middot middot -middot - bullmiddot -- r~ bull ~- middot~ ---- ~bullbull bullbull bull - middot ~- middot bull middot bullmiddot
at the Jet Propulsion Lab (JPL) Goldstone Facility California
Woomera Australia Johannesburg South Africa and at least one
mobile station located near mission injection points Each of
these stations is located at approximately equal longitudinal
intervals around the globe each iii equipped with 85-foot diameter
I I
reflectors capable of precision tracki ng and communications and
i each station can provide coordinated tracking command and
telemetering functions for middotdeep space probes The Apollo program
wi ll also use existing Mercury control stations encompassing the
Pacific and Atlantic Range instrumentation sites Data collected
from the combined sites is fed into the Goddard Space Flight
G~nter for real-time analysis ~
(b) Soviet Program
By using a semi-ballistic re-entry vehicle the
Soviets could utilize tracking and recovery techruques very
similar to those now in use for the i r arth orbit recovaries
A south to north re-entry corridor similar to that presently used by
the Soviets i11 assumed or the returning vehicle hw middot 1~ thi~
corridor is also dependent on the original launch CJiuuth the
number of guidance corrections made through the flig~~t and
the accuracy of theae corrections The uslt- of the srmiddotmiddot p r-ntry
corridor would provide the Soviets with versatility throuh ~hirmiddot
17
SECREf AFMDG amp3-377Z
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 25
_---~-middotmiddot middot- middotmiddot------- -~ -middotmiddotmiddotmiddotmiddot ~ middot middot- middot--- middotmiddot___~ --~ middot__-- -- -middot middot-middotmiddot
SECRET ship~baiied tracking network and would therefore not necessitate
a worldwide fixed land tracking network as is planned I or US
programs k8)
Minimum requirements for a Soviet recovery range
command and control system include the establishment of a
recovery control center three or more beacon tracking stations
search aircraft staging areas and recovery forces stagig areas
The recovery range control center will probably control the entire
recovery operation under the auspices of the central mission
control and apace track center Jrf
The recovery lange control center should be
located in cloiie proximity to the planned impact area maintaining
contact with the rnis sian control center and lts subordinate i
I recovery forces on secure HF UHF or VHF communications
liriks cent
Initial impact predictions and cal ulations would
probably be forwarded rom the central mission control and
spacetrack center to the recovery phase of opcr-ti-bullbull1 The
recovery range controller would then dispatch ant ontrol search
aircraft via radio communications channels Sinntaneously the
recovery range controller would receive real-tim( middot -ota on the downed
vehicle frorn recovery range associated beacon trltocklmiddotmiddot g stltions
18
SECREf AFMDC 63-377Z
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 26
~-middot-~~~middotmiddot___ middot~middot~-~~~middot~- ~---) ~middot ~- middot -middot~ lt~~-7-~~~7r~-gt middot -~~--middot-middot-~~ middot middotmiddot _ -~~- middot_ middotmiddotmiddotmiddot ~--~~_ ~~---middot-
middot------ -- --- ---~middot-middot-middotmiddot-middotmiddotmiddot------------ middotmiddotmiddotmiddotmiddot--middot-- middot _____ __- _ -middot
SECRET These stations would provide accurate impact location information
derived from standard radio DF methods The numbc1middot of beaet)middot
tracki ng stations could be limited to chree stations alipneii to zive
accurate triangulation data The Sov iet Krug network of high-
frequency 1middotadio digtmiddotection inding stations currently located at
some twenty-six operational sites through the USSR could easily
serve this function By using this network of stations the
Soviets could cut cost on range instrumentation required anlt-- still maintain tolerable impact locatiol1 requirements m
The Krug system reportedly has a bearing
accuracy of plus or minus 1 7 degrees at extreme ranges 1 i (8000 NM) with lttccuracie s approaching one -tenth of a degree at
middot I
short ranges Existing stations located in close proximity to themiddotl i bull proposed recovery zone include Krasnodar Tbilisi Shulmiddotaabad
ALma Ata and two stations at Tashkent (Figure 5) ~
Data received from the eacll track~_g statior~ is
fed into the central mission controller for correlation with
calculated impact data and at the same time is sent to ~ e -eovery
control center which dispatches the search aircraft tc the recovery
zone This exercise could be handled 011 normal two-ltay HF or
UHF communications links (Figure 6 18
19
-SECREr AFMDC 63-3772
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 27
middotmiddot middot- middot----- -middot- middot--middotmiddotmiddotmiddotmiddot- -- __ __ ____ _ - -shy-- -- middot- middot middot middot- middotmiddotmiddot-middot --~---middotmiddotmiddotmiddotmiddot middot middot middot -
Fig 5 ~ Krug S1tcs
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 28
- - - - -middot bullmiddotmiddotmiddotmiddot -
-- ---- -middot-middotmiddot - ~ -middot ~ -~ middot middot--middot -~- middotmiddotmiddotmiddot- --middot-middot- middotmiddotmiddot- -middot
SECRET
RECOVERY RANGE CONTFltOL
( INTR - ~ -~
FIG 6 (U) RECOVERY TRACKING NETWO K
21
SECRET
AFMOC 63-3772-SECREtshy
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 29
~ middot-middot -~-- -- middot-~middot- - middot- middotmiddot middot -- -~-- -middot _ __ ~-- -middot _ __ -~ middot middotmiddot middot middotmiddotmiddotmiddot - -
-SESREfshy(2 Lifting Re-Eltry Vehicle_
For a relatively high lift (LID ) I) lunar re-entry
vehicle the equipment requirements increase substantially for
both orbital corridor stations and the recovery site Continuous
tracking will be required from the deboost point to the impact
site which wi ll normally result in an initial need for at least
eight tracking stations along the orbital corridor This arrangeshy
ment will provide continuous tracking from deboost to landing
ln the recovery area the probable instrumentation requirements
include C and S band radaramp radio D F equipment airborne
radars precision doppler radars for velocity measurement)
mobile ground radars (for immediate off -range coverage) angle
and distance measuring equipment tracking telescopes and
ballistic cameras Absolute minimum instrumentation requireshy
ments ior recovery puTposes are a tracking and acquisition radar
and radio D F equipment however~ thbulls situaL-1 whiJe -imp1e
and economical is an extremely rough approach to a very sophistishy
cated problem Safety considera~ions and the de~ middot oe tc obtain
refined and accurate mission information will rr-st probably
dictate the use of the greater equipment requir-eroents postulated
above if the litins re-entry vehicle i s actually utized by either
the IJS or the Soviets JS
SECRET AFMDC b3-377Z
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 30
middotmiddotshy middot middot---- -middot _____ __ ___ __ - ___
g Search and Recovery Techn iqu~
Although the search and recov -ry techniques currently being
used by the Soviets are unknown it has been established that the
most effective recovery methods itlclude th~ use of search aircraft
for vehicle location combined with helicopter or ground mobile
systems or physical recovery Proposals for the US Apollo
program include the combined use of these vehicles during the
recovery exercisa bull
The number of aircraft involved in the search activity is
dependent upon the precalculated impact accuTacy of the re-entry
vehicle To minirnize the number of aircraft required for search
operations the ralge would probably be divided into search
sector with the bulk of the aircraft deployed in the primary
precalculated impact zone This zone could then be broken down
into seiirch sectors employing one or more aircraft per secto-r
depepdent on the size of tce O-~a tcgt ~ co rerd middotn_ bull bull ~ge
control center woulC naintain constant voice communications dith
the search forces and provide all vector information (lf
Once the spacecraft was sighted the geographic coordinates
could be forwarded to the recovery range controller who in turn
would dispatch the physical recovery vehicles to th~ impact site
Pickup of the re-entry vehicle would probably be arried out by
Z3
-sECRET AFMDC )3-3772
i i
-middot I
1 i
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 31
---middot-middotmiddotmiddotmiddot bull bullbullbullbull- -- _ ___ bull bullbullbull middot-bull - r-o _ middot---~~ - --- -4-middot --- middot-~middot-middot middot middot-middot-shy- shy __
SECRET conventional means dependent on its physical charac teristics
and then transported to a predete1middotmi ned checkout or transh i pment
a r ea (U)
Since this method is adequate and yet employs nothing more
than atanda1middotd search techniques it may be assumed that the Soviets
would use equal s implicity in a planned lunar recovery mission
Figure 7) )8f
24
SECREt AFMDC 63-3n
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 32
middot-middotmiddot middotmiddot-middot middot-- --middot--middotmiddot-middotmiddotmiddotmiddotmiddotmiddot-middot--middotmiddotmiddotmiddotbull ~ - bull-middotmiddot ~
SECRET
middot
FlG 7 (U) SEARCH RECOVERY NETWORK
-shyRV I BEACON
TRACKING j
STATION
--
1
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 33
middot- middot _ --middot-middotmiddotmiddotmiddot-middot--~ ~~ middotmiddot -middot--middotmiddot --middot -- -middotmiddotmiddot middot - -~middot --- middotmiddot
SECRET SECTION IlL
~MODEL OF USSR LUNAR RECOVERY RANGE
The proposed lunar recovery range outlined in this section
includes those areas of the USSR which best it US standard
recovery range site selection criteria The earth orbit recovery
lt~-reas currently being used by the Soviets fit well within the
proposed boundaries of tte lunar recovery range and could continue
to be used dependent on the external constraints o the chosen
lunar mission and its re-entry vehicle characteri11tics It should
be remembered however that these are limiting site selection
factors and the area proposed is made with no knowledge of USSR
lunar recovery mission technology m The broad boundaries of the proposed recovery range include
i
appears to include the largest number of logistic support areas
Althoughmiddot this area is believed to be the met uitable poundor the
recovery of a semi -ballistic type re-entry vehicle the entire
area still presents good possibility Utilization of more aoltltherly
sectors of the proposed range would suggest the uG~ of a high lift
Zb
AFMDC 63-377Z
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 34
______ middot-middot---middotmiddot - -middotmiddot ------ bull -- -~ -M bull o- --------middot -middot ---- - middot -middot-- middotmiddot -~ - middot ----shy
SECRET vehicle or the construction of logist ic support bases designed
specifically for the suppor t of a lunar program Pltgtst Soviet
philosophy suggests that maximum usc will be made of existing
facilities or such a ptmiddotogram rather than the development of an
~ntirely new range lpound1
Figure 8 includes the primary secondary and tertiary
landing areas which would p r obably be used by the Soviets in a
programmed lunar return mission J8f Figure 9 illustrates a functional lunar recovery miaion
control network which could be used aasuming a semi -balli stic
re-entry vehicle This diagram incorporates control techniques
which are proposed for the US lunar recovery program and
includes c e rtain Soviet conunand and control technique5 which are
believed to be used in current earth orbit operations )IS1
Z7
SECREf AFMDC b3-3772
1
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 35
-middotmiddot- --middotmiddotmiddotmiddotmiddotmiddot middotmiddot--middot middot-- middot middot ~ middotmiddot-
-~
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
shy - bull middot --shy bull bull bull - ( bull bull
bull bull ~ bullbullbull middotmiddotmiddot bull bull middot _middot_ _middot ___ bullbull~r middotshy bull bull bull bullbull bullbullbull _middot
-
-
_
) middotmiddot
~~--middot
middot __
-
-middotmiddot~ middot middot~
middot
_- -
- -
RIO GRANDE
AREA MAP SHOWING LOCA110N OF AFMDG
Page 36
-middot- - ------- - - -~
I I I I
I i
FIG 9 (U) MISSION CONTROL NETWOPO SEGRE=
AFMCC 63-3772
SECREf
- _ - --middot--middot _
SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
- ~middotmiddot------ bull bullbullbullbullmiddotbullbull- bullmiddotbullbull middot____ _ bullwbull+ - -bull-bullbullbull ___ __ middotmiddot-middot ---middot- _____ ~ bullmiddot bull-middot- bull bull bull- bull
shy
SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
- --
--middotmiddot- ____ ----------~-----~-middot _____ - _____ middot -middot-~
Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
01-0Z 03-04 05-09 10-11 12-13 14-15 16-17 18-19 20-21 22-23 24-ZS Z6-27 28-29 30-31 32-33 34-35
-36 37
__ - w~c o3-3772
-middotshybull bull
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SfOOH (U ) BrBLLOGRAPHY
l Caldwell D M Jr and Dunlap E W Recovery of a Lunar Re-Entry Vehicle at a Prto-Selected Landing Site Ai r Force Flight Test Center Edward s AFB Ca lifornia Technical Documentary Report 62 -18 SeptEo cmiddotnber 1962 (Unclassified
2 Eggleston John M and Young John W Trajectory Control for Vehides Entering the Earths Atmosphere at Small Flight-Path Angles NASA Technical Report R-89 (Unclassified)
3 Foudriat E C Study of the Use of a Terminal Controller Technique for Re-Entry Guidance of a Capsule Type Vehicle NASA Technical Note D-BZB (Unclassified)
4 Henry 1 G SR 192 -Strategic Lunar System- Volume Vli (Trajectory Studies) Aerojet General Corporamption Final Report 1741 (Seeret)
5 Jensen Townetend Kork Kraft Design Guide to Orbital F light McGraw-Hi ll Book Company Inc (Unclassified)
6 Wong T J and Slye R E The Efect of Lift on Etry Corridor Depth and Guidance Requirements for the Return Lunar F_ight NASA Technical Report R-80 (Unclaampsified
7 Apollo Systems Study Mid - Term Review GeneTal Electric March i 91middot DIN 2388 middot-09-0 (Co fiditiliall
amp L tlmiddotum~nta~iv- Guidance and Navigation for Soviet AeroshySJace Vehicl~~ FTD-TlS -EL-61-63 (Sccl et) bull
9 Krug HFDF has Multiple High Priority_~~icm~ May Provide Navigational Fixes fo1middot SLRA Weekly Intelligence Review NORAD Issue Nr 2762 (Sectctl middot
10 Lunar Expedition Plan Headquarters Space Systems Division AFSC Lunex WDLAR-S-458 (Seebullet)
liFMDC b3-377Z
11
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SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
~i~~_-tD12 Space Vehicle Recovery Control Syst~
Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
31
SECRET AFMDC 63-3772
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FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
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DISTRIBUTION
OPR
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SECRET 0 L-g )_L 11 Soviet Launch Faciht1es FTD TWPshy
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Company Waltham 54 Massachusett
13 Space Vehicle Recovery Get1e1middotal Eleo Communications Department Santa B 63 SPC -1 (Unclassified)
14 SR-192 Strategic Lunar Systems Studmiddot Aircraft Corporation Report Nr 0700~
f3ee1 et)
15 SR-192 Strategic Lunar System Aerojet General Corporashytion Special Report Nr 1779 (See etl
16 The US Planetary EX1oration Program JPL May 1961 Technical Report Nr 3~-84 (Seex et)
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SECRET AFMDC 63-3772
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Organization
FTD FTD FTD AFSC BSD SSD ASIO ESD AMD RADC AFWL AFFTC AFMTC APGC AEDC RTD AFMDG
lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
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lt AFMDG
DISTRIBUTION
OPR
TDFS TOES TDBDP SCFD BSF SSF ASF ESY AMF RAY WLF FTY MTW PGF AEY RTGS MDO MDNH
Copy Nr
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