NASA CONTRACTOR REPORT b b 0 (0 v4 N65-28735 UCCTSSION NUMBER1 a NASA CR-61077 < -A CR OR rnx OR AD NUUIIIER) DESIGN STUDY OF SPECIAL PURPOSE SYSTEMS FOR THE LUNAR SURFACE GPO PRICE $ Prepared Under Contract NAS8-5307 by P. J. Adinolfi CFSTI PRICE(S) $ F. A. Heinz, Jr. Hard COPY (HC) Microfiche (M F) HAYES INTERNATIONAL CORPORATION Missile and Space Support Division ff 653 July 65 i NASA - GEORGE C. MARSHALL SPACE FLIGHT CENTER Huntsville, Alabama April 30, 1965 https://ntrs.nasa.gov/search.jsp?R=19650019134 2020-07-08T16:25:58+00:00Z
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N A S A C O N T R A C T O R R E P O R T
b b 0
(0 v4
N65-28735 UCCTSSION NUMBER1
a
NASA CR-61077
< -A CR OR rnx OR AD NUUIIIER)
D E S I G N S T U D Y O F S P E C I A L P U R P O S E S Y S T E M S FOR T H E L U N A R S U R F A C E
GPO PRICE $ Prepa red Under Contract NAS8-5307 by
P. J. Adinolfi CFSTI PRICE(S) $
F. A. Heinz, Jr. Hard COPY (HC)
Microfiche (M F) HAYES INTERNATIONAL CORPORATION Missile and Space Support Division
t DESIGN STUDY OF SPECIAL PURPOSE SYSTEMS FOR THE LUNAR SURFACE
BY
P. J. Adinolf i and F. A. Heinc, Jr.
ABSTRACT
This r epor t d e a l s with spec ia l purpose equipment t h a t w i l l be requi red t o
support lunar sur face opera t ions with emphasis on the 1969 t o 1975 t i m e per iod.
Spec ia l purpose equipment as used here p e r t a i n s t o i t e m s such as t o o l s ; small
wagon-like veh ic l e s ; po r t ab le s h e l t e r s and s h i e l d s ; emergency devices ; etc.
Their purpose is t o complement the s c i e n t i f i c equipment and o the r s y s t e m s ,
s p e c i f i c a l l y LSSM, MFS, MOLAB and LEM s h e l t e r .
t
The pa t t e rn of t he s tudy was t o analyze t h e missions t o determine t h e
support opera t ion and t a sks which needed t o be performed, then t o p l o t c h a r t s
of t a sks versus equipment. Based on these equipment requirements, conceptual
des igns were derived. The ob jec t ive was t o provide a l imi t ed number of mult i -
purpose devices which would rep lace the many i t e m s of equipment l i s t e d on t h e
cha r t s . These multi-purpose devices and t h e i r app l i ca t ions are descr ibed i n
the repor t .
s i o n is a l s o considered.
fi *:
: The u t i l i z a t i o n of ex i s t ing lunar equipment by rework and conver-
4
The conceptual designs and o the r i t e m s of s p e c i a l s i p p o r t eqiiipment a r e
r e l a t e d t o t h e var ioi is lunar mission phases, i.e., LEM, AES, and semipermanent
base establ ishment .
4
NASA CR-61077
c DESIGN STUDY OF SPECIAL PURPOSE SYSTEMS
FOR THE LUNAR SURFACE * i BY
P. J. Adinolfi F. A. Heinz, Jr.
Prepared Under Contract NAS8-5307 by HAYES INTERNATIONAL CORPORATION
Huntsville, Alabama
For
Propulsion and Vehicle Engineering Laboratory
Distribution of this report is provided in the interest of information exchange. Responsibility for the contents resides in the author or organization that prepared it.
NASA-GEORGE C. MARSHALL SPACE FLIGHT CENTER
PREFACE
This report was prepared by Hayes International Corporation, Apollo Logistics
Support Group, Huntsville, Alabama, for the Base Development Group, R-P&VE-AB,
George C. Marshall Space Flight Center, under the authorization of Task Order H-34,
Contract NAS8-5307.
The NASA Technical Representatives were Mr. J. Rains and Mr. C. Darwin,
R-P&VE -AB.
Illustrations for this study were prepared by M r . K.D. Renfro, and
the sketches, and Appendix A were prepared by M r . Love, NASA, R-P&VE-ABT.
FIGURE 1 - Estimated Schedule - Manned Lunar Exploration and Base Development FIGURE 2 - Equipment Versus Tasks - LEM FIGURE 3 - Equipment Versus-Tasks - AES FIGURE 4 - Equipment Versus Tasks - Semi-permanent Base FIGURE 5 - Special Purpose Equipment Proposed for the Various Missions FIGURE 6 - Utility Belt
(5.8 feet) long, and weighs 12.2 kilograms (27 pounds). The shield segments
are formed from 1.27 millimeter (0.050 in.) aluminum sheet (2219T87) and will
fold into a package whose size is 39.6 X 91.4 X 94.5 centimeters (1.3 X 3.0
X 3.1 feet), as is shown by the cross-hatched section.
Another configuration is shown in Figure 31. This shield is extended
around the astronaut while he is in the seated position. The cross section of
wall shows an outside thickness of 1.52 millimeter (0.060 in.) aluminum, an
insulating material thickness of 10.7 millimeters (0.42 in.), and an internal
wall thickness of aluminum of 0.51 millimeters (0.02 in.). This package will
be 24.2 kilograms (53.2 pounds) earth weight, and 4.0 kilograms (8.8 pounds)
lunar weight. The expanded size will be 0.91 meters (3 feet) in diameter, and
1.07 meters (3.5 feet) high. The collapsed shield, a s shown in Figure 31, will
be J-shaped with a size of 0.46 X 1.07 X 0.49 meters (1.5 X 3.5 X 1.6 feet). . The two shields, when partially extended, can be mounted on the MULE, the
man-powered tricycle, or other vehicles for protection while traversing the
lunar surface. During blasting operations, the shields could be used to
28
p r o t e c t t h e a s t r o n a u t s a s W e l l a s equipment . i n t h e v i c i n i t y from f l y i n g d e b r i s
and dus t .
The Travois, a l s o , when turned upside d m w i l l provide a s h i e l d a g a i n s t
micrometeoroid storms f o r one man i n a prone o r s ea t ed pos i t i on .
t fon is i l l u s t r a t i d in Figure 19.
This app l i ca -
3.4 MISCELLANEOUS EQUIPMENT
3.4.1 MARKER POLES
Marker poles were i n i t i a l l y conceived f o r t r a i l and si te marking i n t h e
event t h e lunar s u r f a c e is covered by a r e l a t i v e l y deep dus t layer .
could also be used t o support f lood l i g h t s , antennas, power and/or communica-
t i o n l i nes . I n t h i s case, a heavier po le would be requi red .
are proposed-for compactness i n s to rage and t r anspor t ing .
po le a r e presented.
They
Telescoping po le s
Two ver s ions of t h e
The f i r s t is a very l ight-weight (magnesium) p o l e 1.9 cen t ime te r s (3 /4 in . )
i n diameter by 1.53 meters (5 f e e t ) long, which would extend t o a he igh t of 4.9
meters (16 f e e t ) above t h e sur face . It would weigh 0.366 kilograms (0.8 pounds)
and would be manually emplaced.
- 1.
A l a r g e r ve r s ion is shown i n Figure 32, and would have g r e a t e r s t r u c t u r a l
capac i ty . It is 7.6 cen t ime te r s (3 inches) i n diameter by 1.9 meters (6% f e e t )
long and would t e l e scope t o a height of 4.6 meters (15 f e e t ) above t h e sur face .
29
Its weight is 2.46 kilograms (5 ,42 lbs).
an explosive cartridge which would drive the 0.6 meter (2 feet) spike into the
lunar surface. In the case of a very hard surface, small shape charges could
be used to form the emplacement holes.
such as trail and instrumentation sites mafking,are depicted in Figure 33.
The'lines strung between the poles provide power for lights, instruments, and
battery recharging.
It would be emplaced by activating
Some typical marker pole applications,
A switch in the pole light circuit at the shelter would
allow visual signalling with the lights.
be as a telephone circuit.
tions or would be a back-up system.
An alternate use for the line would
This would reduce the power required for communica-
3.4.2 UTILITY ROCKETS
Small missiles or projectiles could perform many useful functions, parti-
Some of the obvious uses cularly for emergency or back-up modes of operation.
are as signaling devices and quick delivery of written messages or small
articles such as tools, medical supplies, or lunar samples. Other applications
will be enumerated below.
The two most likely methods of propelling the projectiles are the use of
rockets or firing from guns.
rockets are favored because the infrequent use of these devices would not
warrant the development cost nor delivery weight of gun type launchers.
other uses for a gun-type launcher could be shown, such as for drilling or
riveting, then the gun should be reconsidered.
Each method has certain advantages; however,
If
30
Figure 34 typifies a missile configuration. The sectims are integral,
interchangeable modules so that the building block technique can be used to
achieve the appropriate assembled configuration for a given application.
example, a signal missile would be composed of:
For
1. A spiked-nose section for stand-off from the surface upon impact.
2. A payload section consisting of a prepackaged pyrotechnic or
pressurized, colored gas display which would be released during
flight along the trajectory and continue to eject upward for a
period after impact.
Besides the visual signal, an audible signal in the form of a radio beeper or
tone from a small transmitter in the missile would alert the astronaut on the
receiving end to look for the visual signal.
Since the signal missile could be used because the receiving astronauts’
radio receiver was out, he also would not hear the missile-transmitted signal.
Therefore, a better audible (vibration) signal would be the detonation of a
small explosive charge in the spike tip just after the spike penetrates the
lunar surface upon impact. This method of alerting the man to look for the
visual signal would depend on the propagation characteristics of the lunar
surface.
Various sized rockets could be used depending on the application. A
typical rocket would be 1z08 centimeters (5 inches) in diameter by one meter
(39 inches) long.
the length and would weigh about 10 kilograms (22 pounds) of which 7.4 kilo-
grams (16 pounds) would be solid propellant fuel. The weight of the forward
The rocket motor and nozzle would account for about half
31
s e c t i o n s would b e 0.73 kilograms (1.6 pounds) depending on t h e conf igu ra t ion
being app l i ed p lus any added cargo weight.
Propulsion would produce around 45 kilograms (100 pounds) of t h r u s t f o r
several seconds. V e l o c i t i e s i n t h e reg ion of 152 t o 305 meters/second (500 t o
1000 feet /second) would be a t t a i n e d wi th t h e range depending on t h e launch
angle.
rocke t p r i o r t o launch as a ' cons ide ra t ion f o r s t a b i l i z i n g t h e missi le during
f l i g h t .
A s i m p l e tube o r r a i l - t y p e launcher would be used wi th spin-up of t h e
F igure 35 d e p i c t s var ious a p p l i c a t i o n s for. u t i l i t y rocke ts . The -simpler
ve r s ions would use only t h e i n i t i a l po in t ing azimuth and e l e v a t i o n angle f o r
achiev ing the des i r ed range and d i r ec t ion .
ploy w i r e o r radar guidance with j e t vane o r f l u i d i n j e c t i o n s t e e r i n g devices .
More complex ve r s ions could em-
3.4.3 ANTENNA
An app l i cab le e x i s t i n g antenna m a s t design which can be used on t h e lunar
s u r f a c e weighs 29.1 kilograms (65 pounds) and extends t o a he igh t of 22.86
meters (75 f e e t ) .
e r ec t ed by two men i n a s h o r t t i m e . 8
and t h e assembled m a s t arrangement.
t u b u l a r mast p l u s n ine mast guy-wire cables .
i s depic ted , o the r devices may be s u b s t i t u t e d .
This antenna has been designed f o r t h e Army and can be
Figure 46 d e p i c t s t h e e r e c t i o n method
There a re f i f t e e n s e c t i o n s t o t h e
Although a pa rabo l i c antenna
32
3.5 CONVERSION AND UTILIZATION OF EXISTING LUNAR EQUIPMENT
3.5.1 TRAILERS
Trailers can be f a b r i c a t e d from t h e abandoned descent s t a g e i n t e r n a l
supe r s t ruc tu re , tankage-xnd p ip ing; A module of t h i s desc r ip t ion i s shown i n
F igu re 36. The large, cy l ind r$ca l , hemispherical-ended tanks are u t i l i z e d as
wheels and are supported by a chass i s t h a t i s f a b r i c a t e d from t h e supers t ruc-
t u r e o r t h e i n t e r n a l brac ing members of t h e abandoned LEM-Truck. To complete
t h e u n i t , i t i s necessary t o add jack s h a f t s , wheel support and a t r a i l e r
h i t c h .
need. The modules can be towed by a MOLAB, LSSM, o r o t h e r veh ic l e s .
Trailers wi th e i t h e r 3 o r 4 wheels can be assembled, depending on t h e
The t ra i lers w i l l have many uses such as hau l ing l a r g e s e c t i o n s of w a l l s
f o r shelters, replacement tanks , engines, antennas, r a d i a t o r s , and o t h e r
supe r s t ruc tu res .
3.5.2 SHELTERS
A f t e r landing, t h e abandoned LEM-Truck, as shown i n F igu re 3 7 , can be
revamped f o r u t i l i z a t i o n as a d i f f e r e n t type of module. The descent s t a g e
can be disassembled by f i r s t removing a l l p ip ing and the tankage, then t h e
inne r v e r t i c a l w a l l s ec t ions . Tools needed i n t h e disassembly process are an
e lectr ic a r c - c u t t i n g t o o l , an electric o r battery-powered saber s a w , a manual
s a w , and poss ib ly a b o l t remover. The i n t e r n a l descent engine, tankage, p ip-
ing , and hardware w i l l be set a s i d e i n a p ro tec t ed a r e a o r enc losure f o r re- -
usage a t a l a t e r da te . A s w i l l be shown, almost a l l of t h e components w i l l be
u t i l i z e d .
33 e
Figure 38, t h e modified LEM-Truck, shows a design t h a t may be incorpora ted
i n t o t h e e a r l y LEM-Trucks, o r l a te r , t h e i n i t i a l lunar landings. This des ign ,
i f i n s t i t u t e d before o r dur ing t h e f a b r i c a t i o n of t h e 20 "Lunar Bugs11 which
NASA has under con t r ac t , would s impl i fy t h e u t i l i z a t i o n of t h e g r e a t e s t p a r t
of t h e Moon-Landing Veh ic l e ' s payload. Figures 38, 39, and 40 show a hinge and
hinge-pin design which have been added t o t h e 12 j o i n t s of t h e LEM-Truck.
The descent engine can be removed and set as ide .
manually o r by remote c o n t r o l ; t h e p ins w i l l be used f o r l e v e r s and o the r
purposes. The e igh t i n t e r n a l wall pane ls can then be swung toward the ou te r
w a l l s and locked i n t o pos i t i on .
provide add i t iona l mass f o r more r a d i a t i o n and me teo r i t e p ro tec t ion .
The hinge-pins can be removed
This new dual e x t e r i o r w a l l t h i ckness w i l l
A phys ica l f a c i l i t y module is shown i n Figure 4. This design is accom-
p l i shed by t h e add i t ion of a dome l i n e r and base p l a t e t o t h e modified LEM-
Truck.
f l o o r may be made of a honeycomb wal l s e c t i o n wi th the proper i n s u l a t i o n bonded
t o it. The design can a l s o inc lude such f e a t u r e s as environmental c o n t r o l and
i n g r e s s l e g r e s s provis ions.
The roof s e c t i o n s may be of a double th ickness c ros s - sec t ion and t h e
S imi l a r ly , f a c i l i t i e s f o r an astronomical observatory, medical, and TV
s t a t i o n can be constructed.
s t r u c t u r e i n t o a modified LEM-Truck s h e l l , t h e module can be converted i n t o
a u s e f u l system, a s shown i n Figure 42.
of a c o l l a p s i b l e v e r t i c a l wa l l , a f l o o r s e c t i o n , and a top.
t r anspa ren t o r an opaque s h e l l with a s m a l l observa t ion b l i s t e r .
f o r t h e environmental c o n t r o l system and power supply can be made through an
By i n s e r t i n g a p re s su r i zed bladder-wal l type
The p res su r i zed enc losure w i l l c o n s i s t
The top may be
Connections
3 4
interface panel located on the vertical face of the LEM-Truck.
solar cells may be added at any convenient location.
Radiators and
Further studies show that by redesigning the LEM-Truck with all pin
joints, many different-sized enclosures may be fabricated. One in particular,
called a Dodecagon Shelter, is shown in Figure 4 3 . In order to fabricate such
a shelter, it is necessary that two or more lunar missions be performed to
land LEM-Trucks in or near a predetermined, designated area. These abandoned
LEM-Trucks can be partially disassembled for the purpose of refabricating them
into shelters. The tankage again can be stored for future usage with other
components. By removing several of the pins at the pin-joints, various sizes
and various-sided (Figure 4 4 ) shelters or modules can be assembled. During
the AES missions, additional equipment and superstructures can be delivered
for the purpose of completing the shelter module.
(panels) can be made from the internal structure of the LEM-Truck.
and floor of the shelter can be fabricated from superstructure panels.
floor then is reinforced with support trusses.
to the multipurpose shelter, an airlock and hatch door are installed at the
bottom of the shelter.
types of radiation, micrometeoroids, and extremes of lunar temperature can be
provided by piling lunar surface material around the shelter.
Upper and lower side walls
The roof
The
To provide ingress and egress
After assembly of the shelter, protection from all
3 . 5 . 3 ANTENNAS
Lunar antennas can be erected and assembled from the legs (landing gear)
of the LEM-Truck descent stage. The hinge-pins can be removed from the pin
35
j o i n t s which w i l l a l low the l egs t o be assembled i n a t r i p o d (LAR) as shown
i n F igure 45. This arrangement a l lows f o r a t r i a n g u l a r a r e a a t t h e c e n t e r
from which the antenna mast i s extended upward. The m a s t can be made of t h in -
wal led metal tubing and assembled i n a te lescoping design. A s t h e m a s t i s
r a i s e d , the sec t ions w i l l be bo l t ed o r w i l l au tomat ica l ly lock i n t o p l ace by
t h e u s e of a b a l l de ten t lock design. The pa rabo l i c antenna and mast w i l l be
de l ive red t o the luna r su r face v i a one of the miss ions . Mast concept design
could be s i m i l a r t o t h a t used i n t h e s t a t e - o f - t h e - a r t as shown i n F igu re 4 6 .
36
4.0 SUMMARY AND CONCLUSIONS
.
I .
This study w a s r a t h e r broad i n scope with numerous and d i v e r s e a r e a s
a v a i l a b l e f o r e x p l o i t a t i o n . Consequently, it was not p o s s i b l e t o i n v e s t i g a t e
and develop f u l l y a l l of t h e p o t e n t i a l s a f fo rded by t h e sub- task scope wi th in
t h e t i m e allowed. One of t h e problems w a s t h a t of s e l e c t i n g and l i m i t i n g t h e
coverage so t h a t some of t h e more promising r e s u l t s could be presented.
The study ind ica t ed t h a t many menial o r r o u t i n e types of t a s k s w i l l be
necessary t o support t h e var ious major t a s k s and could r e q u i r e a v a r i e t y of
d i f f e r e n t equipment f o r accomplishing them. Fur ther , t h e na tu re of t h e luna r
s u r f a c e w i l l i n f luence t h e types, q u a n t i t i e s , a n d d e t a i l e d design of t h e s p e c i a l
purpose equipment t h a t w i l l be needed. The number of d i f f e r e n t items can be
reduced by des igning items of equipment t h a t perform m u l t i p l e func t ions .
same philosophy should be extended t o a l l m a t e r i a l t o be de l ive red t o t h e
luna r sur face .
This
Generally, s p e c i a l purpose equipment w i l l be small i n s i z e and q u a n t i t y
f o r t h e e a r l y manned lunar missions and w i l l become p rogres s ive ly l a r g e r and
more numerous f o r t h e subsequent mission phases.
s u r f a c e bases w i l l be developed, as well a s t h e environment, w i l l have a g r e a t
in f luence .
The e x t e n t t o which lunar
37
5.0 RECOMMENDATIONS
1. The more promising conceptual designs that have resulted from this study
should be carried on through detailed analysis and design, mockup and
prototype hardware, testing, and evaluation stages of development.
2 . This study should be continued, or subdivided into several studies, to
obtain a more detailed analysis of the various mission requirements and
concepts of special multipurpose equipment.
studies are:
Some examples of additional
a. Studies and evaluations should be made on vehicles smaller than the
LSSM, such as the Travois, MULE, tricycle, etc. Considerations for
maximum utility, type of power, steering, adaptations, environment,
etc., should be investigated more completely.
b. Further studies should be' conducted on the inf latable/extendable
structures, cabins, and shields for emergency uses. Also, their
application to conversion of existing vehicles, shelters, and other
lunar equipment should be explored more fully.
c. Redesign of the LEM Truck should be considered f o r the purpose of
shelter utilization. All lunar equipment designs should be reviewed
from the standpoint of serving multiple functions as is o r by subsequent
modifications.
38
d. Additional studies on the types and applications of tools should be
conducted. The need for power tools versus hand tools and the type of
power to be used should be considered. Investigation of the frequency
of use would form the basis for determining this, as well as the quantity
and detailed design of a given type of tool.
e. Interface studies are required for determining the package envelope
availability, tie-down, deployment and other aspects of physical and
functional compatibility with existing and planned designs for other
equipment. This is especially true of the Travois, expandable shelters,
and other large items of equipment which have been presented in this
study.
3 . The studies should have continuing effort applied or be periodically review-
ed and revised to reflect changes in mission operations, other equipment
designs, and information on the nature of the lunar surface.
39
ILLUSTRATIONS
41
ii M
M
ct
I Q l-
€ h h
I I
u H F
42
SITE ESTABLISHM' I
\ I Shove 1 X I 1 '
I
Wheelbarrow x - , I 1 Broom + : ,
\ Y
S 1 ing Sheet Panels Marker Poles Lever Jack Auger P i ck /Hame r Exp lo s ive s Rocket Deployable Covers Hack Saw Wagon
- / i 1
. .
x
._
EXPLORATION lONSTRUCTIO1 EMERGENCIES
- t- 77
I ' X i I x a
X
FIGURE 2 - EQUIPMENT VERSUS TASKS - LEM
43
AES
SCIENTIFIC SITE ESTABLISIM ' T
m \ 1L y EQUl PMENT
scoop Push Broom Sheet Panels Marker Poles R=P Lif t /Hoist Lever / Jack Pathfinder Wire Auger Shove 1 Pick Explosives Trailer Rocket Power Vehicle T rans i t /Telescope Ladder Cord Grapple Bridge Lights Deployable Covers Sledge S takes /Rods Shield I n f l a t a b l e Cabins Fasteners Sheet Metal Hack Saw Welder Patch Kit Hand Tools D r i l l Mu1 t ime ter Camera Containers
EXPLORATION
1 -+ --
EMERGENCISS
FIGURE 3 - EQUIPMENT VERSUS TASKS - AES 44
SEMI-PERMANENT BASE
\
EQU I T r a n s i t Dozer Ro 1 ler Poles Wires /Reels D r i l l S h u t t l e Car Rover Expan. S t ruc tu res Digger Beacons Antennas Flood1 i g h t s Welderlcutter Inf l a t. Cabins Tubing/Fi t t ing Explosives Power Shovel Trac tor T r a i l e r Fork L i f t Dredge Furnace Chemicals He ta l l . I n s t r . Hand Tools Power Tools Fa 8 tener 8
Spare P a r t s Converter Ai r locks U t i l i t y Rockets
FIGURE 4 - EQUIPMENT VERSUS TASKS - SEMI-PERMANENT BASE
45
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i!
3 U
!i u
9) & s \ a & 0 U
is E; rl
6 0
A U rl rl 4
A U 4 rl rl
rl cd
rl rn El
.. m 0 u
0) 8 i2
A 2
46
47
3 4 il 9'
n 3 -4 4 -4 3 3
I
0
i l -
2 3 4
1
m ai rl
Lc Lc 0 P) U U
U cd Fo
3 d
rn d l-l .I4
aJ rn 0 a Lc 3 a I rl U d
; 0 d &I u V 0) d a d
0 a 0 d U P m a J U O F c c d o a
n
I- v) W e
v) J 0 0 I-
W 0
v)
o
I- o w J W
v
a e
- a
W J
4 I-
0 QI
m
a
48
P i c k
\ \ \
5. AdapterIExtension Shaft
(Various Lengths)
ATTACHMENTS
Hand le d;. 2. Dr i 11 /Auger
3. Chisel 8 A 1 . \\ Tamper
FIGURE 8 LUNAR COMBINATION HANDTOOIJ
49
i
I Crank Arm/Extension Shaft
Brapp 1 ing
kl Post Hole Digger
Hook
F ' i l E PAR EL
HAYES I N S
LUNAR COMBINATION HAND TOOL FIGURE 9
50
Handle
Pick
Spade
Drill/Awer
FIGURE 10
LUNAR COMBINATION HAND TOOL
51
I .
*
.
c
r r
I-
d LL
52
- 2
- I
- Y
_ -
- I
- - *
d
_- t
- -n
- *
_ - ---
.
53
a W P I- 0 I
(3 a J J - c
54
m
PL W CI 2 Lr, - I I- e a
55
56
a
a
W J
a I-
0-
57
w (3 P 0
a m
c
58
-I W > 0 I v)
Q 0 0 0 v)
5 9
.
9 < n
K W
3 W
u) r
60
s
FIGURE 20 - EXTENSION LADDER 61
.
-\
-= fi \
/-
FIGURE 21 - DREDGE 62
0 H
\
63
.
Motorized Wheels
Hand or foot steerable.
vide track for stability.
U TOP V IEW
c
Seat and Harness Mount internally, or
externally on sides,
or both for increased
S l D E V I E W
MOD LIE FIGURE 23 - MULE 64
65
.
I
loot Stccrlnm
I i
FIGURE 25
66
I
67
68
P)
cc R
x o r
4 B4
r a h z w bo
r c 0 Q)
r a
69
70
n w
71
C l o s e d Po s i t ion
FIGURE 31 EXTENDABLE SHIELD
for MICROMETEORITE PROTECTION
Folded Pos i t ion
72
1.9 m (6 ' -3"
Igni t e r
Colored Spherical Reflector Electric Light or Both
4.6 m - ( 1 5 f t )
Above Surface Fully Extended
Burst Diaphragm
4
2 '
F I G U R E 32
MARKER POLE
. 1
- Lunar Surface
f'i3EFYAHE 0 uv HAYES INTERNAT
HUNTSVILLE, A IS
73
74
W W
/
a a, u G
3 & a ,
C & UP(
: g
U c (d rl 4 a a 0 k pc
t- 8 8 U
w v)
W v) 0 2
8 H w U w v)
F
I
. !
, ! I
I 1
i I
!
I ' 1
'76
U. D.M. H. /Hydrazine Tank
1 . 3 m Dia. \
\ I
7 3.937 m (155 i n >
0.76 m b m 4 ( 3 0 i n ) i n )
0.15 m
FIGURE 36
LUNAR TRAILER PREPAXED 3 y
77
a
Electrical arc cutter for removal
FIGURE 37
REMOVAL OF INNER SECTIONS OF LEM TRUCK,
FOR UTILIZATION OF FRAME
78
See detail "A"
f
FIGURE 38
MODIFIED LEM TRUCK
79
FIGURE 39
DETAIL "A" REMOVABLE ENGINE AND HOUSING
'80
Remove e n g i n e box, s e c u r e d by removable p i n s , see d e t a i l "A".
FIGURE 40 MODIFIED LEM/TRUCK
81
Elliptical dome, metal or transparent
*r / i \
uper Insulation
FIGURE 41 SOLARIUM - PHYSICAL FACILITY
82
FIGURE 42
ASTRONOMICAL OBSERVATORY
MEDICAL FACILITY/TV STATION
83
.
-- -
PREPARED BY
HAYES I NTER NATlO NAL
. I - 6.1 m @ (20'-0" 1
b Each / Existing Legs / From -~ LEM Truck /
tions
Roof (Fabricated) Observation
Bottom Panels
DODECAGON SHELTER F I G U R E 43
84
I
Storage of Fuel ECS, Tanks, Corn., Bat ter i e s , etc.
PLAN VIEW
Bottom Panel
ELEVATION VIEW
FIGURE 44
SMALL AREA STORAGE
85
.
F
PLAN
Antenna
Three
VIEW
Parabolic Radar Antenna
ELEVATION VIEW
FIGURE 45 LUNAR ANTENNA REASSEMBLED
86
87 FIGURE 46 - ANTENNA MAST
L
*-
e
APPENDIX A
POWERED VEHICLE CONFIGURATIONS
c
88
APPENDIX A
Several configuration variations of powered vehicles are represented in
the attached sketches (Figures A-1 through A-9) which were furnished by R-P&VE-
AB. one-wheeled, or track-
type vehicles; two-wheeled, side-by-side type vehicles; two-wheeled, fore-and-
aft type vehicles; three wheeled; four wheeled; and multiples of these arrange-
ments in trailer modules. In any of these vehicle design concepts, a final
These vehicles can be categoriyed in six groups:
selection would be predicated on such as vehicle weight, manueverability,
and packaging.
The last three sketches (Figure A-7, A-8, and A-9)show various types of
drive components such as wheels, powerpod, controls, switches, fasteners,
centerless wheel design, skids, hand trailer and some protective gear for the
man on the moon.
c
89
c
91
3/ 9 ’
8
.
FIGURE A - 3
92
L
FIGURE A-4
93
2 0
4l J 3
C
95
FIGURE A-6
c
OR
FOLDED
. REFERENCES
1. Scope of Work, R-P&VE-AB-65-4, January 8 , 1965.
2. I1Recomendations on Remaining Task Work", Lunar Surface - Special Purpose
Equipment Memo, March 24, 1965.
3. Evans, Maj. T. C., "Extended Lunar Exploration", presented a t 10th Annual
Meeting of AAS, May 4-7, 1964.
4. IIScope of Work, Preliminary Design Study of a Lunar Local S c i e n t i f i c
Survey Module;" NASA-MSFC, March 15, 1965.
5. Mason, R. L., W. M. McCombs, D. C. Cramblit, Engineering Lunar Model
Surface (ELMS), NASA - J. F. Kennedy, S. C. TR-83-D, Sept. 4, 1964.
6. I Cramblit , D. C., W. Merritt, Preliminary Lunar Roving Vehicle S teer ing
and S t a b i l i t y Considerations, TR-4-56-2-D, NASA - J. F. Kennedy Space
F l igh t Center, March 31, 1964.
7. IlSpace Bat te r ies" , Technology Handbook, NASA SP-5004.
C 8. "Antenna (75' Portable Army Type)", Arde, Inc., 2115 Seminole D r . S. W.,
Huntsvi l le , Ala.
9. Doughtie, James, Elements of Mechanisms, llLinkagesll, Chapter 5,
Wiley, 1954.
99
.
DISTRIBUTION
INTERNAL
DIR DEP-T R-DIR R-AERO-DIR
-S -SP (23)
R-ASTR-DIR -A (13)
-A -AB (15) -AL (5)
R-P&VE-DIR
R-RP-DIR -J (5)
R-FP-DJR R-FP (2) R-QUAL-DIR
R-COMP-DIR -RSP
-J (3)
R-ME-DIR -x *
R-TEST-DIR -I
I-DIR MS-IP MS-IL (8)
EXTERNAL
NASA Headquarters MTF Col. T. Evans MTF Maj. E. Andrews (2) MTF Capt. Bart Cambell MTF Mr. D. Beattie R-1 Dr. James B. Edson MTF William Taylor
Kennedy Space Center K-DF Mr. von Tiesenhausen
EXTERNAL
Hayes International Corporation (5) Missile and Space Support Division Huntsville, Alabama
Scientific and Technical Information Facility P. 0. Box 5700 Bethesda, Maryland Attn: NASA Representative (S-AK/RKT) (2)
Manned Spacecraft Center Houston, Texas
Mr. Gillespi, MTG John M. Eggleston C. Corington, ET-23 ( i ) William E. Stoney, ET (2) ,