N A S A C O N T R A C T O R R E P O R T

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NASA CR-61077

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.

TECHNICAL REPORT H-MOL29

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.

I ' 4 .*

TABLE OF CONTENTS

Section Title . Page

4

Y

3 . 0

i

1 . 0 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . 1

2 . 0 MISSION OUTLINE . . . . . . . . . . . . . . . . . . . . . . . 4

2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . 4 2.2 Lunar Excursion Module (LEM) . . . . . . . . . . . . . . 4

2.2.1 Site Establishment . . . . . . . . . . . . . . . . 5 2.2.2 Scientific Tasks . . . . . . . . . . . . . . . . . 5 2.2.3 Exploration . . . . . . . . . . . . . . . . . . . 6 2.2.4 Emergencies . . . . . . . . . . . . . . . . . . . 6 2.2.5 Construction . . . . . . . . . . . . . . . . . . . 6

2.3 Apollo Extension Systems (AES) . . . . . . . . . . . . . 7 2.3.1 STEM . . . . . . . . . . . . . . . . . . . . . . . 7

2.3.2 AES . . . . . . . . . . . . . . . . . . . . . . . 7

2.4 Semi-Permanent Base . . . . . . . . . . . . . . . . . . . 9 2.4.1 Facilities . . . . . . . . . . . . . . . . . . . . 9

2.4.2 Systems . . . . . . . . . . . . . . . . . . . . . 10

2.5 Permanent Base . . . . . . . . . . . . . . . . . . . . . 12

2.6 Summary . . . . . . . . . . . . . . . . . . . . . . . . . 13 CONCEPTS . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3.1 Tools . . . . . . . . . . . . . . . . . . . . . . . . . . 18 3.1.1 Small Tools and Utility Belt . . . . . . . . . . . 18 3.1.2 COMBO . . . . . . . . . . . . . . . . . . . . . . 18

3.1.3 Fork Lift . . . . . . . . . . . . . . . . . . . . 19

3.2 Vehicles . . . . . . . . . . . . . . . . . . . . . . . . 20

3.2.1 Travois . . . . . . . . . . . . . . . . . . . . . 20

iii

TABLE OF CONTENTS (Continued)

Title Page

3 . 2 . 2 MULE . . . . . . . . . . . . . . . . . . . . . . . 22

3 . 2 . 3 CAMUL . . . . . . . . . . . . . . . . . . . . . . 23

3 . 2 . 4 Man-Powered Tricycle . . . . . . . . . . . . . . . 24

3 . 3 Shelters . . . . . . . . . . . . . . . . . . . . . . . . 25

3 . 3 . 1 Inflatable Shelters . . . . . . . . . . . . . . . 25

3 . 3 . 2 Collapsible Shelters . . . . . . . . . . . . . . . 27

3 . 3 . 3 Shields . . . . . . . . . . . . . . . . . . . . . 28

3 . 4 Miscellaneous Equipment . . . . . . . . . . . . . . . . . 29

3 . 4 . 1 Marker Poles . . . . . . . . . . . . . . . . . . . 29

3 . 4 . 2 Utility Rockets . . . . . . . . . . . . . . . . . 30

3 . 4 . 3 Antenna . . . . . . . . . . . . . . . . . . . . . 32

3 . 5 Conversion and Utilization of Existing Lunar Equipment . 33

3 . 5 . 1 Trailers . . . . . . . .- . . . . . . . . . . . . . 33

3 . 5 . 2 Shelters . . . . . . . . . . . . . . . . . . . . . 33

3 . 5 . 3 Antennas . . . . . . . . . . . . . . . . . . . . . 35

4.0 SUMMARY AND CONCLUSIONS . . . . . . . . . . . . . . . . . . . 37

5 . 0 RECOMMENDATIONS . . . . . . . . . . . . . . . . . . . . . . . 38

ILLUSTRATIONS . . . . 0 4 4 f * 41

. . 0 0 .. w 8 8 APPENDIX A . POWERED VEHICLE CONFIGURATIONS REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99

L

iv

. LIST OF ILLUSTRATIONS

Figure Title

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*

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

FIGURE 7 - Portable Electric Space Tools FIGURE 8 - Lunar Combination Hand Tool FIGURE 9 - Lunar Combination Hand Tool FIGURE 10 - Lunar Combination Hand Tool FIGURE 11 - Lift FIGURE 12 - Travois FIGURE 13 - Travois FIGURE 14 - Pathfinder FIGURE 15 - Loading Ramp FIGURE 16 - Trailer FIGURE 17 - Bridge

FIGURE 18 - Travois Applications FIGURE 19 - Travois Applications FIGURE 20 - Extension Ladder

FIGURE 21 - Dredge FIGURE 22 - Travois Adapted to Fork Lift and Crane FIGURE 23 - MULE FIGURE 24 - CAMUL

V

LIST OF ILLUSTRATIONS (Continued)

Figure Title _- .

FIGURE 25 - Man-Powered Tricycle

FIGURE 26 - Inflatable Shelter Wall Section

FIGURE 27 - Two-Man Emergency Medical Tent

FIGURE 28 - Emergency Medical Tent

FIGURE 29 - Collapsible Shelters

FIGURE 30 - Extendable Shield (Buggy Type) for Micrometeorite Protection

FIGURE 3 1 - Extendable Shield for Micrometeorite Protection

FIGURE 32 - Marker Pole

FIGURE 33 - Marker Pole Application

FIGURE 3 4 - Utility Missile

FIGURE 35 - Signal Rocket Application FIGURE 3 6 - Lunar Trailer Reassembled Tanks FIGURE 37 - Removal of Inner Sections of LEM Truck, for Utilization of Frame

FIGURE 38 - Modified LEM Truck

FIGURE 39 - Detail "A" - Removable Engine and Housing FIGURE 40 - Modified LEM/Truck

FIGURE 41 - Solarium - Physical Facility

FIGURE 42 - Astronomical Observatory Medical Facility/TV Station

FIGURE 43 - Dodecagon Shelter FIGURE 44 - Small Area Storage

FIGURE 45 - Lunar Antenna Reassembled FIGURE 46 - Antenna Mast

*

vi

. 1.0 INTRODUCTION

4

This r e p o r t is i ssued i n response t o t h e NASA sub-task work s ta tement

e n t i t l e d "Design Study of Spec ia l Purpose Systems f o r t h e Lunar Surface."l

General ly , t h e work s ta tement pointed out t h e d e s i r a b i l i t y of having a v a r i e t y

of small, s p e c i a l purpose devices f o r mobi l i ty , t r a n s p o r t a t i o n , and o t h e r

s p e c i a l jobs, such as emergency s h e l t e r s , to be used as a i d s i n lunar s u r f a c e

base development.

The purpose of t h e sub-task is t o o u t l i n e t h e range of p o t e n t i a l requi re -

ments f o r s p e c i a l equipment, conceptually o u t l i n e some genera l approaches f o r

providing t h e s e systems, and t o def ine how t h e more promising of t h e s e devices

f i t s w i t h i n t h e AES and subsequent programs wi th emphasis on t h e 1969-1975

t i m e period. These items would be of a secondary n a t u r e t o such systems as

E M S h e l t e r , M O M , LSSM, and MFS.

B r i e f l y , t h e scope of work w a s :

1. Prepare a s k e l e t o n o u t l i n e of planned and proposed lunar s u r f a c e

systems and mission operations.

i

2. Out l ine p o t e n t i a l a r e a s where s p e c i a l purpose equipment, of any

na ture , might be used and show how it would support t h e mission.

3. Conceptually design c e r t a i n s e l e c t e d items including weight estimates

and i n t e g r a t i o n with mission opera t ions and primary lunar s u r f a c e systems.

. 4 . Study proposed systems, such as MOLAB, LSSM, MFS, and Lunar Shelters

to identif-y accessories which might at some point be added to accom-

plish a desired function.

5 . Coordinate with other MSFC and Hayes organizational elements for

inputs concerning equipment requirements, design, and mission analysis.

Many ideas were generated during the course of the study. Time did not

permit a detailed analysis of all the items or even the complete design con-

sideration of those devices which had obvious merits, One of the greatest

difficulties was to restrain the effort to the bounds of the study and not en-

croach on other areas such as design of equipment for scientific experiments

and larger systems already under study.

Consequently, the devices presented herein depict equipment for performing

the more mundane, but nevertheless important, functions required for lunar sur-

face base development.

Another great difficulty, which is not peculiar to this study, was predicting

the nature of the lunar surface. This, of course, would have a great effect on

the type of equipment required as well as on the detailed designs of obviously

necessary equipment,

which a selection could be made once the surface conditions are determined; for

example, an auger or shaped charge for hole drilling.

An attempt was made to present a choice of items from

In addition, other items are proposed which would be useful regardless of

2

c

t h e s u r f a c e condi t ion. Design modif icat ions would be made t o opt imize t h e i r

performance, i f requi red , f o r s p e c i f i c lunar s u r f a c e condi t ions. For instance,

t h e load-bearing capac i ty of t h e surface would determine t h e wheel conf igura t ion

f o r vehic les .

R e l i a b i l i t y , weight, c o s t , and t h e o t h e r usua l f a c t o r s were considered i n

t h e des ign d e r i v a t i o n s as w e l l as t h e i n t e r f a c i n g with t h e t r a n s p o r t modules

and t h e i r a s s o c i a t e d payloads.

One s i g n i f i c a n t design philosophy r e s u l t e d from t h e s tudy, and s t e m s

p r i m a r i l y from t h e high c o s t of t ranspor t ing payloads t o t h e moon.

every p iece of equipment o r mater ia l should be designed o r s e l e c t e d t o perform

as many func t ions a s p o s s i b l e a f t e r reaching i t s d e s t i n a t i o n . I n o t h e r words,

t h e r e should be l i t t l e , i f any, abandoned equipment. The la t te r p a r t of t h i s

philosophy p e r t a i n s more t o t h e l a t e r s t a g e s of lunar base development, s i n c e

e a r l i e r missions w i l l l i k e l y be made a t widely separa ted l o c a t i o n s of var ious

g e o l o g i c a l p o i n t s of i n t e r e s t and equipment landed i n previous missions would

not be a v a i l a b l e .

That is,

These thoughts a r e probably not new, but seem worthy of emphasis. The

experience of t h i s s tudy has shown t h a t , wi th a l i t t l e e x t r a thought and some

des ign v a r i a t i o n s , a p iece of equipment can be made t o perform s e v e r a l d i f f e r e n t

t a s k s o r f a c i l i t a t e ease of modif icat ions a t a la ter d a t e t o perform some o t h e r

o r a d d i t i o n a l funct ions.

3

2.0 MISSION OUTLINE

2.1 GENERAL

The two primary concerns on a l l manned missions t o t h e moon w i l l be

The equipment s u r v i v a l and the success fu l completion of ass igned t a sks .

requi red t o insure s u r v i v a l w i l l remain f a i r l y cons tan t f o r each ind iv idua l

man. The equipment requi red t o c a r r y out t h e mission opera t ions w i l l vary

cons iderably throughout t h e var ious phases of lunar exp lo ra t ion and u t i l i -

za t ion , I n general , t h e equipment w i l l become l a r g e r , more complex, and

more numerous. That i s , t h e same o r s i m i l a r s p e c i a l u t i l i t y equipment used

i n e a r l y missions w i l l a l s o be needed f o r subsequent miss ion ,p lus a d d i t i o n a l

items.

The planned and proposed lunar missions a r e shown i n Figure 1 and a r e

I b r i e f l y out l ined i n t h e fol lowing paragraphs. These missions a r e pos tu l a t ed

t o e s t a b l i s h the types of s p e c i a l equipment

varying degrees of lunar su r face exp lo ra t ion and t h e t i m e per iods f o r which

they would be requi red .

t h a t would be used t o support

2.2 LUNAR EXCURSION MODULE (LEM)

The i n i t i a l landi&) on t h e lunar s u r f a c e w i l l be very s i g n i f i c a n t , I

al though short i n dura t ion .

w i l l be t o determine t h e s u i t a b i l i t y f o r f u r t h e r exp lo ra t ion and e s t a b l i s h

more d e f i n i t i v e design c r i t e r i a f o r equipment on f u t u r e missions.

The primary purpose,once on t h e lunar s u r f a c e ,

S ince

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I

*

t h e mission w i l l be of very l imi ted du ra t ion , t h e t a s k s and, t h e r e f o r e , t h e

items of s p e c i a l equipment needed,will be few.

however, it is imperative that t h e few items enhance t h e man's e f f i c i e n c y

as much a s poss ib le .

Because of t h e s h o r t t i m e ,

The opera t ions performed during a L E M miss ion could go something l i k e

t h i s :

2.2.1 SITE ESTABLISHMENT

Af te r landing and v e r i f y i n g the s u i t a b i l i t y of t h e lunar enviormnent f o r

o u t s i d e exp lo ra t ion , t h e following t a s k s exemplify those t h a t could be performed:

Unload equipment

Clean dus t and d e b r i s from spacec ra f t and surrounding landing areas

Measure impression of landing f e e t and s e t t l i n g ra te

Measure e f f e c t s of rocke t b l a s t on luna r s u r f a c e

Deploy marker panels and o ther s i g n a l i n g devices t o assist CM i n s p o t t i n g

Level t h e ascent s t a g e

2.2.2 SCIENTIFIC TASKS

The fol lowing s c i e n t i f i c support t a s k s might be performed:

Carry instruments and conta iners t o d e s i r e d areas

D r i l l ho les t o o b t a i n sub-surface readings and samples

Emplace instruments, telemetering modules, antenna, and mark l o c a t i o n

Co l l ec t samples, seal conta iners

5

Observe and photograph lunar features and celestial bodies

Conduct experiments --- gravity, seismic, etc.

2 .2 .3 EXPLORATION

The investigation of various lunar features could involve:

Trailmaking and marking

Climbing or descending steep slopes

Spanning fissures

Mapping

Finding future landing areas

Transporting instruments and samples

2.2.4 EMERGENCIES

Emergencies which could arise are:

Pressure leaks - - - suit or spaceship Injury or collapse during exploration

Radio failure

Survival pack malfunction

Micrometeorite storm

2.2.5 CONSTRUCTION

Construction would be very minor and limited to such things as:

Burying or covering equipment

t

6

Erec t ing antennas, beacons

Clear ing and marking f u t u r e landing s i te

Dust r e t a i n i n g walls

Shade t e n t s

The foregoing t a s k s are char ted versus t h e equipment requi red t o perform

them i n Figure 2. This c h a r t was then used as t h e b a s i s f o r e s t a b l i s h i n g

s p e c i a l equipment requirements and derivirig equipment designs which could

perform m u l t i p l e funct ions.

2.3 AWLLO EXTENSION SYSTEMS (AES)

3 According t o a NASA r e p o r t , "Extended Lunar Exploration11 , t h e concepts

f o r AES can vary considerably. Br ie f ly , t h e concepts presented are:

2.3.1 STEM

The Stay-Time Extension Module would c o n s i s t of adding more equipment t o

t h e L E M t o i n c r e a s e t h e s t a y t i m e from one t o s e v e r a l days and t h e m o b i l i t y

r a d i u s from one io s e v e r a l m i l e s .

2.3.2 AES -

The Apollo Extension System u t i l i z e s two launch vehic les : a L E M Taxi t o

t r a n s p o r t two men t o t h e lunar sur face from o r b i t and r e t u r n them, and a L E M

Truck descent s t a g e t o land t h e s h e l t e r and/or v e h i c l e s and equipment, unmanned.

7

According to the latest thinking, the basic version of the LEM Truck payload

consists of a two man LEM Shelter and one or two small, open, powered vehicles

called Local Scientific Survey Modules (LSSM) which would provide 14 days stay-

time and a mobility of 16 kilometers for each of several sorties lasting from

three t o s i x hours each,. 4

Another version, which probably will occur in later A E S missions, depicts

the MOLAB as a LEM Truck payload.

hundred miles with a 14 day stay-time for two men. A manned flying system

(MFS) may be included with either version.

The MOJAB provides a mobility of several

The operations to be performed would be similar to those for LEM except

The two descent stages might require the clearing of on an expanded scale.

two sites and a link between them. As a minimum, the same special equipment

and materials as used for the LEM missions would be needed with an increased

quantity of certain items such as marker poles, explosives, etc.

Subsequent AES missions would require larger special items. Such things

as conversion of LSSM by the addition of inflatable, self-contained cabin

systems are considered. Generally, the special purpose equipment would

fall between those items required for the LEM and semi-permanent base

establishment. The chart in Figure 3 depicts the equipment required for

the various tasks and, as with the chart for LEM, was used to establish

requirements and conceptual designs.

8

2.4 SEMI-PERMANENT BASE

.

One of the important tasks of the earlier missions will be the selection

of a site for a semi-permanent and, eventually, a permanent base complex on

the moon. Data on the suitability of lunar materials for structures and other

uses also should be available fromthe earlier exploration and would be

utilized as extensively as possible in the base facilities and systems.

is likely, however, that nearly all of the material will still be transported

to the moon in an almost final form, as was done on earlier missions.

It

The Lunar Exploration System for Apollo (LESA) proposes landings, with

the unmanned logistic spacecraft being a direct flight capable of delivering

11,370 kilograms (25,000 pounds) to the lunar surface. The payload would be

a large shelter-laboratory and a PQLAB type vehicle. This system would allow

a 90-day stay-time with extensive mobile exploration.

The semi-permanent base could consist of multiple LESA-type shelters with

different laboratory-type equipment or central support type systems in each,

such as an astronomical observatory in one, a nuclear power generator in

another, etc.

facilities and systems which could be found in such a base complex.

The following is a partial listing of the various types of

2.4.1 FACILITIES

1. Basic living shelters

2. Astronomical observatory

9

3 .

4.

5.

6 .

7 .

8.

9 .

Earth TV monitor station

Experimentation laboratory analysis and testing of lunar materials

and earth materials in lunar enviroment

Repair and fabrication shop

Medica 1 facility

Physical conditioning facility - Exercise equipment, bathing equipment, sun lamps, centrifuge

Storage areas

Solarium - Hydro-ponic and soil growing of food. fertilizer, CO

Uses waste for

and O2 exchange for ESC. 2

2.4.2 SYSTEMS

1. Power generation and conversion - Solar cells, thermo-electric,

thermionic, thermo-mechanical, nuclear, power distribution, battery

charging .

2. Environmental control

(a) Temperature - Heat-pumps, radiators, solar reflectors (b) Humidity

(c) Atmosphere

(d) Pressure

3 , Lighting - Natural: reflectors, diffusers; Artificial: flourescent,

incadescent

.

10

,

4. Waste reclamation and disposal

5 . Communications - Radio, TV, telephone (sound power) 6 . Cryogenics conditioning and handling I

I

7. Pumping - Airlocks, pressurization 8 . Automatic landingllaunching system - Radar, beacons, doppler, computers I

Some of the special equipment requirements that can be envisioned for I ~

integrating, linking, and supporting the separate semi-permanent base facilities I

l and operations are listed below:

Road construction

Power and utility distribution lines and poles

Flood lights

Emplacement of heat-pump coi 1s

Interconnecting conveyor pipes

Setting-up an automatic landing/ launching system

Shuttle bus between shelters for transporting personnel without leaving I

pressurized environment

Hoisting and transporting large items

Maintenance and repair of various equipment

Excavat ionlmining type operations

Processing and utilization of lunar materials

11

This is a partial listing to cover only those facilities and systems which

are likely to occur or be initiated during the early part of a lunar semi-

permanent base establishment since the greater portion of this operation lies

beyond the time period covered by this study-

postulated to support the early phases of semi-permanent base development.

Figure 4 shows the equipment

2 . 5 PERMANENT BASE

Since this phase of lunar development falls well beyond the time period

covered by this study, a detailed analysis of special purpose equipment was

not carried out. Some general thoughts on the subject are:

1. The type of equipment needed will depend primarily on:

(a.) The environment, topography, and materials on the moon

(b.) The type and method of construction to be used

(c.) The extent to which the base(s) will be developed.

2. The facilities and systems likely to be established would be similar

to those listed for the semi-permanent base.

3 . The method of sheltering these systems, facilities, and personnel

would be different. Lunar materials would be used for optimum

meteoroid, radiation and thermal protection. One of the most obvious

ways of using the natural materials is by tunneling beneath the surface

or into the side of a mountain. The latter appears more attractive

since mountains would likely be composed of more solid material and

would be clear of surface dust.

.

1 2

Needless t o say, a much b e t t e r i n s igh t t o t h e problem w i l l be a t t a i n e d

as da ta from t h e preceding missions becomes ava i l ab le .

2.6 SUMMARY

As a r e s u l t of t h e above, t h e items of s p e c i a l equipment w e r e separated

i n t o categories of t o o l s , vehicles , instruments, materials, and miscellaneous.

They are f u r t h e r grouped a s small, medium, and l a rge and are presented i n

Tables I, 11, and I11 respectively.

Select ions were made from these lists of t h e items f o r which new concepts

were desired. These concepts a r e presented i n t h e following section.

.

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16

3.0 CONCEPTS

.

.

As s t a t e d previous ly , t h e l i s t s of equipment presented thus f a r were not

meant t o i n f e r t h a t each of t h e s e items should be used t o support lunar opera t ions .

Rather , they formed t h e b a s i s f o r der iv ing a few i t e m s of mult i -purpose equipment

which would perform t h e requi red ' func t ions . Those

i t e m s which a l r eady exist and are d i r e c t l y a p p l i c a b l e t o lunar ope ra t ions are

included i n t h e f i n a l l i s t of proposed equipment.

d e t a i l design changes t o b e t t e r s u i t them t o luna r opera t ions , but t h e b a s i c

concepts a r e d i r e c t l y app l i cab le and, t h e r e f o r e , are not presented as new concepts

here. Some examples are shaped charges, t r a n s i t , f l a s h l i g h t , etc.

This w a s not always poss ib le .

Such items might undergo

Numerous conceptual designs and ideas w e r e genera ted , but only those i t e m s

t h a t seemed p a r t i c u l a r l y unique and p r a c t i c a l are presented.

a p p l i c a t i o n of t h e s p e c i a l purpose equipment t o t h e d i f f e r e n t miss'ion phases

is shown i n Figure 5 . Some of t hese i t e m s are r e f e r r e d t o by t h e nicknames

assigned f o r i d e n t i f i c a t i o n purposes i n t h i s r epor t . The i t e m s are descr ibed

i n t h e fol lowing sec t ions .

The proposed

I n add i t ion t o t h e a s s i s t a n c e and sugges t ions provided by t h e NASA Base

Development Sec t ion i n t h e pe r iod ic review meeting, the ske tches a t t ached a s

Appendix A a t t h e end of t h i s r epor t a l s o w e r e furn ished by them.

is a p i c t o r i a l summary typ i fy ing var ious small lunar veh ic l e conf igu ra t ions

and o the r ideas culminat ing from previous e f f o r t s and recent ideas a p p l i c a b l e

to t h i s s tudy.

The appendix

17

3.1 TOOLS

3 . 1 . 1 SMALL TOOLS AND’ UTILITY BELT

The general type of t o o l s t h a t can be used are shown i n F igures 6 and 7:

a sample pouch, a tape r u l e , a battelfy f l a s h l i g h t , a k n i f e t o o l hook, a r e p a i r

k i t , a s a w , a hammer, and a u t i l i t y b e l t . Two por t ab le e l e c t r i c space t o o l s ,

(PESTS) t o be u t i l i z e d a re a b a t t e r y opera ted , motor dr iven d r i l l wi th d r i l l

b i t s , and a por tab le e lectr ic , bat tery-operaged, mult i -purpose space t o o l .

,

I

, 3 . 1 . 2 COMBO

The COMBO (combination too l ) i s p i c tu red i n F igu res 8, 9 , and 10. The

bas i c t o o l i s a combination p ick , shove1,and pry ba r . A choice of a t tachments ,

as shown, renders i t app l i cab le t o o t h e r func t ions , most of which a r e s e l f

explana tory . Snap locks provide quick a l t e r a t i o n t o the va r ious conf igu ra t ions .

A rope o r cord would be a t t ached t o the handle when used a s a grappl ing hook

wi th the pick and shovel extended and the grapple a t t ached a t r i g h t angles t o

them.

as the b i t progresses i n t o t h e ground.

I

Rela t ive ly deep d r i l l i n g can be performed by adding t h e extension shaf t

The bas i c device would be f a b r i c a t e d from t o o l s tee l and would weigh 7.0

kilograms (15 .4 pounds) without a t tachments .

a r e l i s t e d below:

The va r ious attachment weights

Handle 0.1 kg (0 .22 l b )

Auger 0.45 kg (1.00 l b )

Ch i se l 0 .45 kg (1.0 l b )

Tamper 3.60 kg (8.0 l b )

18

.

Sledge

G rapp 1 e

Posthold Digger

Extensions

3.1.3 FORK LIFT.

4.5 kg (10 l b )

0.9 kg (2.0 l b )

0.9 kg (2.0 l b )

1.18 kg/m (0.8 l b / f t )

During t h e s c i e n t i f i c mission and lunar base es tab l i shment , many occasions

undoubtly w i l l aris.e when equipment must be moved from one area t o another.

t h i s purpose, a l i f t t h a t w i l l be capable of l i f t i n g , h o i s t i n g , j ack ing , and

t r a n s p o r t i n g equipment has been designed (see Figure 11). The o v e r a l l s ize of

t h i s l i f t i n g device is 76 x 76 x 183 cent imeters (30 x 30 x 72 inches) , and it

has a weight of 90 kilograms (200 pounds).

columns t i e d toge the r a t t h e top w i t h a header and a t t h e bottom wi th a gear -

d r i v e base. Removeable swing l egs a re a t t ached t o t h e columns t o provide

l i f t i n g and t r a n s p o r t i n g c a p a b i l i t i e s . Between t h e v e r t i c a l members i s a

c a r r i a g e t h a t r i d e s up and down through t h e use of e i g h t r o l l e r s .

i s d r iven up and down wi th a bal l -screw and b a l l - n u t assembly u n i t .

and worm-gear d r i v e i s d i r e c t l y fas tened t o t h e b a l l screw and is capable of

accept ing t h e a r i a 1 t h r u s t caused by t h e exer ted load.

by a hand crank through u n i v e r s a l s and a d r i v e s h a f t .

For

The des ign c o n s i s t s of two v e r t i c a l

The c a r r i a g e

A worm

The gear box is dr iven

The c a r r i a g e has two use fu l s ides , each wi th f i v e s l o t s . The fou r ou te r

s l o t s are used t o hold t h e f o r k - l i f t fold-away arms, and locking an arm i n the

c e n t e r slot: w i l l provide a device t o j a c k up o r h o i s t equipment. A h o i s t hook

can be placed i n t h e c e n t e r of the fold-away arms so t h a t i t could l i f t hardware

t h a t has a s l i n g o r nylon rope attached.

of t h e s t r u c t u r e so t h a t t he l i f t may be r o l l e d i n t o p o s i t i o n f o r l i f t i n g

Two wheels a r e provided a t t h e bottom

19

and also so that the complete unit may be converted into a push or pull cart.

For moving from one place to another, items must be loaded onto the two swing

legs.

Figure 11.

nism ismade of stainless steel. The lift will provide five feet of travel.

These legs can be removed and stowed in a vertical position as shown in

The basic super structure is made of aluminum and the drive mecha-

Figures 12 and 13 depict the configuration and design features. The size

was dictated primarily by those dimensions required for carrying or covering a

space-suited astronaut with back-pack.

steel applied in those areas where added strength and abrasion resistance is

The basic material is magnesium, with

I required. The estimated weight, using these materials, is 39.1 kilograms

The Travois also is readily adaptable to a fork-lift type mechanism

through the addition of a crank, a winch, and the Travois ladder.

22 for a visual description.

See Figure

3.2 VEHICLES

3.2.1 TRAVOIS

One of the most promising concepts to come out of this study is the

Travois. This name was chosen because the initial concept was a simple de-

vice to aid in transporting equipment,

American Indians. By expanding this basic concept, a versitle, multipurpose

vehicle and tool was obtained.

similar to the travois used by the

20

(86 pounds) or, on the moon, 6.52 kilograms (14.35 pounds). This weight

includes 10 D-size, rechargeable batteries.

The primary function of the Travois is to serve as a carrier for the many

items of equipment that the astronaut will have to carry in the course of his

walking traverses and performance of scientific tasks. In addition, however,

the Travois is capable of performing many other functions.

applications are shown in Figures 14 through 22.

configurations shown can be accomplished quickly since spring-loaded, snap-

lock pins are employed for positioning the tailgate/scoop, wheels, and ladder.

Collet-type, friction locks are used for positioning the handles. The handles

and the spotlight can be removed from the ladder and attached to the body of

the Travois or used separately.

Some of the many

Adjustments to the various

The equipment box is to be used to carry small items and also to provide

for the attachment of devices such as winches and reels for wire laying.

Mounting points also are located in other positions for attaching fixtures such

as a push broom or roller as a part of or in place of the tailgatelscoop.

A more extensive adaptation is shown in Figure 22, where conversion to

a hand powered fork lift has been effected.

addition of:

This was accomplished by the

1. an adapter to attach the ladder

2.

3.

a sliding adapter for mounting the tailgatelscoop on the ladder

an adapter for attaching the pulley system and cable guide to the

top of the ladder

a hand winch with cable mounted on the equipment box 4.

21

The add i t iona l p ieces weigh 7.6 k i lometers (16.75 pounds). An extended

l i f t i n g he ight of approximately 3.35 meters (11 f e e t ) can be obtained by adding

another ladder i n series wi th the one ladder and using a longer cable . Obviously,

t h e fo rk l i f t arrangement a l s o can se rve a s an overhead ho i s t .

Another v a r i a t i o n of t he Travois , which has no t been f u l l y explored, i s accom-

p l i shed by t h e add i t ion of a small power pack.

t o d r i v e the winch descr ibed above, t o se rve as a d r i l l i n g r i g a t tachment , o r t o

provide l imi t ed mobi l i ty . The l a t t e r i tem i s envis ioned as providing an a s s i s t t o

t h e a s t r o n a u t i n pushing o r p u l l i n g the Travois up grades o r over rough t e r r a i n .

A l imi t ed r i d i n g . c a p a b i l i t y would be a v a i l a b l e i n emergencies, but not t o the

ex ten t proposed f o r t he MULE descr ibed i n a l a t e r s ec t ion .

Some of the apparent uses would be

t

Some growth p o t e n t i a l s of t he Travois a r e covered i n the sec t ions desc r ib ing

t h e MULE and CAMUL.

3 . 2 . 2 MULE

The Travois c a n be converted t o a mobile c a r r i e r by adding a s e a t , power

pack, s t e e r i n g mechanism, t a i l s k i d s , and rep lac ing t h e wheels with l a r g e r ,

motorized wheels. The n e t weight increase i s es t imated a t 82 kilograms (180

pounds) f o r a t o t a l v e h i c l e weight ( l e s s man) of 93 kilograms (205 pounds).

The lunar weight would be 15.5 kilograms ( 3 4 . 2 pounds). A l a rge con t r ibu t ion

t o the veh ic l e weight i s t he 22.7 kilograms (50 pounds) power pack. This weight

of s ea l ed , rechargeable , Ag-Zn b a t t e r i e s would provide approximately 500 wat t -

hours of energy.

22

Two views of the MULE are shown in Figure 2 3 . As can be seen, most of the

weight is well forward over the driving wheels for better traction.

leaves considerable room in the rear of the bed for equipment or another man.

This also

One of the deployable shields or covers described in another section could

be attached for micrometeorite protection and/or shade, if necessary.

An extended mobility range, as well as cargo carrying ability, can be

realized by pulling a trailer with additional power packs and life support back

packs behind the MULE. This would also be true for other lunar vehicles (LSSM,

MoLA3).

3 . 2 . 3 CAMUL

The CAMUL (cabin MULE) is shown in Figure 2 4 . This configuration is

obtained by attaching a self-contained, semi-inflatable cabin system to the

MULE vehicle. This same concept could be applied to other lunar vehicle designs,

such as LSSM.

The inflatable portion of the cabin would be made of a sealed fabric ma-

The double wall con- terial with double walls and stress hoops evenly spaced.

struction allows continuous pressure to be applied to prevent cabin collapse

when the inner volume is evacuated for airlock operation.

close each end of the cabin with the access door and viewing port forming a part1

of the rear hemisphere. A transparent dome provides visibility for steering and

observation. The forward hemisphere contains sealed interfaces and linkages for

Aluminum hemispheres

23

the steering mechanism and oxygen pressure tank attachment. Instruments would

also be housed here.

This concept uses the whole cabin as an airlock, although there is room

for an intermediate pressure divider and door which would permit using only

the rear portion of the cabin as an airlock.

The inner volume of the cabin is 1.68 cubic meters (60 cubic feet) when

extended to the 2.9 meter (9.5 feedlength.

1.1 meters (3.6 feet) for storage. The estimated weight of the cabin system

and empty 0 bottle is 33.1 kilograms (67.3 pounds). The 02 bottle provides 2

28,320 cubic centimeters (1.0 cubic feet) of volume and would contain approxi-

mately 4.1 kilograms (9 pounds) of oxygen.

The cabin can be collapsed to

3.2.4 MAN- POWERED TRICYCLE

There seems to be some question as to the need for a vehicle which is

smaller than,the Local Scientific Survey Module, but which would provide

mobility capacities greater than that of the walking astronaut. Figure 25

illustrates a suggested design for such a vehicle, called a Man-Powered Tri-

cycle. This design has three wheels that are attached to a torsion bar chassis.

The one front wheel is in the shape of a long cylinder, and is 30.5 centimeters

(12 inches) in diameter and 91.6 centimeters (36 inches) long. ( A wheel of a

larger diameter will be considered for future studies.) It is mounted on a

fork which is foot-steerable. In the rear are two wire-spoked wheels that are

91.6 centimeters (36 inches) in diameter, and 30.5 centimeters (12 inches) wide.

24

The rear wheels are connected to the rear axle and are driven by an oscillating

arm,quick-return crank type mechanism. This mechanism is powered by the astro-

naut through hand pump lever Linkage. The driver Ls seated and strapped in so

that he can provide push and pull power required €or mobility.

'pe entire tricycle is 152 x 213 x 140 centimeters (60 x 81 x 55 inches),

a size which will readily fit into the payload envelope.

36.3 kilograms (80 pounds).

ELMS report.

the aluminum is used for the superstructure and the steel for the internal

drive mechanism.

The module weighs

It was designed to requirements presented in the

The materials selected for this module were aluminum and steel;

The advantages of this specific design include the factors that no fuel

is needed to power the vehicle, it can haul other equipment through the use

of a hitch attachment, it can furnish the necessary exercise that a man should

have under the influence of one-sixth g, and it will consist of fewer parts,

such as brakes, etc.

3.3 SHELTERS

3.3.1 INFLATABLE SHELTERS -

A preliminary design analysis indicates that a crosz sectional thickness

of one inch will meet the imnediate needs for a shelter. The shelter wall will

25

consist of an exterior wall of 0,152 centimeters ( 0 , 0 6 0 in.) of white silicone

rubber, a 2.29 centimeters (0 .90 in.) layer of insulated urethane foam, a

0.076 centimeters ( 0 0 0 3 in.) matrix of a stress filament with a polyurethane,

elastomeric compound and a 0.025 centimeters (0.01 in.) internal gas pressure

seal, butyl rubber wall. The first two layers will act as a micrometeoroid

bumper, the filament layer will provide the necessary structural integrity,

and the internal layer will seal the shelter against oxygen pressure leaks.

Figure 26 illustrates a typical inflatable shelter wall cross section where

the internal cabin configuration is pressurized at 3.5 to 4.0 psi.

Another shelter design presents a pressurized wall construction generally

utilized as an emergency facility, shown in Figure 27. The wall cross section

is 2.54 centimeters (one inch) thick and consists of an inner and outer wall

both of which are tied together with a tension membrane to prevent wall sepa-

ration. In this design the wall is pressurized until the shelter stands erect.

The floor is constructed in the same manner; however, it is much thicker in

order to support the weight of two men and their equipment. This shelter is

capable of standing erect with or without pressurization of the inner cabin.

A zipper with a pressure-seal type lip is provided around the door. In

emergency service, the zipper is closed and the cabin is pressurized to 4.0

psi.

has an expanded internal volume of 47.6 cubic meters ( 1 7 0 cubic feet), a

stowage volume of 8 .4 cubic meters ( 3 0 cubic feet), and a stowed size of 0.61

x 0.762 x 1.83 meters ( 2 x 2% x 6 feet).

The two-man emergency medical tent weighs 45.4 kilograms (100 pounds),

26

.

The s i n g l e man emergency medical t e n t i s shown i n Figure 28 and i s p a r t

of t h e a s t r o n a u t s ' s o r t i e equipment. I n t h e stowed or r o l l e d up package, t h e

t e n t i s 61 cen t ime te r s (24 inches) long by 30.5 cen t ime te r s (12 inches) i n

diameter and weighs 10 kilograms (22 pounds). The package con ta ins seve ra l

oxygen b o t t l e s , an a i r b o t t l e , a s u i t r e p a i r k i t , and an emergency s i g n a l

c o n t r o l device. The t e n t is cons t ruc ted i n t h e same manner a s t h e two-man

medical f a c i l i t y .

This t e n t w i l l provide pro tec t ion f o r t h e a s t r o n a u t i n t h e event t h a t h i s

s u i t should be damaged. It w i l l have s u f f i c i e n t oxygen and oxygen pressure

f o r him t o remove h i s v i s o r i f h e should f e e l ill. A i r (oxygen) i s used t o

i n f l a t e t h e ou te r wa l l s of t h e t e n t , then t h e wan s l ides i n , c l o s e s t h e

z ippe r , and f i l l s t h e i n t e r i o r with oxygen.

t h e necessary s u i t r e p a i r s .

H e then is i n a p o s i t i o n t o make

3.3.2 COLLAPSIBLE SHELTERS

I n a d d i t i o n t o providing s h e l t e r f o r a s t r o n a u t s , it a l s o is important

t h a t equipment be p ro tec t ed from the lunar environment. These enc losures ,

c a l l e d c o l l a p s i b l e s h e l t e r s , could provide p r o t e c t i o n f o r both. They a r e

l a r g e i n volume and small i n weight, and, a s shown i n Figure 29, they a r e

designed i n v a r i o u s shapes so as t o conform t o t h e equipment contours and

luna r stowage needs.

m a t e r i a l i s an aluminized mylar supported a t va r ious i n t e r v a l s wi th metal

b races of a sc i s so r s - type assembly. When t h e s h e l t e r s a r e expanded, they

w i l l s e rve t o p r o t e c t equipment from t h e lunar dus t , s o l a r energy and

The genera l cons t ruc t ion i s such t h a t t h e ou t s ide

27

radiation, and micrometeoroids. However, in order to protect equipment from the

latter, lunar soil must be added around and over the shelter.

3.3.3 SHIELDS

In the category of shelters and shields, several other designs are pre-

sented which will protect the individual man from micrometeoroid showers during

sorties. An extendable shield (buggy type) is shown in Figure 30. This shield

is 0.686 meters (2.25 feet) wide, 0.838 meters (2.75 feet) high, 1.77 meters

(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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P i c k

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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

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- I

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53

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54

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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)

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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

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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) ,

Donald Elston Manned Lunar Exploration Investigation Astrogeological Branch USGS Flagstaff, Arizona

Langley Research Center Hampton, Virginia

Mr. R. S. Osborn

c

1

100