Lunar Surface Mobility Systems Comparison And Evolution -Books Pdf

LUNAR SURFACE MOBILITY SYSTEMS COMPARISON AND EVOLUTION
17 Dec 2019 | 29 views | 0 downloads | 26 Pages | 1.12 MB

Share Pdf : Lunar Surface Mobility Systems Comparison And Evolution

Download and Preview : Lunar Surface Mobility Systems Comparison And Evolution


Report CopyRight/DMCA Form For : Lunar Surface Mobility Systems Comparison And Evolution



Transcription

FINAL REPORT,BOOK 1 MOLEM MOCOM MOCAN,PART 1 TECHNICAL REPORT. PART 2 RESOURCE PLANNING,BOOK 2 MISSION ANALYSIS,BOOK 3 S Y S T E M S ENGINEERING. LUNAR ROVING VEHICLES,BOOK 4 S Y S T E M S ENGINEERING. LUNAR FLYING VEHICLES,BOOK 5 RESOURCE PLANNING,BOOK 6 EVOLUTION METHODOLOGY. DEVELOPMENT,BOOK 7 EVOLUTION METHODOLOGY,USER S MANUAL.
VOLUME 111,I RESEARCH AND TECHNOLOGY,IMPLICATIONS, THE BOOK YOU ARE READING I S INDICATED BY T H E ARROW. LUNAR SURFACE MOBILITY,SYSTEMS COMPARISON,AND EVOLUTION MOBEV. FINAL REPORT,VOLUME 111,RESEARCH A N D T E C H N O L O G Y. IMPLICATIONS,BSR 1 4 2 8,PREPAREDFOR,NATIONAL AERONAUTICS AND SPACE ADMINISTRATION. GEORGE C MARSHALL S P A C E FLIGHT CENTER,HUNTSVILLE A L A B A M A.
UNDER CONTRACT N O NAS8 20334,Approved by P Q,C 3 Weather ed D i r e c t o r. Lunar Vehicle P r o g r a m s,N O V E M B E R 1966. aAerospace,CORPORATION Systems Division, This document p r e s e n t s the r e s u l t s of the L u n a r Surface Mobility. S y s t e m s Comparison and Evolution Study MOBEV conducted f o r the. National Aeronautics and Space Administration M a r s h a l l Space Flight C e n t e r. Huntsville Alabama under Contract NAS8 20334 The Bendix t e a m r e. sponsible f o r the MOBEV Study includes Bendix Systems Division of The. Bendix Corporation Bell A e r o s y s t e m s Company and Lockheed M i s s i l e s. and Space Company Bendix in addition t o o v e r a l l p r o g r a m management. and s y s t e m integration h a s been responsible f o r L R V Systems Mission. Studies and the MOBEV Methodology Bell h a s been responsible f o r the. Flying Vehicle S y s t e m s Lockheed has been responsible f o r the LRV Human. F a c t o r s Environmental Control Life Support and Cabin Structures. The study w a s p e r f o r m e d by personnel of the Lunar Vehicle P r o g r a m. D i r e c t o r a t e of Bendix Systems Division The Bendix Corporation under. the d i r e c t i o n of Mr C J Weatherred P r o g r a m D i r e c t o r Mr R E W t m g. Engineering Manager and Mr C J Muscolino P r o j e c t Manager MOBEV. The NASA Technical Supervisor for the c o n t r a c t w a s M r Richard Love. R P V E A A M a r s h a l l Space Flight Center,1 INTRODUCTION 1 1. 2 AERONAUTICS 2 1,3 BIOTECHNOLOGY AND HUMAN RESEARCH 3 1.
3 1 LIFE SUPPORT 3 1, 3 1 1 Two Gas Control S y s t e m Oxygen Partial P r e s. s u r e Sensor 3 2, 3 1 2 Regenerative Molecular Sieve C 0 2 Removal 3 2. 3 1 3 Vacuum Drying Waste P r o c e s s i n g 3 2,3 1 4 P r e s s u r e Suits 3 3. 3 1 5 P o r t a b l e Life Support S y s t e m s 3 3. 3 2 HUMAN FACTORS AND SIMULATION 3 3,3 2 1 LRV Simulation Needs 3 4. 3 2 2 LRV Mission Simulation Studies 3 4,3 2 3 L F V F r e e Flight Simulation 3 4.
3 2 4 L F V Visual Display R e s e a r c h 3 5,3 2 5 Lunar Celestial Azimuth Reference 3 5. 3 2 6 Maintenance Capabilities of the Astronaut 3 6. 3 2 7 C r e w Composition Studies 3 6, 3 2 8 Spacesuit P e r f o r m a n c e C h a r a c t e r i s t i c s 3 6. 3 2 9 Metabolic Rates 3 7,3 2 10 LRV Vehicle Vibrations 3 7. 3 2 11 C r e w Safety Studies 3 7,4 ELECTRONICS AND CONTROL 4 1. 4 1 ROVING VEHICLES 4 1,4 2 FLYING VEHICLES 4 1,5 MATERIALS AND STRUCTURES 5 1.
5 1 FLUID DAMPING SUSPENSION SYSTEMS 5 1,5 2 LUBRICANTS 5 1. CONTENTS CONT,5 3 EXTERNAL SURFACE MATERIALS 5 1,5 4 COLD WELDING 5 1. 5 5 THERMAL COATING RESEARCH 5 2,5 6 LOW CONDUCTIVITY TASK SUPPORT STRUCTURE 5 2. 5 7 HIGH TEMPERATURE INSULATION 5 2,5 8 MICROMETEORITE PROTECTION 5 3. 5 9 ENERGY ABSORPTION TECHNIQUES 5 3,5 10 DAMPED SPRING MATERIAL INVESTIGATION 5 4.
NUCLEAR SYSTEMS 6 1,6 1 RTG 6 1,6 2 RTIG 6 1,6 3 RANKINE SYSTEM 6 1. PROPULSION AND POWER GENERATION 7 1,7 1 TRACTION DRIVE MECHANISMS 7 1. 7 2 RADIATION COOLED THROTTLEABLE ENGINE,DEVELOPMENT 7 1. 7 3 ROCKET EXHAUST PLUME E F F E C T S 7 1,7 4 PHOTOGRAPHY THROUGH ROCKET EXHAUST. PLUMES 7 2,ABBREVIATIONS AND VEHICLE NOMENCLATURE,LM Apollo Lunar Module.
CM Apollo Command Module,CAN Multimis sion Module, LM Shelter Two Man Lunar Shelter derived from Apollo Lunar. LM Truck LM T Logistics Delivery System derived f r o m Apollo. Lunar Module descent stage, MOLEM Lunar Surface Mobility System derived from LM. MOCOM Lunar Surface Mobility System derived from C M. MOCAN Lunar Surface Mobility System derived from CAN. ECS Environmental Control System,RTG Radiosotope Thermoelectric Generator. ELMS Engineering Lunar Model Surface,PLSS P o r t a b l e Life Support System. LIOH Lithium Hydroxide,EVA E x t r a Vehicular Activity.
H2 Hydrogen,E PS E l e c t r i c a l Power System,SNAP Space Nuclear Awcilary Power System. TDM Traction Drive Motor,SDM Steering Drive Mechanism. IMU Inertial Measurement Unit,Alignment Optical Telescope. Apollo Logistics Support Systems,P r a t t and Whitney. Mobility Test Article,Spe c if i c Re ac tan t Cons ump ti on.
Local Scientific Survey Module,Manned Space Flight Network. Kennedy Space Center,MOLAB Mobile Laboratory,Mission Control Center. Dimension from r e a r wheels to CG over total length. Point of Slip at which maximum t h r u s t i s developed. Apollo Extension Systems,Lunar Exploration Systems for Apollo. AAP Apollo Applications P r o g r a m, I The following nomenclature is used throughout the r e p o r t and was. adopted to facilitate recognition of the l a r g e number of vehicles and m i s. s ions considered,1 ROVING VEHICLES, 1 F i r s t l e t t e r R defines vehicle a s Rover.
2 Second number 0 through 3 defines vehicle c r e w size. 3 T h i r d letter A through D defines specific mission of vehicle. 4 Fourth l e t t e r E o r B defines vehicle a s being Exploration o r. Base Support vehicle,Example R l B E rover one man vehicle B mission. exploration vehicle,FLYING VEHICLES, 1 F i r s t l e t t e r F defines vehicle as F l y e r. 2 Second number 0 through 3 defines vehicle c r e w s i z e. 3 T h i r d l e t t e r A through E defines specific mission of vehicle. Example F1B flyer one man vehicle B mission,CSM Apollo Command and Service Module. C N Guidance and Navigation,AES MLS AES Manned Lunar Surface. ALSEP Apollo Lunar Surface Experiments Package,LFV Lunar Flying Vehicle.
MFS Manned Flying System, MIMOSA Mission Modes and Systems Analysis for Lunar. E xplo ration,SLRV Surveyor Lunar Roving Vehicle,DPV Design Point Vehicles. LLV Lunar Logistics Vehicle,ESS Emplac e d Scientific St ation. INTRODUCTION, Results obtained on the Lunar Surface Mobility S y s t e m s C o m p a r i s o n. and Evolution Study MOBEV indicate that f u r t h e r e f f o r t s in c e r t a i n a r e a s. of r e s e a r c h and advanced technology would be d e s i r a b l e The r e c o m m e n d a. tions a r e s u m m a r i z e d in this volume and a r e l i s t e d under the following c a t e. Aeronautics,Biotechnology and Human R e s e a r c h.
E l e c t r o n i c s and Control,M a t e r i a l s and S t r u c t u r e s. Nuclear S y s t e m s,P r o p u l s i o n and P o w e r Generation. AERONAUTICS, N o aeronautics p r o b l e m s requiring r e s e a r c h and technology advances. a r e foreseen,BIOTECHNOLOGY AND HUMAN RESEARCH,3 1 L I F E SUPPORT. The development of life support s y s t e m components and s u b s y s t e m s f o r. the Gemini Apollo and L M P r o g r a m s as w e l l as the independent r e s e a r c h. a n d development efforts w i l l provide a f i r m b a s i s f o r development of the. MOLAB and MOBEX f a m i l i e s of vehicles, The MOLAB vehicles utilize concepts identical o r v e r y s i m i l a r to the.
a p p r o a c h e s used in the c u r r e n t l y funded h a r d w a r e p r o g r a m s It is e s t i. m a t e d that as much a s 5070 of the life support components r e q u i r e d f o r. MOLAB vehicles w i l l be directly available f r o m o t h e r p r o g r a m s while. 3570 w i l l r e q u i r e only slight modification A s low as 1570 will be new. component design and these will be w e l l within the existing technology. T h e development of a n a i r l o c k pumping s y s t e m improved s p a c e radiator. design f o r lunar s u r f a c e operation d u s t removal i m p r o v e d s u r f a c e c h a r a c. t e r i s t i c s folding capability improved s u i t design f o r i n c r e a s e d mobility. improved was te collection componentry and improved PLSS design f o r. g r e a t e r operational u s e a r e r e q u i r e d f o r the MOLAB vehicles. In addition to the development w o r k outlined above the MOBEX v e. h i c k s prese t ZPU technnloev Droblems a r i s i n g f r o m the new life support. s y s t e m concepts applicable to the longer m i s s i o n s The introduction of a. two gas a t m o s p h e r e regenerable m o l e c u l a r s i e v e C 0 2 r e m o v a l and. vacuum drying w a s t e d i s p o s a l p r e s e n t development problems The ex. tended m i s s i o n piaces g r e a t e r emphasis on the development of s p a c e r a d i a. t o r s m e t e o r o i d puncture problems and ultraviolet U V degradation of. t h e r m a l coatings s t o r e d food with higher package density and g r e a t e r. e a s e of rehydration and p r e s s u r e s u i t s with g r e a t e r flexibility of o p e r a. tion possibly the h a r d s u i t, 3 1 1 Two Gas Control System Oxygen P a r t i a l P r e s s u r e Sensor. Numerous studies have been conducted which tend to s u b s t a n t i a t e. the need f o r a two gas s y s t e m when a s t r o n a u t s a r e in a confined cabin. environment f o r m o r e than 2 8 days Although two gas control s y s t e m s. have been operated s u c c e s s f u l l y f o r periods exceeding 90 days in l a b o r a. t o r y and flight prototype s y s t e m s periodic calibration of the oxygen p a r t i a l. p r e s s u r e s e n s o r h a s been required This p r e s e n t s a n a r e a f o r significant. development effort Without the development of a longer life m o r e s t a b l e. oxygen p a r t i a l p r e s s u r e s e n s o r periodic calibration probably e v e r y seven. d a y s by the crew will be required Such calibration has been proved. feasible in simulated flight operations but r e q u i r e s additional equipment. and s o m e o p e r a t o r time approximately 10 minutes p e r calibration The. polargraphic P O 2 s e n s o r offers the g r e a t e s t potential a t this time De. velopment efforts f o r this s e n s o r must d e a l with the electrolyte drying. problem a s the m o s t significant variable affecting stability and life. 3 1 2 Regenerative Molecular Sieve CO Removal, The regenerable molecular s i e v e concept for C02 r e m o v a l has. r e c e i v e d a considerable amount of development work A l a r g e number of. l a b o r a t o r y and flight prototype units have been built and tested S e v e r a l. long duration runs up t o 6 0 d a y s have been completed P r o b l e m s have. been encountered during many of these runs that w e r e p r i m a r i l y a s s o c i a t e d. with component life and loading of the m o l e c u l a r s i e v e beds with w a t e r. vapor The l a t t e r problem has been solved by periodic heating of the. m o l e c u l a r s i e v e bed during CO2 desorption to a l s o remove w a s t e vapor. Littie ir any basic dcve cpment wcrk is needed f o r the r e g e n e r a b l e. m o l e c u l a r s i e v e s y s t e m but functional and r e l i a b i l i t y testing of a flight. unit should be initiated e a r l y in the p r o g r a m to allow time f o r component. life upgrading,3 1 3 Vacuum Drying Waste P r o c e s s i n g. A number of l a b o r a t o r y vacuum drying w a s t e p r o c e s s i n g s y s t e m s. have been built and tested Feasibility of this concept of w a s t e p r o c e s s i n g. and s t o r a g e had been demonstrated but much work r e m a i n s to provide a. unit that is suitable f o r operational use The following methods need to. be investigated 1 loading and unloading w a s t e m a t e r i a l to minimize. o p e r a t o r involvement 2 reducing drying t i m e by i n c r e a s i n g contact between. heating s o u r c e and the w a s t e m a t e r i a l and 3 preventing clogging of valves. s e a l s and f i l t e r s by w a s t e m a t e r i a l Waste collection p r o c e s s i n g and s t o r. age h a s in g e n e r a l received much l e s s than i t s s h a r e of development a t t e n. 3 1 4 P r e s s u r e Suits, The r e s t r i c t i o n s of s t a t e o f t h e a r t p r e s s u r e s u i t s a r e w e l l r e c o g. nized by m o s t vehicle s y s t e m s developers A considerable amount of de. velopment e f f o r t is d i r e c t e d toward improving this situation by developing. a b e t t e r softsuit and development of a hardsuit Assuming this develop. m e n t effort continues and is successful the p r i m a r y remaining problem. is one of s u i t life The longer duration m i s s i o n s of the MOBEX vehicles. with g r e a t e r EVA p l a c e a s e v e r e s t r a i n on the life of suit joints s e a l s. c a b l e s h o s e s gloves and the p r e s s u r e s h e l l itself The c u r r e n t suit. development p r o g r a m should be broadened to include increasing suit life. and r e s i s t a n c e to damage,3 1 5 P o r t a b l e Life Support Systems.
One of the m o s t c r i t i c a l operations in a m i s s i o n is the exchange of. the P U S during a s o r t i e Mission r e q u i r e m e n t s dictate that this exchange. be m a d e on the l u n a r s u r f a c e by a single a s t r o n a u t The p r e s e n t PLSS and. s p a c e s u i t designs do not p e r m i t this exchange thus s e v e r a l modifications. a r e n e c e s s a r y on the PLSS A dual connector fitting m u s t be developed. f o r the s u i t which would allow the oxygen connection from two P U S S to be. attached to the suit R e s e a r c h is r e q u i r e d on the sealing and disconnecting. a s p e c t s of the PLSS to this fitting n t q u i er G LC n r t h e r m l protection. during PLSS switching should be investigated, Employing the P U S exchange station f o r switching PLSSs will. r e q u i r e a longer P U S t o s u i t hose than p r e s e n t l y e x i s t s on the PLSS. P r e s s u r e d r o p and flow r a t e implications m u s t be r e e v a l u a t e d a s they. a f f e c t blower sizing,3 2 HUMAN FACTORS AND SIMULATION. In the c o u r s e of analyzing and developing the MOBEV vehicles in con. ceptual f o r m a number of human f a c t o r s a r e a s requiring f u r t h e r study have. been uncovered A brief description of f u t u r e r e s e a r c h needs and advanced. technology r e q u i r e m e n t s follows,3 2 1 L R V Simulation Needs. To d e t e r m i n e m o r e p r e c i s e l y a s t r o n a u t capabilities on the lunar. s u r f a c e a m o r e r e a l i s t i c simulation of the lunar s u r f a c e environmental. c o n s t r a i n t s is required While attempts to s i m u l a t e e l e m e n t s of the lunar. environment have been m a d e o r are underway a n integration of these. e l e m e n t s into a lunar s u r f a c e t e s t bed h a s been lacking To provide the. simulation r e a l i s m r e q u i r e d the test bed should synthesize the following. l u n a r environment elements 1 6 gravity suspension lunar illumination. l u n a r s u r f a c e c h a r a c t e r i s t i c s vacuum conditions l u n a r t h e r m a l conditions. and mockups prototypes o r simulators f o r such lunar s u r f a c e h a r d w a r e. s y s t e m s as the lunar s h e l t e r and o r lunar roving vehicles. 3 2 2 L R V Mission Simulation Studies, With the simulation tools described above time line studies should. be conducted to e s t a b l i s h performance t i m e s r e q u i r e d to accomplish s c i. entific m i s s i o n objectives and vehicle o r s h e l t e r station keeping functions. T h e s e data would be considerably m o r e a c c u r a t e than the a r m c h a i r e s t i. m a t e s available to date T h e s e e m p i r i c a l data a r e r e q u i r e d f o r a c c u r a t e. f o r m u l a t i o n of scientific objectives scientific equipment payloads and. c r e w activity scheduling,3 2 3 L F V F r e e Flight Simulation.
Definitive data a r e lacking on m a n s ability to f l y and land i n the. l u n a r environment under the constraints of lunar lighting and visual con. ditions unfamiliar s u r f a c e f e a t u r e s reduced gravity and the p r e s s u r e. s i l i t T h e LM is designed f o r a single relatively h a r d landing as c o m. p a r e d to e a r t h VTOL landings at a level unobstructed site On ihe other. hand a n exploration vehicle m u s t m a k e r e p e a t e d landings a t m a n y un. familiar s i t e s possibly on rough and difficult s u r f a c e s. F o r lack of suitable lunar flight data a conservative design a p. p r o a c h has been taken in the flying vehicles Flight instrumentation. landing stability and impact capability have been designed into the vehicle. i n e x c e s s of that usually employed on e a r t h VTOL vehicles If b e t t e r data. could b e obtained on m a n s ability to navigate control and land a s m a l l. l u n a r flying vehicle i t might be possible to m a k e design simplifications to. r e d u c e weight c o s t and development t i m e.


Related Books

The International Insolvency Review - Slaughter and May

The International Insolvency Review Slaughter and May

This second edition of The International Insolvency Review once again offers an in-depth review of market conditions and insolvency case developments in a number of key countries. Building on the first edition, coverage has been expanded to include Belgium, Greece, Jersey, Poland, Portugal, Singapore and South Africa bringing the total number

CURRICULUM VITAE: David F - David F. Chang,

CURRICULUM VITAE David F David F Chang

1 David Chang CV CURRICULUM VITAE: David F. Chang, M.D. Academic title: Clinical Professor, Department of ...

Design and Evaluation of a CMMI conformant Light-Weight ...

Design and Evaluation of a CMMI conformant Light Weight

Light-Weight Project Management Approach ... Project Monitoring and Control ... Design and Evaluation of a CMMI conformant Light-Weight Project Management Approach

Florida Department of Health 2019-2020 Annual Regulatory Plan

Florida Department of Health 2019 2020 Annual Regulatory Plan

Florida Department of Health 2019-2020 Annual Regulatory Plan Section 120.74(1)(a), Florida Statutes (2018) (1)(a) Laws enacted or amended during the previous 12 months which

FOR THE UNDERGRADUATE COURSE IN ... - maths.ox.ac.uk

FOR THE UNDERGRADUATE COURSE IN maths ox ac uk

This handbook applies to students starting the course in Michaelmas term 2018. The information in this handbook may be di?erent for students staring in other years. This handbook is intended as a guide and reference for you throughout your Mathematics and Philosophy course at Oxford. Please keep it as a handy reference guide.

CMMI for Small Business - Software Value

CMMI for Small Business Software Value

CMMI for Small Business ... Project Monitoring and Control Supplier Agreement Management ... Samples of project artifacts from current processes

Integrated Processes for CMMI Compliance

Integrated Processes for CMMI Compliance

Project Monitoring and Control ... statement and expected artifacts ... Integrated Processes for CMMI assuredcommunications ...

Finding CMMI Compliant Artifacts and A Needle In A Haystack

Finding CMMI Compliant Artifacts and A Needle In A Haystack

Finding CMMI Compliant Artifacts and A Needle In A Haystack Presented to National Defense Industrial Association ... (PP) and Project Monitoring and Control (PMC)

CENTRE (Common Enterprise Resource)

CENTRE Common Enterprise Resource

CENTRE CMMI 1.2 Artifacts for Process Improvement CENTRE CMMI Version 1.2 Compliance Project Monitoring and Control - White Paper Author ...

Treasures Unit 2 Decodable Reader - mybooklibrary.Com

Treasures Unit 2 Decodable Reader mybooklibrary Com

Treasures Unit 2 Decodable Reader ... Download or Read Online eBook treasures unit 2 decodable reader in PDF Format From The Best ... share examples of friends ...