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WI-1S-3I1 

Copy 1 

Page 1, 

C. L. Olson 

S SPECIAL HANDLIINg 

PLANNING BRIEFING 

4-12-67 

• MOL SYSTEM PLANNING OBJECTIVES 

VIABLE INITIAL PROGRAM 

FOLLOW-ON GROWTH THROUGH IMPROVED: 

O SYSTEM ECONOMICS 

O OPERATIONS. FLEXIBILITY 

O MISSION PERFORMANCE 

O ADDITIONAL APPLICATIONS (NATIONAL SPACE GOALS) 

SPIEMIL HANDLEINO 
WHS-311 

Page 2 

liIrCIFF.T.SPECIAL HANDLING. 

MOL PLANNING GUIDELINES 

NRO APPROVED FOR 

RELEASE 1 JUL niC 

• EVOLUTIONARY (NOT REVOLUTIONARY) SYSTEM CAPABILITY GROWTH. 

• PRIMARY MISSION IS HIGH RESOLUTION RECONNAISSANCE. 

• CONTINUAL EXAMINATION OF FUTURE ALTERNATIVES, TO GUIDE. 

PRESERVATION OF OPTIONS IN ONGOING PROGRAM. 

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RERELSPECOL. HAMM wpa,Figse_ 311 

WI. PLANNING ELEMENTS 

0 MAJOR MOL SYSTEM SEGMENTS 

LAUNCH VEHICLE FACILITIES 

✓ LABORATORY VEHICLE / FLIGHT CREW 

PAYLOAD / TRAINING SIMULATORS 

✓ RE-ENTRY VEHICLE I SUPPORT FORCES 

I SUPPORT MODULE 

0 TYPICAL PLANNING STUDY CONSIDERATIONS 

✓ PRELIMINARY SYSTEM DESIGN ✓ RELIABILITY ESTIMATES 

I CONFIGURATION ANALYSIS I COST ESTIMATES 

I PERFORMANCE ANALYSIS SCHEDULE CONSTRAINTS 

✓ OPERATIONS SCENARIO ✓ EFFECTIVENESS COMPARISONS. 

✓ ,CREW FUNCTIONS 

RELEASE 1 J 

SPICUIL HANDIUKI 
NRO APPROVED FOR 

RELEASE 1 JUL 

D SEEL. ElADIUNg WHS-311 

Page 4 

REVIEW OF MOL PLANNING ACTIVITIES 

ORGANIZATION AND SCOPE OF BRIEFING. 

O EARLY SYSTEM DEFINITION STUDIES (1963 - 1965) 

O RECENT SYSTEM IMPROVEMENTS AND GROWTH STUDIES ( 1965 - 1967) 

O CURRENT MOL PLANNING FRAMEWORK (1967 - 1968) 
NRO APPROVED FOR 

' RELEASE 1 

NEORETSPE: 

REVIEW OF MOL PLANNING ACTIVITIES 

ORGANIZATION AND SCOPE OF BRIEFING 

O EARLY SYSTEM DEFINITION STUDIES (1963 - 1965) 

O RECENT SYSTEM IMPROVEMENTS AND GROWTH STUDIES (1965 - 1967) 

O CURRENT MOL PLANNING FRAMEWORK (1967 - 1968) 

ARM 

WHS- 31 

Page 5 

SPECIAL 'INOUE 
NRO APPROVED FOR 

, RELEASE 1 JULY 21 15 Mr I 

4 4 G 

TYPICAL MOL PLANNING S TUDIES - 

SPECEIA 

EARLY SYSTE

HARIDU E

m wFINITION PERIOD r.. 

WHS-311 

Page 6 

LABORATORY VEHICLE 

I. 10 FT. VS 13 FT. DIAMETER 

2. AMOUNTS OF PRESSURIZED AND UNPRESSURIZED VOLUMES 

SINGLE VS DUAL PRESSURIZED COMPARTMENTS 

4. FORWARD VS AFT LOCATION OF TEST SECTION 

5. LONGITUDINAL VS TRANSVERSE CREW ORIENTATION 

6. E-BY-SIDE VS END-TO-END DOCKING MOD 

7. 1E-.."RNAL VS EXTERNAL ARTIFICIAL GRAVITY PROVISIONS 

8. LAR ARRAY VS FUEL CELL ELECTRICAL POWER] 

94 tPROVISION FOR" VS "ADD-ON" VS "BUILT-IN" APPROACH FOR RENDEZVOUS' 

FAND DOCKIN 

10, MAINTENANCE VS REDUNDANCY FOR SYSTEM EFFECTIVENE 

.11. SINGLE VS MULTI-LEVEL ATTITUDE CONTROL THRUSTERS 

:12. GEMINI VS APOLLO ATTITUDE CONTROL ELECTRONICS APPLICATION 

13. REACTION JET VS COMBINED REACTION JET/MOMENTUM STORAGE ATTITUDE 

CONTROL SYSTEM. 

14. RADIATIVE VS ABLATIVE ATTITUDE CONTROL THRUSTERS 

15. OPTIMAL ATTITUDE CONTROL JET CONFIGURATION 

16. COMBINED VS INDIVIDUAL ELECTRICAL INVERTERS/CONVERTERS/REGULATORS 

17. SEPARATE VS INTEGRAL HEAT REJECTION SYSTEM FOR ELECTRICAL POWER 

SPEC A flikNILI% 
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TYPICAL MOL PLA NING STUDIES - EARLY SYSTEM DEFINITION PERIOD Page 7 

LABORATORY VEHICLE (CONTINUED) 

18. FUEL CELL SELECTION FOR ELECTRICAL POWER 

19. USE OF AUXILIARY BATTERIES VS USE OF THE LABORATORY CENTRAL POWER SYSTEM 

FOR SPECIAL PURPOSE ELECTRICAL LOADS AND/OR EMERGENCIES 

20. SINGLE VS DUAL GAS ENVIRONMENTAL CONTROL SYSTEM 

21. 'GASEOUS VS SUPERCRITICAL ORSUBCRITICAL CRYOGENIC FLUID STORAGE 

22. • WICK ABSORBERS VS CENTRIFUGAL ROTATORS FOR HUMIDITY CONTROL 

23. LITHIUM HYDROXIDE VS MOLECULAR SIEVES FOR CO2 CONTROL 

24. RADIATOR VS WATER BOILER FOR PEAK THERMAL Lek D CONTROL 

25. ALUMINUM VS MAG-LITHIUM STRUCTURAL. MATERIALS 

26. SINGLE VS MULTI-WALL STRUCTURAL CONFIGURATIO 

27. CURVED VS FLAT PRESSURE BULKHEADS 

28.-INTEGRATED VS INDIVIDUAL COMPONENT TM/TRACK AND COMMAND 

29. COMBINED VS SEPARATE DATA MANAGEMENT FOR LABORATORY AND EXPERIMENTS 

GEMINI ti 

1. HOLE IN THE HEAT SHIELD VS INFLATABLE TUNNEL VS ROTATED GEMINI FOR 

ASTRONAUT TRANSFER 

2. ABORT TOWER VS SEAT IMPROVEMENT, ADDITIONAL REDUNDANCY, AND ADDITIONAL 

PROPULSION' FOR CREW ESCAPE 

3. RE-ENTRY GUIDANCE SYST MS VS - • CONTROL 

PECIIAIL HAMLIN 

• 

I 
SPEC.[IL 1116LEG 

TYPICAL MOL PLANNING STUDIES - EARLY SYSTEM DEFINITION PERIOD 

WHS-311 

Page 8 

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GEMINI. B (CONTINUED) 

' 4. AUTONOMOUS BATTERY OR FUEL CELL POWER VS UTILIZATION OF LABORATORY POWER 

5. USE OF A'GEMINI-A ADAPTER VS ALTERNATIVE NEW ADAPTERS 

TITAN III C 

I. ACTIVE VS PASSIVE ON-ORBIT TRANSTAGE TEMPERATURE CONTROL 

2. .ALTERNATIVE DEGREES OF REDUNDANCY FOR RELIABILITY AND SAFETY IMPROVEMENT 

3. TRANSTAGE VS NO TRANSTAGE STUDY . 

OPERATIONS/PERFORMANCE 

I. ORBIT DECAY VS CONTROLLED RE-ENTRY - VS EXPLOSIVE DESTRUCTION FOR -

LABORATORY DISPOSAL 

2. OPTIMAL DISTRIBUTION OF EXPERIMENTS PER FLIGHT AND THE SEQUENCE OF 

EXPERIMENTS CONDUCT WITHIN EACH FLIGHT 

3. INCREASED ON-ORBIT LOITER CAPABILITY FOR GEMINI B VS INCREASED RECOVERY 

FORCES 

4. QUALIFICATION OF EQUIPMENT FOR STORAGE ENVIRONMENT VS ALTERNATIVE 

METHODS OF PROVIDING AN ENVIRONMENT COMPATIBLE WITH EXISTING QUALIFICATIONS 

S. RBIT ALTITUDE SELECTION FOR RENDEZVOUS 

6. FIXED VS VARIABLE LAUNCH-AZIMUTH CAPABILITY FOR. 

7. LTERNATIVE PERFORMANCE IMPROVEMENTS FOR; TITAN III G:.VS PROGRAM COS, 

FFECTIVENESS ro,.r-si•rf% ,n t v417': I. IA CIL`, 

3rtt, AL H V ULIIVIS 
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RELEASE 1 JULY 2015 

IT-1366/8.X1,SPECIAL HANDLING WHS-311 

, Page 9 

TYPICAL MOL PLANNING STUDIES EARLY SYSTEM DEFINITION PERIOD 

OPERATIONS/PERFORMANCE (CONTINUED) 

8. TARGET DECK SIZING 

9. WEATHER ANALYSIS - ALTERNATIVE RETARGETING 

10. DETERMINATION OF MAN'S IMC PERFORMANCE 

11. SENSOR SIZING SYSTEM STUDIES - ALT/OPTICS/DRAG 

12. .OPTICAL SYSTEM STUDIES - BAKER-GREY 

13. TRACKING MIRROR VS DUMP TRUCK ANALYSIS 

14. AUTONOMOUS NAVIGATION STUDIES 

tl 

ESEGREZSPECIAL HANDLING 
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YARIDLES 

TYPICAL GROWTH-ORIENTED STUDIES 

EARLY SYSTEM DEFINITION PERIOD 

(LABORATORY VEHICLE) 

WHS-311 

Page 10 

• PRESSURIZED VOLUME AND COMPARTMENTATION 

TRADES IN VOLUME UTILIZATION, DUAL VS SINGLE COMPARTMENTS, RELATIVE 

CREW SAFETY 

• ENVIRONMENTAL CONTROL SYSTEM 

APPLICABLE, EXISTING EQUIPMENT, SINGLE OR DUAL GAS ATMOS. CO2REMOVAL 

- APPROACH DEFINED 

• ELECTRICAL POWER 

DETERMINED POWER PROFILES. FUEL CELL VS SOLAR CELL TRADES, 1000 HR FUEL 

CELL AVAILABILITY 

• STRUCTURAL CONFIGURATION 

ARRANGEMENT OF STRUCTURALLY AND THERMALLY REQUIRED MATERIAL TO 

MAXIMIZE METEOROID PROTECTION 

• ARTIFICIAL GRAVITY CONCEPTS 

EVALUATION OF SYSTEM COMPLEXITY, WEIGHT PENALTIES, DYNAMIC PROBLEMS, 

OPERATIONAL FLEXIBILITY 

• DOCKING MODES 

STUDY OF APPROACH MANEUVERS, MISALIGNMENT CONSTRAINTS, CREW/CARGO 

TRANSFER, DRAG EFFECTS 

• EXTENDED MISSION DURATION 

EVALUATION OF RENDEZVOUS OPERATIONS AND DISCRETIONARY PAYLOAD CAPABILITY 

• MAINTENANCE/REDUNDANCY OPTIMIZATION 

FAILURE MODE AND EFFECTS ANALYSIS, IN-SPACE MAINTENANCE CONSIDERATIONS, 

REDUNDANCY V SPARES TRADES, 60 DAY MISSION CAPABILITY 

Ntar[111KS 
WHS-311 

Page 1'1 

REVIEW OF MOL PLANNING ACTIVITIES 

ORGANIZATION AND SCOPE OF BRIEFING . 

O EARLY SYSTEM DEFINITION STUDIES (1963 - 1965) 

O RECENT SYSTEM IMPROVEMENTS AND GROWTH STUDIES (1965 - 1967) 

O CURRENT MOL PLANNING FRAMEWORK (1967 - 1968) 

SPECEL HAMMING 

NRO APPROVED FOR 

RELEASE 1 J 2111 
.NRO APPROVED FOR 

RELEASE 1 JULY2f15 

WHS-311 

Page' 12 D-seettT. '-gPECLAL HANDLING 

TYPICAL RECENT - PLANNING STUDIES 

SYSTEM ECONOMICS 

O LAUNCH VEHICLES & SPACECRAFT APPLICABLE TO MOL 

SATURN I AND TITAN III BOOSTERS„ APOLLO, GEMINI AND 

MOL SPACECRAFT. ETR & WTR OPERATIONS 

O EVALUATION OF ETR & WTR OPERATIONS FOR MOL 

UPRATED SATURN I AND TITAN ILI BOOSTERS, ETR AND WTR 

OPERATIONS 

O RENDEZVOUS/RESUPPLY SYSTEMS GROWTH 

CONFIGURATION DEVELOPMENT,- RENDEZVOUS AND DOCKING 

MECHANICS, OPERATING MODES, RELIABILITY CONCEPTS, 

COST BENEFIT COMPARISONS 

(60 MIN) 

(60 MIN), 

(120 MIN) 

O EXTENDED DURATION INTEGRAL LAUNCH SYSTEMS GROWTH 

50-90 DAY MISSION CAPABILITY FOR BASELINE MOL DERIVATIVES (30 MIN) 

O SUBSYSTEM LIFE EXTENSION CONCEPTS 

TRADES BETWEEN MAINTENANCE, REPLACEMENT, REPAIR. BLOCK (60 MIN) 

AND FUNCTIONAL REDUNDANCY - MEAN MISSION LIFE & SYSTEM 

AVAILABILITY 

O MAXIMUM DURATION AUTOMATIC.MODE VEHICLE 

60 DAY DESIGN LIFE AUTO MODE VEHICLE DEVELOPMENT 

GUIDELINES DEFINED 

O WHOLLY UNMANNED SYSTEM EVALUATIONS 

COST BENEFIT COMPARISONS BETWEEN OPTIMIZED WHOLLY 

UN-MANNED (WUM) SYSTEM. AND MOL FOR DORIAN MISSION 

(30 MIN) 

(90 MIN) 

SPECIAL HANDLING 
D S T SPECIAL HANDLING 

TYPICAL RECENT PLANNING STUDIES 

OPERATIONS FLEXIBILITY 

WHS-31 

Page 13 

O EVALUATION OF SV-5 MANEUVERING RE-ENTRY VEHICLE FOR MOL 

MARTIN CO. PROPOSAL FOR MEDIUM HYPERSONIC L/D VEHICLE (15 MIN) 

TO BE DEVELOPED FROM PRIME CONFIGURATION 

0 MANEUVERING RE-ENTRY VEHICLE TEST ON MOL AUTO-MODE FLIGHTS 

FEASIBILITY INVESTIGATION OF FULL SCALE, UNMANNED PROTOTYPE (20 MIN) 

LIFTING BODY FLIGHT TEST ON MOL DEVELOPMENT FLIGHTS 6 & 7 

O MAN'S CONTRIBUTION TO MOL MISSION EFFECTIVENESS 

ACTIVE TARGET INDICATORS, WEATHER AVOIDANCE, WEATHER (120 MIN) 

VERIFICATION, PRECISION NAVIGATION FOR TARGET ACQUISITION, 

IMPROVEMENT BY MAINTENANCE/REPLACEMENT/REPAIR 

O ORBITAL RESCUE AND ESCAPE 

ESTIMATE OF RISK THAT CREW BE STRANDED IN ORBIT, AND EVALUATION 130 MIN) 

OF VARIOUS MEANS TO REDUCE HAZARD 

O CONTINGENCY PLANNING ALTERNATIVES 

ANALYSIS OF BACK-UP HARDWARE COSTS AND LEAD TIMES FOR (10 MIN) 

FLIGHTS 1 AND 2, AND FOR OPTIONAL USE OF M/AM OR AM 

CONFIGURATIONS FOR FLIGHTS 6 AND 7 

O POSSIBLE FOLLOW-ON VEHICLE MIX 

FISCAL FUNDING ANALYSIS OF LEAD TIMES AND COSTS FOR A RANGE (10 MIN) 

OF "CARBON COPY" FOLLOW-ON BUYS. 

O "CONVERSION" VS "SUBSTITUTION" M/AM -- AM 

STUDY OF DECISION LEAD TIME AND COSTS FOR VARIOUS APPROACHES (15 MIN) 

TO OPTIONAL CHOICE OF M/AM OR AM FLIGHT CONFIGURATIONS 

D SPEC 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
WHS- 311 11"* \ 

Page 14 

(30 MIN) 

(20 MIN), 

(20 MIN) 

ET SPECIAL HANDLING 

TYPICAL RECENT PLANNING STUDIES 

MISSION PERFORMANCE 

. 0 ADVANCED (GROWTH) PAYLOAD 

FEASIBILITY AND CHARACTERISTICS OF ADVANCED OPTICAL 

SYSTEM RESOLUTION) 

o SYSTEM ROUGH SIZING: FOCAL LENGTH. APERTURE 

o CONFIGURATIONS: TRACKING MIRROR. POINTING TELESCOPE. 

FOLDED OPTICS 

DEVELOPMENT/FABRICATION OF LARGE MIRRORS 

Ni LARGE CONTROL MOMENT GYROS 

FLIGHT VEHICLE CONFIGURATION ANALYSIS 

O COMPLIMENTARY PAYLOAD ELEMENTS 

POSSIBLE ENHANCEMENT OF BASELINE HIGH RESOLUTION OPTICS 

SYSTEM BY "ADD-ON" DETECTION/ACQUISTION SENSORS. SENSOR 

EQUIPMENT AND VEHICLE INTEGRATION REQUIREMENTS 

o ELECTRONIC POINTING SYSTEM (ELINT) 

o FORWARD LOOKING RADAR 

O BASELINE PAYLOAD ENHANCEMENT 

o POINTING AND TRACKING SCOPE ALTERNATIVES 

o EXTENSION OF CAPABILITY FOR AUTOMATIC IMC 

o SINGLE VERSUS DUAL CAMERA/FILM LOADING STUDIES 

NRO APPROVED FOR 

RELEASE 1 JUIY201E 

ir"JSCJ&E:&SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY. 

HANDLING 

TYPICAL RECENT PLANNING STUDIES 

ADDITIONAL APPLICATIONS 

O NAV-MOL SYSTEM 

MOL VEHICLE SYSTEM + NAVY PAYLOADS FOR OCEAN SURVEILLANCE 

O SAA 209/MOL EXPERIMENTS PLANNING 

MAN-EQUIPMENT EXPERIMENTS UNIQUE TO MOL, FLOWN ON NASA 

S-IV B "ORBITAL WORKSHOP. " EVALUATE PROCEDURES, MAINTENANCE. 

TOOLS, CREW RESTRAINTS, 

O SELECTED MOL/GEMINI-B DATA FOR AAP 

PERFORMANCE, CONFIGURATION, SUBSYSTEMS DATA, INCLUDING 

GROWTH POTENTIAL FOR INTEGRAL LAUNCH AND RENDEZVOUS. 

REQUESTED BY NASA. 

WHS-311 

Page 15 

(IS MIN) 

(20 MIN) 

(TOR 

REPORT) ' 

(20 MIN) 

O ASTRONOMY 

POTENTIAL FOR BASELINE SENSOR TO PHOTOGRAPH NEAR PLANETS: (30 MIN) 

MODIFICATIONS FOR STELLAR PHOTOGRAPHY 

O BIO- MOL CONCEPT (PSAC) 

MOL VEHICLES FOR PROLONGED BIO-MED TEST, COMBINED WITH 

DOD MISSION OR SEPARATE FLIGHTS. 

O MOL VARIANTS FOR NASA APPLICATIONS "A" + BIO-TEST MISSION 

ACCOMMODATE 14 METEOROLOGICAL EXPERIMENTS ON SEPARATE 

FLIGHT OR PIGGYBACK ON BASELINE VEHICLES. 

(60 MIN) 

(60 MIN) 

Trnelikra_SPECIAL HANDLING 
DiEGREE1P EMU HANDLONG WHS-311 

Page 16 

A MOL SHORT RANGE PLANNING STUDY EXAMPLE 

"FOLLOW-ON SYSTEM ANALYSIS" 

w • 

PEVIAL HANDLIIKG 

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RELEASE 1 JU 
NIRO APPROVED FOR /8 

• RELEASE 1 JULY 2015 (D) S - SPECIAL HANDLING 

30 FT. 

WHS-311 

Page 17 

POINTING CASSEGRAIN CONFIGURATION 

CAMERA ACCESS 

TUNNEL CMG's 

U 

YOKE ROLL 

BEARING 

LAB MODULE 

BARREL PITCH AXIS 

(DrSZSAF,Z: SPECIAL HANDLING 

• 
SPIEMM HANORIG 

POSSIBLE VOL LAUNCH VEHICLE EVOLUTION 

NEW 

SO 

(15 66) 

SAME' 

STAGE I 

SAME_ 

SOLIDS 

SAME 

SOLIDS 

SAME 

STAGE I 

NEW 

STAGE I 

O O 0630 

T- III EXPANDED 

MOL , STAGE I 

EXPANDED 

STAGE U 

156" 

SOLIDS 

1.A A I A 

SAME NEW__ 

TAGE STAGE II 

SAME .01. 

STAGE II 

BASIC 

P/L (1300110/130) 32.000 

STEP I 

440 46. 000 

STE II • STEP III 

48 — 53.000 706• 80. 000 

VENAL HANALEg WHS-311%%\ 

Page 18 

NRO APPROVED FOR 

RELEASE 1 JUL 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

4. 

Vol }-210LEING 

EXTENDED DURATION INTEGRAL LAUNCH 

ORBITING VEHICLE 

WHS- 311 

• .Page 19 71\ 

MM 

T III LDC I CAPABILITY ia90°, 80/180 N. MI 

—30 

VEHICLE 

LAUNCH 

WEIGHT, W 

(1, 000 LBS) 

UNPRESSURIZED 

COMPART MENT 

LENGTH, L 

(FT) 

10 20 30 50 

MISSION DURATION • DAYS 

1111r0 
D SPECIAL NITITLIHR 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 2o 40 

EXTENDED DURATION INTEGRAL LAUNCH 

ORBITING VEHICLE 

(SO DAY MISSION DURATION), 

SPEER MEM „Page 20 

WE 1 S-31 

:11 AI Al • 

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• wf-ter vit'2Thit ■:... As° 

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40•40.- 

EXTENDED 

GEMINI B DURATION LABORATORY .- — 

COMPARTMEN MODULE 

MISSION 

MODULE 
WHS-311 

Page 21 

NIRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPEcm11.1111E1 

KnIPPL Y S Y &TWA CONCEPT 
.1■1 RO APPROV 

RELEASE 1 Y 2015 

WHOLLY UNMANNED VEHICLE - TM 7 SEG BOOSTER 

CONTROL 

MODULE MISSION MODULE 

MISSION 

SUPPORT 

• MODULE 

FLIGHT 

DIRECTION 

ON-ORBIT 

(=> 

ATTITUDE CONTROL NOZZLES (16) 

SOLAR PANEL (ERECTED) 

ATTITUDE CONTROL GAS (6) 

l*B 

••■•.„, 

SECTION A.A loA 

PROPELLANT 

TANKS (4) 

BACK-UP THRUSTERS (2) 

PRIMARY THRUSTER 

RE-ENTRY VEHICLES 

EQUIPMENT BAY 

SPECIAL HANDLING 

A4CLAL HANDLING 

WHS-311 

Page Z2 

SECTION B-B 
T-IUM 

12.7K P/L 

30 DAY 

RENDEZVOUS 

RESUPPLY 

1 

1.4 

A 

a RRV 

T-II1M12. 7K P/L 

CONTINUOUS 

OPERATION . 

60 DAY 

RESUPPLY 

CYCLE 

.4=1111■11w 

LDC 1 - 7 SEG SRM 

12. 7K P/L - 50 DAY 

NRO APPROVED FOR 

RELEASE 1 JULY_21:11c 

GROWTH AVENUES 

DICRETSPICE_. 

WHS-311 

Page 23 

RIV 

A RRV 

T-IIDA 20. 8K P/L 

CONTINUOUS 

OPERATION. 

60 DAY 

RESUPPLY 

top CYCLE 

gams01•1■■ •1111111111•11M 

T-III LDC 1 lk 2..7 SEG SAM 

20. 8K P/L - 60 DAY 

• 

BASIC MANNED SYSTEMS 

MOL WHOLLY 

PROGRAM UNMANNED SYSTEM 

T-111/A 12. 7K P/L 

85 DAY DESIGN WUM 

(58 DAY MMD) 

-4 

10! 

4 

ti 
SCOPE SPIEMIL HANDLIIRTI • WHS-311 

Page 24 

RESUPPLY SYSTEM STUDIES 

• RENDEZVOUS OPERATING MODES 

RENDEZVOUS MECHANICS 

VEHICLE SIZING ANALYSIS 

VEHICLE CONFIGURATION DEVELOPMENT 

• DOCKING MECHANICS 

• PERFORMANCE ESTIMATES 

• ATTAINMENT OF EXTENDED DURATION 

• BASELINE HARDWARE IMPLICATIONS 

• OPERATIONS ASPECTS 

t• 

• GROUND, OPERATIONS IMPLICATIONS 

POSSIBLE RENDEZVOUS GROWTH WITH MINIMUM 

BASELINE IMPACT 

• SYSTEM COST AND BENEFIT COMPARISONS 

SPIEMIL Di 14 

a 

NRO APPROVED FOR 

RELEASE 1 JU 
..4 

NRO APPROVED FOR ) 

RELEA 

WHS- 3117'4\ 

Page 25 

.110.1■ ....J 

A -0.1 

LAUNCH VEHICLE CAPABILITY FOR 1 = 96.4° 

OFF-LOADING RATE 

60 DAY DESIGN 

0 

(.0) pl .40 

O 

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(RRV) 

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SUPPLY MODULE 10' UPPLY 

DURATION.... DAYS 

SPECI1AL 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 Cies' u 

T...... . 2ECIAL HANDLING ‘ - WHS- 311.41‘6\ 

RENDEZVOUS/RESUPPLY VEHICLE SIZING APPROACH 

O FIXED VEHICLE ELEMENTS 

GEMIM B 

i RENDEZVOUS PROPELLANT AND TANKAGE 

,..THRUSTERS + Q STRUCTURE 

DOCKING HARDWARE 

TIME DEPENDENT VEHICLE ELEMENTS 

CRYOGENIC STORAGE 

PROPELLANT STORAGE AND PRESSURIZATION 

// FUEL CELLS AND POWER DISTRIBUTION 

.1 PERSONNEL (FOOD, CLOTHING, MEDICAL, ETC.) 

ENVIRONMENTAL CONTROL (ATMOSPHERE) 

SPARES 

DATA RETURN VEHICLES AND FILM 

UNPRESSURIZED HOUSING STRUCTURE AND 

CREW TUNNEL EXTENSION 

■111•111111M1111■111111111111111•Or 

Page 26 
SPECIAL HAMS 

YAKIBUN3 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

."INCICJPECIA 

25-13‘4.) 5 

WHS-117.4\ 

Page 27 

VEHICLE GROWTH EQUATION 

(RIM 

• VARIABLE VEHICLE ITEM, 

a " + + 

+ + +4. 

4;ry 4:rProp.Sys. TrEPS 4EC/LS 4Psrsonnol Data • Spasms Crew Tunnel 

17.2 + (1.46 at 10.4) WvAV +(24 + 40. 3 LB/KW-DAY)+ 15.87 + 5.7 + 63.8 + 6.0 + 4.I 

as 138 + 40. 3 LB/KW-DAY + (1.46 at 10"'S WvzHQV 

NOTE: HOUSING STRUCTURE INCLUDED WERE APPLICABLE 
RELEASE 1 JULY 2015 

NIRO APPROVED FOR ' Sub 230 

SPZCIE RIRle\lidi.11E2 

WHS-311 

Page 28 

RESUPPLY VEHICLE DESIGN 

• GEMINI B + CREW St EQUIP. 6, 450 

• SUPPLY MODULE (ZERO DAY) 

ACTS (THRUSTERS, TANKS, SUPPORTS) 1, 850 

DOCKING HARDWARE 230 

FUEL CELL (1) + DISTRIBUTION 290 

RENDEZVOUS RADAR (GEMINI B) 90 

HOUSING STRUCTURE (e..4..5') 75 

PROPELLANTS (RENDEZVOUS) 2, 300 

.• 

CONTINGENCY (DRY WGT 20%) 970 

TOTAL 12,225 LBS.. 

• 60 DAY GROWTH 0 293 LBS/DAY 17, 580 

TOTAL VEHICLE WEIGHT 

4P 

29,805 LDS 

OFF-LOADING RATE 

PROPELLANT (O. K. + LIMIT CYC. ) 75 

• EPS (1.63 KW-AVG.) 3S 

DA TA 55 

EC/LS + PERSONNEL 13 

SPARES , 6 

111111.1■10 

TOTAL 184 LBS/DAY 

SFECIAL rOLING 
WHS-311 

Page 29, 

600., 

gui 400 

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200 

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RRV/RLV*322 

NRO APPROVED FOR 

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J 

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VEHICLE DRAG CHARACTERISTICS AND 

—151i61511191XWMILMOTREAWIS--- 

0 5 1 0 1 0 

TOTAL VEHICLE LENGTH (L) FT. 

0 20,000 40,000 60,000 - 

AVERAGE VEHICLE WEIGHT (W) LDS 

SPE EN. NA OLEG 
BASELINE AM VEHICLE 

pt. rm nrAtvit PN 0 0 A WA 

WHS- 31114441 \ 

Page 30 1. PECIAL HANDLING 

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RELEASE 1 JULY 2015 

3/4 

RENDEZVOUS RIMDIPPLIF WE CLE RENDEZVOUS EnTIAL VIRECLE 

RR EEL Dm, + FILM HANDLING 

SYSTEM 

.4. 1EXTENDED 

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UNPRESSURIZED 

COMPARTMENT 

• ADD BASELINE SUBSYSTEM 

COMPONENTS 

• ADD DOCKING YSTEM AND 

INTERFACE 

O DELETE GEMINI B 

• ADD EXTENDED DURATION 

PROVISIONS 

• ADD DOCKING SYSTEM AND 

INTERFACE 

• ADD ASCENT FAIRING 

SPECIAL HANDLING 

BASELINE MIAM VEHICLE 
CREW 

• T CNN LII2TANK 

px.11:115URANT 

TANK STORAGE 

COMPARTMENT 

& CREW TUNNEL PROPELLANT 

TANK 

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PROPELLANT 

TANK 

CREW 

TUNNEL 

• FILM 

CHUTE 

TANK 

DRV 

FUEL 

CELL 

TANK. 

PRESSURANT 

TANK Fi LM 

CHUTE 

VIEW A VIEW VIEW C 

•••• R EZVOUS • 

INITIAL 

VEICCLE 

D .-igt*F.ZSPECIAL HANDLING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

WHS-311. 

Page 31 

SE T SPECIAL HANDLING 
RENDEZVOUS ORBITING VEHICLE CONCEPT 

WHS- 311 

Page 32 

RENDEZVOUS 

INITIAL • 

VEHICLE 

DOCKING AND SEPARATION 

PLANE 

RENDEZVOUS 

RESUPPLY 

VEHICLE 

NRO APP FOR 

RELEA 1 JULY 2015 

*sew wk. 

4 

RRV FUNCTIONS 

• CREW TRANSPORT VEHICLE 

• ACTS PROPULSION 

• PRIME POWER SYSTEM 

• LIFE SUPPORT EXPENDABLES 

• DATA RETURN SYSTEM 

• SUBSYSTEM SPARES/REPLACEMENTS 

D 

RIV FUNCTIONS 

• LIFE SUPPORT SYSTEM 

• ATTITUDE CONTROL REFERENCE/ 

ELECTRONICS 

• COMMUNICATIONS AND DATA HANDLING 

• ENVIRONMENTAL CONTROL 

• HRO SYSTEM 

SPECUL NIADURG 
NRO APPROVED FOR 

RELEASE 1.JUI.Y.2015 • . 

L 

SPECIAL, HANDLING 

ZS Jun. 1966 

WHS-311 

Page 33 

DOCKING SYSTEM/INTERFACE CONCEPT 

CREW 

TUNNEL 

MATING SEQUENCE: 

I. DISSIPATE DOCKING ENERGY 

& STABILIZE STRUCTURE 

2. INDEX & LOCK STRUCTURE; 

TUNNEL 

3. MATE MECHANIZED 

UMBILICAL CONNECTIONS 

4. PERFORM FUNCTIONAL CHIC. 

S. OPERATE 

ALIGNMENT.' 

PINS (2) 

TV TARGET TV CAMERA (2) 

EARTH UMBILICAL 

1° 

CONNECTOR • ELECTRICAL POWER 

• COMMUNICATIONS 

LIFE FILM TRANSPORT CHUTE • WATER 

• 

0

2 ER 

INSTRUMENTATION 

• ACTS CONTROL SIGNAL 

SPECIA 1 HANDLING 
NR& APPROVED FOR 

RELEASE 1 JULY 2015 

NECRVsPEEL Mr 12 

CONCEPT OF EXTENDED LIFE SYSTEMS 

COMPLETE REPLACEMENT EACH RESUPPLY CYCLE 

I FUEL CELLS 

.CRYOGENIC TANKAGE 

THRUST CHAMBER ASSY. 

1/ PROPELLANT TANKS/FUEL SYSTEMS 

WHS- 311 

, Page 34 

INTENSE APPLICATION OF SPARES FOR MANNED MAINTENANCE/ 

REPAIRS/REPLACEMENT. 

UTILIZATION OF MAN IN TROUBLE-SHOOTER ROLE 

ELIMINATION OF MAJOR EQUIPMENT PROBLEMS DURING INITIAL 

MOL DEVELOPMNT PROGRAM. 

SPECIAL nuldipLIING 1. 
NRO APPROVED FOR 

RELEASE 1 uLy2g15 D ksPE'1L YLLMLAU V■THS- 311 

RENDEZVOUS ORBITING VEHICLE VAILABILITY FOR LONG DURATION 'Page 35 

SYSTEM UP 

SYSTEM DOWN 

1.00 

. 90 

PROBABILITY 

OF SYSTEM . 80 

BEING OUT OF 

••fr# COMMISSION 

.30 

.20 

.10 

I 

$ a I 

11 I 

I 

LJ 1 

I 

1 

SYSTEM DOWN DURING n 

DOCKING 11. MOORING .4 L.JSYSTEM DOWN FOR REPAIR 

(TYPICAL EACH RRV 'AFTER MAJOR FAILURE. CYCLE) 

PROBABILITY OF 

FAILURE INCREASE" 

DUE TO-CHECKOUT II 

IF NO CHECKOUT 

MADE I 

I s 

II 

II I 

• I II " 

Ar /5 ✓ 

) 

I Iv j 

/ 

k 

I I 

/. 

DopmcpirricT 

V

/ 

EFFECT. OF REPLACEMENT 

BY RESUPPLY 

EFFECT OF UNIMPROVABLES 

120 180 240 300 

MIE4I2N TIME FROM INITIAL. f.AUNCH_ DAY§ 

DERE SVECIIAL 

360 
NRO APPROVED FOR 

RELE4SE 1 JULY 2015 

PEC1111. NAHOUNG WHS-311 

Page 36 

EARLY RESUPPLY FOLLOW-ON PROGRAM ESTIMATED COSTS 

NON-RECURRING 

• RRV DEV. 67. 5 

DESIGN/INT EGRATION 50.0 

/ HARDWARE 17.5 

• DOCKING SYSTEM DEVELOPMENT 

• RIV DESIGN/INTEGRATION 

• ROV INTEGRATION/TEST 

• LAUNCH SITE REQUIREMENTS 

• ADDITIONAL PRODUCTION FACILITY 

AND FACTORY AGE (RRV) 

ID MISSION SIMULATOR MODS 

18. 5 

18. 0 

12.0 

142. 5 

10. 0 

5.0 

TOTAL M$ 273. 5 

PEC1111 HANDLING 
31 NRO APPROVED FOR 

IISEC SPECM1 

RELEASE 1 JULY 2015 

Er 

RRV DESIGN AND INTEGRATION Page 37 

age 37 417'4'4\ 311

ESTIMATED COST IN $1000 

ENG'R DESIGN 

$ 3000/MM 

MEN MAN- MON FOR 18 MON DE V. TEST QUAL, TEST 

• EXTENDED DURATION 20 360 1,080 1,500 ' 1,500 

MODULE STRUCTURE 

• , PROPULSION SYSTEM 15 270 810 1.000 1.500 

'INSTALLATION 

O POWER SYSTEM 15 270 810 1,000 , 1.500 

INSTALLATION 

• CRYOGENIC TANKAGE 15 270 .810 1.000 1,500 

INSTALLATION 

O CARGO COMPARTMENT 10 . 180 540 800 1.000 

& CREW TUNNEL 

• DOCKING SYSTEM 10 180 • 540 

INSTALLATION 

O ACQUISITION AIDS . 20 360 1.080 1.000 1.500 

INSTALLATION 

0.DATA SYS. INSTALLATION 20 360 1.080 1.500 2.000 

• DOCKING PLANE INTER 20 360 . 1.080 1.500 2.000 

CONNECTX)NS 

• GEMINI B INTEGRATION 45* 810 2,500 4.000 5.500 

& LIFE EXT. 

• UNPRESSURIZED COMPART■ 15 270 810 1.000 . 1.500 

MEN T DESIGN/INTEGRATION 

• SYSTEMS INTEGRATION 30 540 1,620 .. lb a I*.. 

• SIMULATION & TRAINING 20 360 1.080 2.000 

13,840 16,300 

MI QIN, OD Mb 

255 4,590 

Mb fl• 

411•1■111•111•11111010 

19.500 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PEEL NMI JIG WKS-311 

Page 38 

RRV GROUND TEST HARDWARE 

(RESUPPLY MODULE) 

M$ 

0 

. / 

/ 

QUALIFICATION TEST UNIT (COMPLETE SET) 

STRUCTURAL TEST UNIT 

11. 8 

5. 7 

STRUCTURE & CREW TUNNEL 1.0 

PROPELLANT TANKS/FEED 1.4 

CRYOGENIC TANKS . 9 

FUEL CELLS (SIMULATED) . 3 

DATA SYSTEM (SIMULATED UNITS) . 7 

DOCKING SYSTEM 4 

VEHICLE ASSEMBLY & CHECK OUT 1. 0 

TOTAL HRDWR COST 17. 5 

SPECIIM HAMBURG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

"D7 nrit-KZ_SPECIAL HANDLING WHS-311s 

Page 39 

RENDEZVOUS/RESUPPLY MODULE RECURRING COST ESTIMATE 

MILLIONS OF DOLLARS 

O STRUCTURE SHELL 1. 0 

SHELL 0. 8 

INTERIOR SUPPORT 0. 2 

ACTS Z. 2 

TCA/ LOGIC 1.0 

O EPS 

/ PROPELLANT TANKS/ 1.2 MANIFOLDS, VALVES, ETC. 3. 4 

CRYOGENIC TANKAGE 1. 6 

/ FUEL CELLS (5) 1. 5 

/ CONTROLS/DISTRIBUTION 0. 3 

O THERMAL CONTROL 0. 2 

O COMMUNICATIONS/TRACKING 0. 2 

O INSTRUMENTATION 0. 2 

® DATA RETURN SYSTEM 1. 8 

/ FILM TRANSPORT & DRV SUPPORT 0. 3 

DRV'S (6) 1.5 

O DOCKING SYSTEM 0. 4 

O SPARES COMPLIMENT (60 DAY) 1. 0 

O VEHICLE ASSEMBLY/CHECKOUT 1. 4 

TOTAL 11. 8 

IIDII SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 32- 13J 

SPECM HANDLING 

DOCKING SUBSYSTEM DEVELOPMENT 

.W,HS- 311 

Page- 40 

ESTIMATED COST IN $1000 

DESIGN DEVEL, TEST gUAL; TEST TOTALS 

• RRV MECHANISM (ACTIVE) 2, 500 2, 500 2.500 7.500: 

ENGAGEMENT & CAPTURE 

DEVICE ACTUATING SYS. , 

CONTROLS. SENSORS ALIGNMENT DEVICE ' 

• RIV MECHANISM (PASSIVE) 2, 000 , 2, 000 2.000 6.000 

ENGAGEMENT & CAPTURE. 

DEVICE ACTUATING SYS. , 

CONTROLS, SENSORS ALIGNMENT DEVICE 

• SYSTEM INTEGRATION 1,000 • • • OP 1.000 

• SIMULATION 500 --- --- . ' • 500 

DISPLAY (CRT) EQUIP FOR 500 

DOCKING 

MODIFY NASA SIMULATOR 1.000 1.500 

• MISSION CONTROL 2 000 , 2.000 

•011.01111.0.1•01111• awavaNeNMIIN■11 MIN11■1.10.01111. 

3,500 6, 000 4, 500 4, 500 18, 500 

REFERENCE: 

• AGENA TARGET DOCKING ADAPTER (TOTAL PROGRAM COST: INCLUDES STRUCTURE, 

ELECTRICAL, ELECTRONICS: AND 7 SETS OF FLIGHT HARDWARE) ry 10 MS 

• PASSIVE TARGET VEHICLE (TOTA C6TI INCLUDES ALL HARDWARE DEV, PLUS 

2 FLIGHT ARTICLES) $ 427, 000 

PAL rl L. I PIS] 

r‘ r . n 
• - NRO APPROVED FOR 

RELEASE 1 JULY 2015 

.1-1.ANI.E1 3 Page 41 ' 

WHS-311 

RENDEZVOUS INITIAL VEHICLE 

(NON-RECURRING COST ESTIMATE) 

• 

O DOCKING SYSTEM INSTALLATION i 

•• • INTERCONNECTION INSTALLATION 

(DESIGN + FLUID & ELECT. DEV.) 

• TUNNEL HOOKUP 

(DESIGN St INSTALL - DEV.) 

• DATA HANDLING 

(DESIGN & INSTAL - DEV.) 

• INTERDOCK SYSTEM 

- ATTITUDE CONTROL ("MINIMUM" TYPE) 

DESIGN 

• 1,000 /s. 

D. T. , Q. T. 

200 0 0 

1.000 1,500 • 600. 

200 , 300 . 400 

1,000 300 600 

1,500 * 1,000 1,500 

- POWER SYSTEM 

• AUTOMATIC SYSTEM 

(INITIAL & INTERDOCK REQ.) 

NOSE CONE 

(DESIGN & INSTALL - DEV.) 

TOTAL COST (INCLUDING HARDWARE) 

LAB EXTENDED LIFE TEST 

TOTAL 

200 300 

200 200 

200 400 . 

4, 500 4, 000 

5, 000 

181 000 K,$ 

. 400 

600 

300 

4, 500 

SPEC11/1 HANDLIING 
L NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIIA1 HAMM 

EARLY RESUPPLY FOLLOW-ON PROGRAM ESTIMATED COSTS 

LAUNCH SITE REQUIREMENTS * 

FACILITIES 

0. 5 

0.5 

TOTALS 

• LCC MODS 

PAD , #1 MODS 

• PAD #2 NEW 15. 5 

• SUPPORT AREAS MODS 4.0 20.9 

• 

AGE 

• LCC . 58.0 

PAD 01 5. 0 

• PAD #2 S6.0 119.0 

OTHER 

• TV/COMM 2.0 

• SYSTEMS ENG/INTEG. 1.0 3.0 

TOTAL COST 142.5 

SAME RATIONAL AND COSTING AS "MOL LAUNCH FACILITIES OPTIONS'. 

STUDY (PLAN 01), DATED 15 FEBRUARY 1967 

D)feRg SP(ECIA11. ORIN 

WHS-311 

Page 4Z 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HANDLING WHS-311 

Page 4S 

EARLY RESUPPLY FOLLOW-ON PROGRAM ESTIMATED COSTS 

RECURRING 

• RIV 

UNIT TOTAL/ LAUNCH 

(MO) (M$) 

69. 4 

HARDWARE (62.3) 

e T- IIIM 14. 5 

o LAB VEHICLE 23. 3 

o MISSION PAYLOAD 22. 0 

o MISC. - NOSECONE 

- AUX. ACTS 2. 5 

- DOCKING & INTERFACE 

O&M (7.1) 

o LAUNCH SERVICES 5.1 

o TRACKING 1.0 

o FLIGHT OPS & SUPPORT 1. 0 

• 

RRV 

HARDWARE (41.3) 

e T- HIM 14. 5 

• 

RRV MODULE 11. 8 

o GEMINI 14. 0 

o PRESS. SUITS, ETC. 1.0 

%, 0 & M ' 9: 0) 

o LAUNCH SERVICES - PRIMARY 3. 1 

o - BACK- UP 1. 3 

o RECOVERY/ TRACKING 1.8 

o FLIGHT OPS. & SUPPORT 1. 8 

o CREW TRAINING 1. 0 

SPECIAL A No 

56.5 
NRO APPROVED FOR 

RELEASE 

FISCAL FUNDING ESTIMATE FORA RESUPPLY FOLLOW-ON OPTION 

WHS-311 

Page. 44 

CY 

FY 

71 72 73 74 75 76 68 I 69 70 

69 70 71 72 73 74 . 75 76 

0 BASELINE PROGRAM XX 0 0 0 El 

0 EARLY RESUPPLY FOLLOW-ON PROGRAM ii-"P"--" 1ST LAUNCH 

• 800 

710 709 

=

6 

Zti 

56 

650 606 

600 

CONTINUING RENDEZVOUS 

PROGRAM 

;FISCAL 

FUNDING 

(M$) 400 

327 

200 

105 

1' I 
3(10 

Page 45 '474 

WHS- 311 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HANDLIHR 

I 71 

85.0 

265.0 

4.0 

354.0 

69.0 • 9.5 

311.0 313.9 101.8 

5.0 4.0 3.0 

385.0 327.4 104.8 

7S [ .76 

71.3 8.2 

2.0 1.0 

a•11••••111.0111•1011 

73.3 .9.2 

72 T 73 74 1 

EARLY RESUPPLY FOLLOW-ON PROGRAM ESTIMATED COSTS 

FISCAL FUNDING 

(MILLIONTOTIr 

. 

FY 69 70 

STUDIES 6.0 

NOTi-RECURRING 111.0 

RECURRING 88.0 

GSE/TD 1.0 

YEARLY TOTAL 6.0 200.0 

t• 

SPECEIAL YAKOLING. 
NEGREMEVIR HANDLIM 

REVIEW OF MOL PLANNING ACTIVITIES 

ORGANIZATION AND SCOPE OF BRIEFING 

0 EARLY SYSTEM DEFINITION STUDIES (1963 - 1965) 

0 RECENT SYSTEM IMPROVEMENTS AND GROWTH STUDIES (1965 - 1967) 

0.. CURRENT MOL PLANNING FRAMEWORK (1967 - 1968)1 

( 

WHS-31.1 .."44 

Page 46 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
NRO APPROVED FOR 

RELEASE 1 J ( v "1' Pao" 

"D::..SrefanPECIAL HANDLING WHS-311 

Page 41 • 

MOL GROWTH OBJECTIVES 

• IMPROVED SYSTEM ECONOMICS 

INCREASED MISSION DURATION 

I EXTENDED UTILIZATION OF SYSTEM SEGMENTS, 

• IMPROVED OPERATIONAL FLEXIBILITY 

RECALL/REPEATER CAPABILITY 

CREW NUMBER INCREASE 

I ORBITAL ASSEMBLY 

ORBITAL STORAGE 

r. VULNERABILITY COUNTERMEASURES 

• IMPROVED MISSION PERFORMANCE 

BASELINE P/L CAPABILITY 

HIGHER RESOLUTION P/L 

ADDITIONAL/COMPLIMENTARY P/L ELEMENTS 

DATA RECOVERY TECHNIQUES 

• ADDITIONAL APPLICATIONS OF MOL HARDWARE TO 

DOD/NASA NATIONAL SPACE GOALS 
CY I 70 • 71 72 73 74 7.5 

de' Sip' 

-ffror 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 Ow SPEC HANTTING W HS - 311 

Page 48 

POSSIBLE MO L PLANNING FRAMEWORK 

• ANNUAL COVERAGE 

0 00 DO 

MOL DEVELOPMENT 

I A.... 

••••••••••••••••••• 

1 ' I 

RESUPPLY SYSTEM 

30% '"7""••••411+•■ ""100 % 

• PAYLOAD ELEMENTS BASIC PAYLOAD 

AD VANC 

 PAY LOA 

ADDITIONAL _4 

P/ L ELEMENTS 

UP 

• LABORATORY SUBSYSTEM BASELINE RATED "I" 

• REENTRY VEHICLES GEMINI B 0111••••11 4■11111011111•M •11111•11111■ •■•■■■•■•■ 

EARLIEST MRV 

• LAUNCH VEHICLES $ T.- M 

moor. orld. - Opp 

oloro arum era. soll/pfr 

I Lac ? 
NRO APPROVED FOR 

RELEASE 

MOL SYSTEM SHORT RANGE PLANNING ACTIVITIES 

IN HOUSE STUDIES FY-68 

WHS-311 

Page 49 

INITIAL FOLLOW-ON MIX 

• FLT. FREQUENCY ALTERNATIVES 

• MANNED & AUTO FLIGHTS 

• FOLLOW ON PROGRAM TIMING 

• COST ESTIMATES 

• LEAD TIME & FUNDING REQMTS. 

RENDEZVOUS/RESUPPLY 

• DAC 'CONTRACT (5 MOS. STUDY) 

• OPERATIONS MECHANICS (ALTERNATIVES) 

• DOCKING DYNAMICS 

• DESIGN EVALUATION 

SYSTEM LIFE EXTENSION 

• MAN'S ROLE IN REPAIR/DIAGNOSIS 

• • EFFECTIVENESS MODEL EXTENSION 

• ACCESSIBILITY STUDIES 

DATA MANAGEMENT/RECOVERY VEHICLES 

(FOLLOW-ON APPLICATIONS) 

sa 

• MULTI DATA•RECOVERY-VEHICLE 

• WIDE-BAND LINK 

• VEHICLE SYSTEM IMPACT 

ADVANCED PAYLOAD 4 TECHNOLOGY 

• MIRROR MATERIAL & FABRICATION' 

• NAVIGATION ACCURACY REQMTS. 

• MAN VS AUTOMATED FUNCTIONS 

• CONTROL MOMENT GYRO DEVELOPMENT 

• FORMAT SIZE AND CAMERA REQMTS 

• FILM TRANSPORT 4 HANDLING 

IMPACT OF ADVANCED P/L ON MOL 

SYSTEM DESIGN/PERFORMANCE 

• STRUCTURAL DESIGN 

• SYSTEM DYNAMICS 

• NAVIGATION SYSTEM REQMTS 

• ATTITUDE CONTROL REQMTS 

• ELECTRICAL POWER SYSTEM 

• LABORATORY CONFIGURATION CHANGES 

• SYSTEM PERFORMANCE 

• LAUNCH VEHICLE REQMTS 

• OPERATIONS (ALTERNATIVES, MAN'S. 

CONTRIBUTION) 

• PRODUCTION FLOW 

• P/L-LABORATORY INTEGRATION 

COMPLIMENTARY PAYLOADS 

(FOLLOW-ON) . 

• ELINT, IR. FWD. 4 SIDE LOOK RADAR, LASER 

VULNERABILITY/SURVIVABILITY 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

WHS-311 

.Page 50- 

SPECIAL HANDLING 

MOL SYSTEM SHORT RANGE PLANNING ACTIVITIES 

/N-HOUSE STUDIES FY-68 (CONT.) 

GEMINI B IMPROVEMENTS STUDIES 

• LAND LANDING 

• REFURBISHMENT/RE-USE 

• STRANDING HAZARD REDUCTION 

• ORBIT STORAGE LIFE EXTENSION 

• CREW SIZE INCREASE • 

OTHER DOD/NASA APPLICATIONS 

• EXTENDED BIO-TEST 

• EARTH SENSOR COMPLEX 

• ASTRONOMY/SPACE PHYSICS 

• ORBITAL ASSEMBLY 

• DOD P/S EXPERIMENTS 

MANEUVERING RE-ENTRY VEHICLE STATUS REVIEW - ADVANCED 

APPLICATIONS- • SUBSYSTEMS TECHNOLOGY 

• SYSTEM REQUIREMENTS (MISSION) 0 ELECTRICAL POWER 

• CONFIGURATION DEVELOPMENT • PROPULSION 

• FLIGHT SYSTEM INTEGRATION • GUIDANCE 81 ATTITUDE CONTROL 

• PERFORMANCE ANALYSIS • • NAVIGATION 

• DEVELOPMENT CYCLE (TEST FLOW) • LIFE SUPPORT 

.• OPERATIONS • THERMAL. CONTROL 

FUTURE MOL VEHICLE SYS. PLANNING 

"60 DAY" AUTO MODE VEHICLE 

IMPLEMENTATION 

• SCHEDULE At COST ESTIMATE 

• TEST REQUIREMENTS 

PECIAL HANDLING 
NRO APPROVED FOR 

RELEASLI JULY 2O1 

J 1 

SPTC[1/1 NAKBLON1 WHS-311 

Page 51 

MOL SHORT RANGE PLANNING REVIEW 

SUMMARY/CONCLUSIONS 

O PLANNING EFFORTS HAVE CONTRIBUTED TO ESTABLISHING 

• A VIABLE PROGRAM 

0* LOGICAL AVENUES OF SYSTEM GROWTH HAVE BEEN 

DEFINED AND PROTECTED 

O A PLANNING BASELINE HAS BEEN ESTABLISHED 

O SHORT TERM PLANNING TASKS HAVE BEEN IDENTIFIED 

SPECDU HAKOLLING 
NRO APPROVED FOR 

(SE REL 1 JULY 2015 

■ 

POSSIBLE UTILIZATION OF MOL HARDWARE 

FOR LONG DURATION BIOASTRONAUTICS TEST MISSIONS 

t• 

SPEC[111 MEM 

SPEC WHS- 311 

Page 52 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

At HAULMS 

POTENTIAL APPROACHES FOR BIOASTRONAUTIC TESTING 

60 TO 90 DAY DURATION 

INTEGRAL LAUNCH MODE - SINGLE OR DUAL COMPARTMENT 

MODULE 

A DURATIONS EXCEEDING 90 DAYS 

RENDEZVOUS MODE - 4 MAN DUAL COMPARTMENT LABORATORY 

CONFIGURATION • 

2 MAN DUAL COMPARTMENT LABORATORY CONFIGURATION 

(COMBINED MISSION) 

WHS-311 

Page 53 

SPECfiAL NtInkiING 
NRO APPROVED FOR 

SE 1 JULY 2015 

40 

WHS-311 

Page 54 

ZTR 

INTEGRAL LAUNCH DUAL COMPARTMENT LABORATORY 

(CONFIGURATION AND PERFORMANCE) 

CONFIGURATION 

ACTS THRUSTO 

MODULES (4) 

AVAILABLE 

FOR MISSION EXTENDIBLF 

EQUIPMENT TUNNEL 

LH

z TANKS (2) 

LO TANKS (2) 

ACTS. FUEL 

TANKS(4) 

CTS PRESSURANT 

TANKS (4) 

 72.0' 

FUEL 

SP CE F6R°1;4° 

ENTRIFUGE 

‘--AVAILABLE 

 22 

MA AK 41111■ , 

1111/01011/A,Ver 

TC10 

H, TANKS (6) 

LO2 TANKS (6) 

10. 

He TANKS 

CELLS (3) 

(3) 

FOR PAYLOAD 

PERFORMANCE 

TOTAL PRESSURIZED VOLUME (SHIRT SLEEVE ENVIRONMENT) 

AVAILABLE PRESSURIZED VOLUME FOR CREW 

AVAILABLE PRESSURIZED VOLUME FOR EXPERIMENT EQUIPMENT 

AVAILABLE UNPRESSURIZED VOLUME FOR EXPERIMENT EQUIPMENT 

EXPERIMENT PAYLOAD CAPACITY (ETA, t s 2$. so, 100 N M CIR) 

(WTR, I a ie. ISO N Irt CIR) 

. ELECTRICAL. POWER (AVERAGE) 

MISSION DURATION 

*INCLUDES 200 WATTS FOR EXPERIMENTS 

SPIEUAL LINKING 

2.000 FT3 

1.200 FT3 

400 FT3 

"." 700 FT3 

AA • 000 LB 

ow 000 LB 

4 4 450 :WATTS* 

90 DAYS 
NRO APPROVED FOR 

RELEASE' Y 

I 

SPECIAL HAMM 

APPROACH TO INTEGRAL LAUNCH EXTENDED DURATION ' 

WHS-311 

Page 55 

• PROPULSION 

PROPELLANTS 

TANKAGE 

• PRIME POWER 

. • CRYOGENICS 

FLUID (L02, L 

TANKAGE 

• PERSONNEL PROVISIONS 

FOOD & PERSONAL GEAR 

• SUBSYSTEM SPARES 

30 DAY 

MOL BASELINE 

(80/160 N MI ORBIT, 1=80°) 

2.000 LBS 

4 FUEL + 4 0=3. 

3 FUEL CELLS 

1,650 WATTS 

1.330 1.433 

2 L02 + 2 LH2 + 1 H 

• 

148 LBS 

160 LBS 

90 DAY 

EXTENDED LAIkATION VEHICLE * 

(180 N MI CIR. ORBIT, 13280u) 

1.450 LBS 

4 FUEL + 4 OXID. 

6 FUEL CELLS 

I, 650 WATTS 

5,320 LBS 

8 L02 + 8 LH2

+ 4 H

e 

443 LBS 

410 LBS 

*DUAL COMPARTMENT LABORATORY 

MOON. Tr MMHG 
• •NRO•APPROVED FOR 

RELEA 

• SPECIE. Ifiat.LINg WHS-311 

Page 56 

• 

• 

MISSION DURATIONS EXCEEDING 90 DAYS 

(RENDEZVOUS) 

• . 

• 

• 
a (4. 4) 

LH2 TANKS (5) 

LO2 TANKS (5) 

ACTS FUEL AVAILABLE FOR. 

TANKS (6) PAYLOAD 

~ILENDEZVOUS RESUPPLY VEHICLE 

(CONFIGURATION AND PERFORMANCE) 

o CONFIGURATION 

• 02 ACCUM. 

TANKS (4) 

DOCKING MECHANISM 

(ACTIVE) . 

ACTS THRUSTOR 

MODULES (4) ACTS PRESSURANT 

,TANKS (6) REW TRANSFER 

TUNNEL 

10.0' 

43. V- 

• 6 PERFORMANCE 

NRO APPR 

REL 1 JULY 2015 MU. HARM WHS- 311 

Page 57 

UNPRESSURIZED VOLUME FOR EXPERIMENT EQUIPMENT 

EXPERIMENT PAYLOAD CAPACITY (WTR, i a .80°, 180 N M CIR) 

ELECTRICAL POWER (AVERAGE) 

RESUPPLY CYCLE (TO SUPPLY 4 MAN CREW) 

*200 WATTS AVAILABLE FOR EXPERIMENTS 

2,000 FT3 

10,000 LBS 

2.000 WATTS* 

60 DAYS 

SPEER. KNOLIING 

D F,OR 
* 200 WATTS AVAILABLE FOR EXPERIMENTS 

WEAL N 

Page 58 4.144\ 

WHS-311 

4 MA DUAL COMPARTMENT LABORATORY 

(CONFIGURATION AND PERFORMANCE) 

AVAILABLE FOR 

MISSION EQUIPMENT 

o CONFIGURATION 

AIM 

MOM 

DOCKING MECHANISM 

(PASSIVE) 

1 0 . 0' 

CTS PRESSURANT CREW TRANSFER 

TANKS (4) TUNNEL 

CTS THRUSTER SPARE • MODULES (4) PARTS 

N.—ACTS FUEL 

TANKS (4) 

 72.0' 

LH2 TANKS (4 

LO2 TANKS (4 

o• PERFORMANCE 

TOTAL PRESSURIZED VOLUME (SHIRT SLEEVE ENVIRONMENT) 

AVAILABLE PRESSURIZED VOLUME FOR CREW 

AVAILABLE PRESSURIZED VOLUME FOR EXPERIMENT EQUIPMENT 

AVAILABLE UNPRESSURIZED VOLUME FOR EXPERIMENT EQUIPMENT 

EXPERIMENT PAYLOAD CAPACITY (WTR, i a 80°. 180 N M CIR) 

ELECTRICAL POWER (AVERAGE) 

RESUPPLY CYCLE 

2,000 FT3 

1,200 FT3 

600 FT 3 

950 FT3 

5,700 LBS 

2,000 WATTS* 

60 DAYS - 

NRO APPROVED FOR 

DOCKING MECHANISM 

(PASSIVE) 

AVAILABLE FOR 

PAYLOAD 

R HaELIING LY•11911=■-•••■ 
10,000 

3 

1148,Q00 

• 

t1. 1 

O 

6, 000 od 

4, 000 

60 70 80 90 

RESUPPLY CYCLE TIME4ft, DAYS 

*DISCRETIONARY PAYLOAD = BOOSTER CAPABILITY LESS WEIGHT OF LOADED RRV 

NRO APPROVED FOR 

(ELS

• Abt 1 JULY 2015 D SP= -71 NANDLIING WHS- 311 

Page 59 

RESUPPLY VEHICLE DISCRETIONARY PAYLOAD 

ROV DISCRETIONARY PAYLOAD 

(60 DAY EXPENDABLES) 

ETR = 10, 200° (i = 28. 5°, 180 NM CIR) 

WTR = 5, 700# (i = 80°, 180 NM CIR) 

14, 000 

12, 000 ETR 

= 28. 5°, 180 NM CM 

WTR 

= 80°, 180 NM CIR. 

SPECIIA11. RANDLIKG 
• 

iATFIS- 3.11 

Page 60 

NROAPPROVED FO 

.RELASrl JULY r 5 

MAN DUAL CdMPARTMERGEARBE 6oRATORY CONFIGURATION • 

ONO 011•1■•••■ 11111•11 01110 1 Imme elmIN MOM WNW NM OP" 

RENDEZVOUS 

RESUPPLY VEHICLE 

(My) 

(COMBINED MISSION) 

RENDEZVOUS INITTALIVEHICES 

• . (RtV) . 

is POSSIBLE CREW 

TRANSFER FROM 

SUBSEQUENT RAY'S 

RRV FUNCTIONS 

• CREW TRANSPORT VEHICLE 

• ACTS PROPULSION 

• PRIME POWER 

• LIFE SUPPORT EXPENDABLES 

• DATA RETURN SYSTEM 

r SUBSYSTEM SPARES/REPLACEMENTS 

• 

• 

• 

• to 

• 

RI V FUNCTIONS 

LIFE SUPPORT SYSTEM 

ATTITUDE CONTROL REF, ELECTRONICS 

COMMUNICATIONS AND DATA HANDLING 

ENVIRONMENTAL CONTROL 

PERFORMANCE DATA 
.NRO APPROVED FOR 

RELEASE 1 JULY 2015 

:WHS- 311 

Page- 61 

9/16/66 

UTILIZATION OF MOL HARDWARE FOR 

4 MAN DUAL COMPARTMENT LABORATORY CONFIGURATION 

0 MOL BASELINE ,VEHICLE 

. . 

72' 

PRESS. 

COME..... 

MISSION 

MOD tatE 

GEMINI LABORATORY 

B MODULE ,CREW TUNNEL 

</DOCKINGSYSTEM 

(PASSIVE) 

0 RENDEZVOUS ENITtAli VEHICLE a 

• ...41r- Z PLACES 

(RIM 

41k• 

4‘CKING ADAPTER 

DOCKING PLANE 

MODIFIED 

PLANE MISSION 

MODULE 

,GEMINI 

UNPRESS 

COMPT. I 

•11■111 

DOCKING SYSTEM 

(ACTIVE) 

0 RENDEZVOUS RESUPPLY VEHICLE 

(RR V) 

• 

11111 

43.5. 

ht SPF 1,11,1n ro !fin 

s. 
MPARTMENT LABORATORY 

WHS- 311 

Page 62 4 MAN DUA 

11 10 L I IU3 

emal. ■••■ OMEN, 

.11.1* •••■■• •••■ 

•■••• 001.11.. •••■••■ •••111111. 

ONO. 01•1111. .1141••••• 40.0 41•111111. 

\ 

\ RRVI12 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

• INITIAL LAUNCH CONFIGURATION (2 MAN OPS) 

1- - %.1 

-- - 7,... 1... 

% RRV#1 

• FIRST RENDEZVOUS RESUPPLY (4 MAN OPS) 

V.16.■ ■•■•■ alams. 

RRV#I 

mmo 

■•■■ •■• •••■• yei 4111INIM 

•-■ 

• ON-ORBIT CONFIGURATION (4 MAN OPS) 

RRV FUNCTIONS 

• ACTS PROPULSION 

• PRIME ELECTRICAL POWER 

0 LIFE SUPPORT EXPENDABLES 

• EXPERIMENTS 

• SPARE EQUIPMENT 

LABORATORY FUNCTIONS 

• LIFE SUPPORT/ENVIRONMENTAL CONTROL 

• ACTS - REFERENCE 

• COMMUNICATIONS/DATA 

• BIO-MEDICAL EQUIPMENT 

• 'EXPERIMENTS 

SPECIAL HANDLIIKG 

,r,1111i'sr 
j,40;0=01.11 

V °am .111. 

NRO APPROVED FOR 

RELEASGa+JULY OM 

IM111111111."- T SPECIAL HANDLING WHS-311 

Page 63 . 

2 MAN DUAL COMPARTMENT LABORATORY 

CONFIGURATION AND PERFORMANCE SUMMARY 

(COMBINED MISSION) 

• CONFIGURATION 

107' 

RESUPPLY VEHICLE 

DOCKING & SEPARATION PLANE 

RENDEZVOUS INITIAL VEHICLE . 

(UV) 

• PERFORMANCE DATA 

TOTAL PRESSURIZED VOLUME (SHIRT SLEEVE ENVIRONMENT). 

AVAILABLE PRESSURIZED VOLUME FOR CREW 

AVAILABLE PRESSURIZED VOLUME FOR EXPERIMENT EQUIPMENT 

RrI. Y. EXP. PAYLOAD CAPACITY (i = 96. 4°, 80/180 NM) 

ELECTRICAL POWER (AVERAGE) 

RESUPPLY CYCLE 

2.060 F r3 

1.200 FT3 

210 F1'3 

3.000 LBS 

2,960 WATTS 

60 DAYS 

• 

SPECIAL HANDLING 

CLO-1000 9-27.66 
SPECIAL HANDLING 

formiaammatumaajo 

TYPICAL WORKCYCLE FOR A NORMAL DAY 

WHS-311 

Page 64 

3 4 5 6 7 8 9 10 11 12 13 14 15 16 

SJ.1•11.111.6** 

P/L ACTIVITY 

AREAS 

CREW REQ'D 

FOR P/L OPS 

READOUT 

CREW #1 

CREW• f2 

uA sr.:. Nuns. 11.',..4.^.1P,r01111:11211re ...ICSAW.11141.11= ONG=110:Nrgrntrs.13.Z.VrellertL=.. 

, Z1 ..-vZ1 

a 

REST/SLEEP 0111101111•• •••••IM UNIM■ 

DAILY SEQUENCE LOAD 

UPDATE EPHEMERIS • • 

(+ WEATHER, PROGRAMMING CHANGE 

A A • • 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 t 

CREW 01 

CREW 02 

POSSIBLE TIMES AVAILABLE FOR CREW TESTING AND VEHICLE HOUSEKEEPING 

vazeiLeminult 

MEMPIPIONDIKUSIC114090 

PECIAL HANDLING 

CLO - 1001 9 47 -66 
NRO APPROVED FOR 

RELEA ILI= 

WHS-311 

Page 65 

POTENTIAL BIOASTRONAUTICS TEST PROGRAMS 

- 4 MAN - DUAL COMPARTMENT LAB 2 MAN - DUAL COMPARTMENT LAB 

LAUNCil DUkATION 

(MONTHS) 

Og-ORBIT TEST bATA LAUNCH DURATION 

(MONTHS) 

ON-ORBIT TEST DATA 

1 & 2 2 2, 2, 2, 0, 2 1 k2 2 2, 0 2 

3. 4 4, 4. 0, 2 4 .3 4 0, 2 4 

4 6 6, 0, 2, 4 6 4 6 0, 4 2 

5- 8 8; 2, 4. 6 ' - 5 8 2, 0 6 

6 10 10, 4, 6, 8 - 6 10 4.0• 2 

7 12 12, 6, 8, 10 12, 6. 8, 10 7 12 6, 2 • 

8 & 9 14 0. 2 

10 16 0, 4 

11 18 2, 6 

12 20 0, 10 4 

13 22 2, 12 2, 12 

TEST DATA TOTALS TEST DATA TOTALS 

1 MAN X 2 MO. 5 MEN X 2 MO. 

1 MAN X 4 MO. • 2 MEN X 4 MO. 

2 MEN X 6 MO. I MAN X 6 MO. 

1 MAN X 8 MO. 1 MANX 8 MO. 

1 MAN X 10 MO. 1 MAN X 12 MO. 

1 MAN X 12 MO. 
SPIEVIAL HAMM 

COST RANGE SUMMARY - WTR 

INCREMENTS ABOVE MOL BASELINE* 

WHS-311 

Page 66 

NRO APPROVED FOR 

RE LY.4046.■ 

• NONRECURRING RECURRING TOTAL** 

PROGRAM ' COST, M$ COST, Ms COST, M$ .•‘' 

• 60 TO 90 DAY BIOASTRONAUTICS TESTING 

• MAN - DUAL COMPARTMENT LAB 

(INTEGRAL LAUNCH) 

• 1 YEAR BIOASTRONAUTICS TESTING 

• 1 YEAR PROGRAM 

4 MAN - DUAL COMPARTMENT LAB 

(INTEGRAL LAUNCH) 

• 2 YEAR COMBINED MISSION PROGRAM 

2 MAN - DUAL COMPARTMENT LAB 

(RENDEZVOUS) 

285 332 562 

515 466 981 

299 97 396 

* 2 MANNED AND 3 UNMANNED LAUNCHES PER YEAR ASSUMED FOR BASELINE 

FOLLOW-ON PROGRAM 

** NOT INCLUDING NASA PAYLOAD EltEMENTS 

D SPEC11/11 MEIN 
DESIGN MOD/TEST DESIGN 

ADD'L LAUNCH FACIL 

EtRV UNMANNED FLT. TEST 

lit MANNED RRV 

libMANNED RI V 

I LAUNCH 

I RI V 

UNMANNED RR 

[EAL-1-AiaL/LkCiail OLAUNCH 

yr 

$ 1FA& 1 ASSY II & C/01 1 

FAB ASSY I & C/O 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 i. 

'qS °A IV 

AVAILABILITY OF ALTERNATE SYSTEMS-WTR 

WHS- 311 

Page 67 

MONTH FROM 

PH II ATP ilIDIEMErff 2 MT 3 MERE 3 -ITEM till! 4 TEMIRIM,M11111?fflEn'T 

Al 

LAUNCH FACILITIESLACTIVAT.LQUI 

VEH.. ENGG. QUAL. IMTING 1 

1st M/AM I FAB _ IN &TL at dib 

L_ F.A13 I Asst_lusisl.) 

. 

INTEGRAL LAUNCH-DUAL COMPARTMENT LAB (90 DAYS) 

DES. MOD/TEST TEST 1 

1 stNASA FLT VEH. L FAB & 

ADD'L LAUNCH FACIL gCONSTR.1---AcTIVATIQN 

4-MAN DUAL COMPARTMENT LAB (RENDEZVOUS) 

DES. MOD/TEST .5'"--I5ESICT TEST 

MOL BASELINE (REFERENCE) A A • 

1st AM 

1 0 

1 

1 

A LAUNH 

ADD'L LAUNCH FACILIS'›CONU . IVATIQI:1 1 

RRV UNMANNED FLT. TEST 1 FAB 1ASSY II & C/01 1 

1 stMANNED RRV 

litMANNED RLV 

UNMANNED 

0 LAUNCHR v 

• LAUNCI1 

Ri V 

• LAUNCti 

1 

I FAB I_ ASSY It & cio I I 

,DOD 2-MAN DUAL COMPARTMENT LAB (COMBINED MISSION - RENDEZVOUS) 

AMICEM Crril-litrall 36 37 38 3 . MONTH 3 4' arra ourturrammag trzry. 

SPE'IAL HAM) FIU 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

. 

Si -A- HANDLING - 

WHS-311 

- 

Pale 68 

-.44''' 

CONCLUSION 

. • TEST DURATIONS UP TO 90 DAYS APPEAR POSSIBLE WITH 

MOL INTEGRALLAUNCH APPROACH 

• 

• MOL RENDEZVOUS APPROACHES PROVIDE FLEXIBILITY 

FOR LONGER DURATION TESTING 

• COMBINED MISSION APPROACH APPEARS PROMISING, 

BASED ON PRELIMINARY ANALYSIS 

nECRR SPEN1,11. 
SPICIM HANDLING 

NRO APPROVED FOR 

RELEASE 

REVIEW 

SHORT RANGE PLANNING ACTIVITIES 

M. O. L. S. E. O. 

12 APRIL 1967 

WHS-311 

• Page 69 

REM 
NRO APPROVED FOR 

RELEA 

...■ 

SHIM MOM -Page 70 

WHS-337""*.4\ 

• 

GROUND RULES FOR MOL AM - 7 SEGMENT WUM COMPARISON 

• ESTIMATE COSTS FOR 30 DAY DESIGNS AT ACCEPTABLE RELIABILITY 

. • PROVIDE EXPENDABLES FOR 65 DAYS (AM) AND 85 DAYS (WUM) 

• IDENTIFY WEAR-OUT PRONE COMPONENTS 

• DETERMINE APPLICABILITY OF STAND-BY REDUNDANCY OR EXTEND 

LIFE TESTING TO IDENTIFIED WEAR-OUT ITEMS 

• ESTIMATE RECURRING AND NON-RECURRING COSTS, AND MEAN 

MISSION DURATION OF THE EXTENDED LIFE SYSTEMS. 

SPECIAL lANDLUM 
ik 

.„4 

DinETSPECIIA NAME 

/ 2.r 

WHS-311 

Page 71 41\ 

NRO APPROVED FOR 

r

t I JUL7 

wHoux UNMANNED VEHICLE 

(7.31CGIMIT T•IIIC) 

O CONFIGURATION 

O SUBSYSTEM 

O WEIGHTS 

O PERFORMANCE 

O RELIABIL/TY 

O MEAN MISSION DURATION 

O COSTS 

O COST - BENEFIT COMPARISONS 

SPECfill RA110014 
PECIA-1., HANDLING ROVED FOR 

EASE 1 JULY 2015 WHS-311 

Page 72 

WHOLLY UNMANNED VEHICLE - Tra 7 SEG BOOSTER 

CONTROL 

MODULE 

MISSION 

SUPPORT 

MODULE 

FLIGHT 

DIRECTION 

ON.ORBIT 

AM AIM 4•■ AIM 

14.0' 36.0' 

 • 74.0' 

ATTITUDE CONTROL NOZZLES (16) 

SOLAR PANEL (ERECTED) 

ATTITUDE CONTROL GAS (6) 

SECTION A-A 

RE-ENTRY VEHICLES 

EQUIPMENT BAY 

SECTION B-B 
r

RELEASE 1 Y 2015 

• D ECREEEYADM IF. 

NRO APPROVED tlaR 

WEDS-311 

Page 73 

' 

-6 

• .• 
NRO APPROVED FOR 

RELEASE VerLMLITIO 

ITSECRET-SPECM.. LAIDLING P

WHS-311

Page74 

7 SEG. • WUM VEHICLE 

SUBSYSTEM SUMMARY 

• STRUCTURE CONVENTIONAL ALUMINUM 

• • ENVIRONMENTAL CONTROL PASSIVE. HEAT SINK PLUS INSULATION 

• ORBIT KEEPING PROPULSION BIPROPELLANT, PASSIVE CONTAINMENT. B

e THRUST CHAMBER. APOLLO THRUST 

CHAMBERS BACK-UP. 

• ATTITUDE CONTROL DIGITAL ELECTRONICS. ANALOGUE BACK-UP. 

REDUNDANT HEAD HORIZON SCANNER. 

REDUNDANT 3 X 2 DEGREE FREEDOM 

STRAP DOWN INERTIAL REFERENCE. 

COLD GAS STABILIZATION SYSTEM. REDUNDANT 

THRUSTERS AND PROPELLANT VALVES. 

• ELECTRICAL POWER ROLL-ORIENTED SOLAR PANELS PLUS BATTERIES 

1000 WATT AVERAGE POWER OUTPUT. 

• COMMUNICATIONS/ SGLS, WITH FUNCTIONAL AND BLOCK REDUNDANCY 

DATA MANAGEMENT 

• MISSION SUPPORT 8 DRV, 5600FILM 

• MISSION MODULE MOL AM SYSTEM 

D PEEL HAMBLIN 
NRO APPROVED FOR 

r

i rrill[77151 5 

DtZGIUMSPECIAL HANDLING 

ELECTRICAL POWER SUBSYSTEM 

WHS-311 

Page 75 

SOLAR ARRAY CHARACTERISTICS 

380 FT TOTAL AREA 

1000 WATTS AVERAGE POWER 

SPECIAL HANDLING 
NRO AP DFOR 

ASE 1 JULY 2015 lyfteSEZ,SPECIAL HANDLING WHS-311 

Page 76 

ELECTRICAL POWER SUMMARY 

SUBSYSTEM AVE. POWER - WATTS 

. ATTITUDE CONTROL AND TRANSLATION 

ELECTRONICS 0 

PROPULSION 

130 

50 

ENVIRONMENTAL CONTROL 30 

commumcwrioNsPritAcaucommAND 12 

INSTRUMENTATION $5 

DATA MANAGEMENT 41 

ELECTRICAL POWER CONTROL/DISTRIBUTION SO 

SUBTOTAL CONTROL MODULE 405 

MISSION MODULE AND COMPUTATION 567 

MISSION/SUPPORT MODULE 25 

SUBTOTAL MISSION PAYLOAD 0 592 

TOTAL ORBITING VEHICLE 997 

SPECIAL NAKOLING 
DUAL RANGE 

YAW REGULATOR 

ROLL 

ROLL ATT. AID 

12aCKATTA--074.715 

ROLL (ROLLRATE.;DIGITAL 

PITCH 4 PITCH RATEAUTOPILOT 

--« 

YAW RATE,, 

EIGHT COMMITTED LATCHED SOLENOID THRUSTERS GAS ISOLATION VALVES 

SWF ——071 ST ORAGE 

RESERVE 

GAS STORAGE 

FILL VALVE 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

D....SW.R-ErIPECIAL HANDLING WHS-311 

Page 77 

ACTS ELECTRONICS AND STABILIZATION SUBSYSTEM 

HORIZON 

SENSOR 

(AD V.000 

4 HEADS 

DUAL 

ELECTR) 

ANALOG 

AUTOPILOTICt 

ROLL AAT 

prrcH,JEITCH RATA, 

 YAW RATE 

L YAW 

- -1PITCH ATT1 

COLD GAS 

ATTITUDE 

STABILIZATION 

SUBSYSTEM 

SWIM •■=11.•11•110 AM" .11•01. OMNI •ON110 Web 0/10 J 

ROLL ATT. 

ti 

STRAP DOWN INERTIAL REFERENCE ASSY. 

(3) TWO-DEGREE OF FREEDOM GYROS 

BACK-UP UNIT CARRIED IN STAND-BY MODE 

SWITCH COMPLETE UNIT BY GROUND 

COMMAND IF NECESSARY 

EIGHT 

THRUSTERS 

LEGR&T--SPECIAL HANDLING 
SPECIAL HANDLING, 

r NRO APPROVED FOR 

TEASE 1 JULI2015 

WHS-311 

Page 78 

--SEelirET,,SPECIAL HANDLING 

PROPULSION SUBSYSTEM 

FILL VALVE 

• 

PRESSURE 

VALVES. 

RELIEF? 

VALVE - 

CHARACTERISTICS 

• BIPROPELLANT • 

• 280 SEC ISP MINIMUM 

• 1,114 LB DRY WEIGHT 

• 7, 464 LB LOADED WEIGHT 

PROPELLANT TANKS 

• EQUAL VOLUME - 44".DIA. 

TITANIUM- 

• PASSIVE CONTAINMENT 

VALVES 

• QUAD REDUNDANT, OX, FUEL 

N

2 (PRIMARY ENGINE) 

• DUAL REDUNDANT, OX, FUEL 

+ N2 (BACKUP ENGINES) 

PRIMARY THRUST CHAMBERS 

* 0 BELL AERO 

RE-ENTRY PROPULSION SYSTEM, 

MINUTEMAN III (1 YR QUAL) 

* • COLUMBIUM-RADIATION COOLED 

• 300 LB THRUST 

• 10" DIA X 23" LENGTH 

BACK-UP 

• TWO I00# APOLLO ENGINES 

CHECK 

VALVES 

B T. C. A. 
MULTIPLEX 

COMMUTATE 

A/D CONVERT 

4_4 1 

MULTIPLEX 

COMMUTATE 

A/D CONVERT 

••■■■••••••••••••••■=11111aL 1/11•MNIII••••••■134 

• SGLS DECRY 

RECEIVERS 

MIllowwimallr H ■ 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

WHS-311. 

go mui UNICATIONVDATA MANAGEMENT SUBSYSTEM (TT&C) Page 79 

CONTROL MODULEI I MISSION MODULE & 

L DATA gyPPT MODULE DATA 

I.(RP' (14* 

• ■••••••••••••ormi 

iv* 

SGLS 

X-HITTERS 

DIGITAL 

T/M UNIT & 

CRYPTO 

TIM 

RECORDER 

DATA 

ADAPTER 

UNITS 

(RI 

CLOCK 

oferoommond 

(8/ 

COMPUTER 

I. 

(R) 

DECODER 

CONTROLLERS 

(R) a REDUNDANT EQUIPMENT 

Moe FUNCTIONAL REDUNDANCY 

SPECIAL HAMM 

/ I 

TRELAY 1 TIME 

I DRIVES 11DRIVES 

CONTROL] MISSION I 

MODULE if MODULE Si 

SUPPORT 

I" I. • 
NRO APPROVED FOR 

L D'ECRErSPECE1 HANDING WHS-311 

Page 80 

■ 

WEIGHTS 

REL 
••■ 

NRO APPROVED FOR 

REL 

■ SPECIAL HANDLING WHS- 311 

- Page 81 WEIGHT SUMMARY 

85 DAY DESIGN LIFE, 8 DRY 

7 SEG. WUM VEHICLE 

80 NM, 900i 

ITEM SUPPORT MODULE CONTROL MODULE MISSION MODULE TOTAL VEHICLE 

. 

DRY WEIGHT 4 574 4,711 8, 380 ' 17, 665 

-INO troNTrRGENcy) _ _ MIIP■ N■ 

CONTINGENCY 592 1, 413 1, 680 3, 685. 

DRY WEIGHT WITH 4, 366 6, 124 10,___ _ 060 20, 550 •■••••■••••••••■ ••■•■•■• MI=1••■•■• --....—. CONTINGENCY 

RESIDUALS 762 762 

PROPELLANT 400 400 

PRESSURANT 252 252 

ATTITUDE CONTROL . 110 110 

GAS 

EMPTY WEIGHT — _ 

4066 6,886 10, 060 ' 21,312 

• EXPENDABLES 88 

-- 

8, 883 --, 

8, 883 

ORBIT KEEPING 6. 350 6, 350 

PROPELLANT . 

ATTITUDE CONTROL 1, 970 1, 970 

GAS 

t. 

DE-ORBIT • 475 475 

PROPELLANT 

CAMERA 88 88 88 

PRESSURIZING GAS 

TOTAL 254 15,681 060 30,995 

SeCECEV—IPECIAL HANDLING 
15 

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t:, 
NRO APPROVED FOR 

WHS- 311 

Page 86 PECK MHOLMR 

VEHICLE WEIGHT COMPARISON 

MODULE. 

AM 

(6 MAY) 

12, 546 

WUM 

(5 SEC:15 DAY) 

.IMP MO. 

WUM 

(7 SEC-85 DAY) 

• 

LABORATORY VEHICLE • OP 

CONTROL MODULE -- 6, 330 14, 268 

MISSION SUPPORT MODULE 7,753 3,040 4, 662 

MISSION MODULE 7, 355 8, 380 8,380 

TOTAL* 27,654 17,750 27, 310 . 

*CONTINGENCY WGT FOR GROWTH NOT INCLUDED 

SPECIAL X1 {I 

n'4 
NRO APEP-Laugr' cry 

REL SE 1 JULY 2015 

SPEC HAMM WHS- 311 

Page 87 

PERFORMANCE 

It 

• %. 
PECIAL HANDLING WHS-311 

Page 88 

SUNLIGHT CONSIDERATIONS 

i. • 900 

. 60 

50 

9 JUNE 

9 FL N..2.11 AUG 

Ne-7 SEPT Ns%. 

"N..... Ns. 

N 

N 10 LAUNCH DAY • I JAN 

NRO ARP VED.F.OR 

RELE9 1 JULY 2015 
4 

NRO APPROVED FOR 

RELEASE LU V .71-. 4 a 

, SPECIAL HANDLING • WHS- 311 .446\ 

- Page 89 

•••••ftElf714-Fhp•T- SPECIAL HANDLING 
( 

WHS- 311 

Page 90 QUM 

• N. 

a 68 LB/DAY 

21 LB /DAY 

WUM PERFORMANCE 

• PROPELLANT RATES 

gig (PROPULSION) 

rw(STABILIZATION) 

TOTAL (INCLUDING 10% CONTINGENCY) a 98 LB/DAY 

MISSION DURATION 

a 8, 320 LBS. 

85 DAYS 

AVAILABLE PROPELLANT 

DURATION (8, 320 ÷ 98) 

I. 

SPECIALHANDLIM 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

••••' 

/fit° 1'1 
NRO APPR 1V_1 FOR 

RELE 1 JULY 201 

EMAIL HAN WHS- 311 

.Page 91 

70/170, Na 16 

80/187, N a 16 

1 

68 72 76 80 84 88 

W/CDA 
LEASE 1 JULY 2015 WHS-311 

Page 92 
NR FOR 

ELEASE 1 JULY 2015 

. D HarilliNG WHS-311 

Page 93 

MEAN MISSION DURATION 

KEMAL HANDLING 
.J 

• 

T SPECIAL HANDLING 

WHS-311 

Page 94 

NRO APPROVED FOR 

RELE JULY fo15 

7-SEGMENT WUM 

PERFORMANCE SUMMARY 

(80/180N. ) 

ORBIT INCLINATION, DEG.' 90 97 

NUMBER OF D. R. V. 'it 8 7 

MAXIMUM MISSION DURATION, DAYS 85 81. 

*MEAN MISSION DURATION, DAYS 

FILM USE RATE, LL'/DAY 

*INCLUDES BOOSTER R 

a ERELPECIAL HANDLING 
SPECUL HANDUNO 

.• 

WHS-311 

Pb.gp 95 

NRO APPROVED FOR 

REL 

VEHICLE RELIABILITY ESTIMATES (30 DAYS) 

SUBSYSTEM MOL AM '7 SEG. WUM 

'EPS 

THERMAL CONTROL 

.998 

. 999 

.995 

.9999 

CRYO . 999 MI OP 

ACTS - P .996 .998 • 

ACTS'- E • .995 .999 

COMMUNICATIONS . 960 . . 985 

COMPUTER . 985 .985 

MALFUNCTION CORRECTION/CONTROL .940 .960 

STRUCT/RADIATOR 

LAB VEHICLE SEGMENT 

CONTROL MODULE 0 

MISSION MODULE 

SUPPORT MODULE 

. 999 .9999 

. 880 

re me 

. 869 

924 

.869 

TOTAL 

SPECOAL INDLIIKG 
8/24/66 

WHS-311 

Pam 96 

Gar 

,MEAN MISSION DURATION 

r. 

O 

2 

NRO APPROVED FOR 

SIMPLIFIED RELIABILITY MODEL - STANDBY REDUNDANCY 

DESIGN 

LIFE, DAYS 

RELIABILITY FOR 30 DAY DESIGN LIFE 
WHS-311 

Page '97. 

8/24/66 

90 - 

DESIGN 

LIFE, DAYS 

90 

70 70. 

60 

,s 

20 • 

10 - 

.7 1.0 

RELIABILITY FOR 30 DAY DESIGN LIFE 

gl;i11 1116.-SPEC AL hiANKIN. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

MEAN MISSION DURATION 

MOL - AM 

COMPUTER MODEL 
Propellant 

Valves,(2) 

Cold Gas 

Valves (2) 

Press. Switch (2) 

Solar Panel 

Actuator (2) 

Pump (2) 

Torquer 

Mirror Bearing 

IMC Mechanism 

Thermal Door Mech. 

CM, MM 

CM 

CM 

• CM 

CM 

*- CM 

CM 

CM 

CM 

CM 

MM 

MM 

MM 

MM 

2040 hr. 

2040 hr. 

I. S hr. 

2040 hr. 

2040 hr. 

<100 eye. 

80, 000 cyc 

300,000 cyc 

"e10 steps 

2040 hr. 

680 br/40, 800 

680 hr/40. 800 

• hr/40, 800 

20.400 cyc 

Gyro (2) 

Horiz. 

Sensor(2) 

Bi-Pro 

Thruster (2) 

Tape Recorders (2) 

Batteries (2) 

4 

NRO APPROVED FOR 

RELEA JULY 2015 

7-SEGMENT WUM WHS-311 

TIME/CYCLE SENSITIVE COMPONENTS Page 98 

Estimated 

Wearout Life 

• Wearout Life 

Mission Life R rnt 

8000 hr. 3.9 

> 1 yr. 4. 3 

> 6 hr. > 4.0 (3) 

6570 hr. 3.2 

Z yr. 8.6 - 

( 41- 30% depth of 

discharge) 

>100,000 cyc. Large 

3 yr. Large 

3 yr. 12.9 

cyc 3 yr. .38.6 

cyc 3 yr. 38.6 

cyc >150,000 cyc 3.7 

>150,000 cyc 7.4 

Vehicle Nominal Mission 

Cssmnsril Sse merit Life Rqmt (1) 

Bearing deiradation 

Flexure fatigue 

Throat or injector 

erosion • 

Bearing degradation... 

drive belt fatigue,' 

tape wear 

Separator 

destruction 

Seat galling 

Linkage wear 

Bearing degradation 

Bearing degradation 

Bearing degradation 

Linkage wear 

Linkage wear 

Nature of Wearout 

>300,000 cyc. 3. 8 Seat galling 

1, 000.000 cyc. 3. 3 Diaphram failure 

(1) Orbital Operation Only 

Q) Redundant in CM 

(3) Vendor Estimate, BeT. C. A. D----"-SeGlitfaSPECIAL HANDLING 
NRO APPROVED ‘,11( 

REL E 1 JULY 2015 

WHS-311 

7 - SEG. WM.:- spEcyL Icams Page 99 

TYPICAL DISTRIBUTION FUNCTIONS OF CESSATION OF SUBSYSTEM OPERATION 

DUE TO WEAROUT AND/OR STORES DEPLETION 

, 

' SUBSYSTEM AFFECTED 

BY STORES 

DEPLETION 

(EXPENDABLES) 

SUBSYSTEM AFFECTED 

BY WEAROUT 

NUMBER OF 

- A GIVEN 

SUBSYSTEM 

CEASING , 

OPERATION 

ECK NAMING iJ 

MEAN MISSION 

DURATION 

VEHICLE 

DESIGN LIFE 

t

D. L. t+ E tW. 0. 

(",4 tp. L.) 

tMMD 

(", 1/ 2 tp.) 

TIME 
t

.1:17E7A 4 11=145 

1. SPECOAIL ___Diu WHS-31 

Page 100 
NRO APPROVED FOR 

REL JULY 2015 

r. 

WHS-311' SPIECIIAL HARDLINE Page 101 

COST SUMMARY COMPARISONS 

NONRECURRING 

OCV 

MISSION PAYLOAD 

LAUNCH VEHICLE 

LAUNCH FACILITY 

GSE/ TD 

OTHER 

SUBTOTAL 

RECURRING 

OCV 

MISSION PAYLOAD 

LAUNCH VEHICLE 

RECOVERY, TRACKING 

OTHER 

SUBTOTAL 

TOTAL PROGRAM 

OCV 

•-• MISSION PAYLOAD 

LAUNCH VEHICLE 

RECOVERY, TRACKING 

LAUNCH FACILITY 

GSE/ TD 

OTHER 

• TOTAL PROGRAM 

10 FLIGHT PROGRAM 

7 SEGMENT WUM 

6 FLIGHTS 

351. 4 , 

270.1 

142.0* 

26.0 

789. 5 

141.8 

147. 4 

102.0 

44.0 

395.2 

473.2 

417.5 

244.0 

24. 0 

2'6.0 

ONIMPIMINNOMM.1.■11 

1,,„184 7 

1•1•■••■••■•••■• 

1 4 48 . 3 

5 SEGMENT WUM 

6 FLIGHTS • • 

344. 4 

Z70. 1 

42. 8 

78. 0 

26. 0 

.1111• •111 

761. 3 

III. 0 

140. 4 

56. 4 

16.2 

324. 0 

455. 4 

410.5 

99.2 

16.2 

78. 0 

26.0' 

1,085.3 

1,120 

DESIGN FOR EXTENDED 

DURATION + LIFE TESTING 

MOL 

5 FLIGHTS 

716.8 

285.5 

206. 9* 

46.2 • 

16.5 

,1,271.9 

220. 1 

137. 0 

105.0 

9.0 

8. 4 

479. 5 

936..9 

422.5 

311. 9 

9.0 

46. 2 

24. 9 

1,751.4 

33. 6 

1,785.0 

* INCL. FACILITY COSTS, BUT DOES NOT INCL. $37.1M OF T-III LINE FUNDS. 

QICIAL NANDUNC 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PIM WHS-311 

• 'Page 102 

RECURRING COST COMPARISON 

(DOLLARS IN MILLIONS) 

ITEM 

WUM 

• r. 

BASELINE MOL 

7 SEGMENT 5 SEGMENT AM 

LABORATORY VEHICLE 33.5(• 1) 53. 7( 2) 

CONTROL MODULE • 20.3 18.5 - .1 Oa • 

MISSION EQUIPMENT 24.6 .23.4 24.0 27.0 

LAUNCH VEHICLE 17.0 9.4 21.0 21.0 

RECOVERY. TRACKING 4.0 2.7 2.7 4.0 

TOTAL 65.9 54.0 81. 2 105. T 

t. 

(1) INCLUDES SUPPORT MODULE @ 4. OM 

(2) INCLUDES GEMINI @ $19.2 M 

CELE 
NRO APPROVED FOR 

r

t I JULY 

ocv 

SPECEL EINEM 

, COMPARISON OF 7 SEGMENT AND 5 SEGMENT WUM 

RECURRING COSTS IN MILLIONS 

CONTROL MODULE 

SUPPORT MODULE 

STRUCTURE 

MISSION MODULE 

STRUCTURE 

FAIRING 

18.74 17.2 

Q. 50 

0.80 

0.25 

MISSION PAYLOAD 24.60 

MISSION MODULE 

EQUIPMENT 

SUPPORT MODULE 

EQUIPMENT 

LAUNCH VEHICLE 17.600 

RECOVERY 2.00 

FLIGHT OPERATION SUPPORT 2.00 

TOTAL 65.89 

SPECIAL RAMBLING 

20.6 

4.0 

23.4 

20.6 

2.8 

9.4 

1. 5 

1.2 

54. 0 

WHS-311 

Page 103, 

• .7, 

D 

7 SEGMENT 5 SEGMENT 

20.29 18.50 

0.50 

0.80 
JDW n/1/66 

WHS- 311 ---.....Z. / 

Page 104 

COST COMPARISON 

7 SEGMENT & ,5 SEGMENT WUM 

MAJOR SYSTEM 

‘DOLLARS IN THOUSANDS) 

ELEUGHT-EapGRAM:--. 

NON-RECURRING RECURRING 

7 SEGMENT 5 SEGMENT SEGMENT 5 SEGMENT 

OCV 

CONTROL MODULE & FAIRING 345,000 338,000 114,000 103,200. 

MISSION MODULE STRUCTURE 3,400 3,400 4,800 4,800 

SUPPORT MODULE STRUCTURE 3,000 3,000 3,000 3,000 

TOTAL OCV 381,400 344,400 121,800 111,000 

.MISSION PAYLOAD 

EQUIPMENT 245,000 245,000 123,400 123,400 

FACILITIES 13,100 13,100 

SUPPORT MODULE EQUIP. 12,000 12,000 24,000 17,000 

TOTAL PAYLOAD 270,100 270,100 147,400 140,400 

SPECIAIL HANfili !NIG 

NRO VE 

EASE 1 JULY 2015 SPEC1141 MOM 
WHS- 311 

Page 105 

81.6 

10.d 

 72. 5 

. • to. o 

6.0 6.0 

3.. 0 3.0 

' 2.4 - 2. 4. 

8. 1 7. 9 

-OD. . 

. MR - 

.....4.0 1N• MO OP . 

1. 5 * 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

COST COMPARISON - CONTROL MODULE 7 SEGMENT & 5 SEGMENT WUM 

NON-RECURRING 

7 Segment 5 Segment 

MANAGEMENT ' 15.0 15.0 - 

SYSTEM ENGINEERING 30.0 30.0 

MODULE DESIGN '. 172.0 177.9 

FLIGHT HARDWARE --- --- 

AGE 54.9 60. 0 ' 

OV TEST AND LAUNCH 6.8' , 6.8 

ON ORBIT SUPPORT 1.5'• 1.5. 

FLIGHT EVALUATION 1.2 • 1:2 

LOGISTICS & SPARES. 3.5 • 3.5 

TEST MODELS 34.6 34:6 

INTEGRATION 7.5 7.5 

FAIRING . 8.0 * 

ADDED CONFIDENCE 10.0 

TESTING FOR WEAR-OUT 

TOTAL 345.0 338.0 114.0 103.2 

* INCLUDED IN MODULE DESIGN AND FLIGHT HARDWARE COSTS 

SPECIAL RAMBLING 

DOLLARS IN MILLIONS 

RECURRING (6 FLT. PROGO 

7 Segment ' 5' Segment 

_ 1.4 1.4 

-door. • 01 ■•• 

-en- QM/ 40 ••• 
• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

L. 

DteRELSECIA.= rjj 

WHS-311 

Page -106 

SUBSYSTEM COST COMPARISON/7 SEG. AND 5 SEG WUM 

DOLLARS IN MILLIONS 

RECURRING (6 F.T. PROG. ) 

7 Segment ' 5. Segment 

3. 00 • 2. 70 

. 90 . 60 

• 5. 50 4; 80 

3. 62 3. 12 

is. 00 8. 52 

. 410 AND 3.00 

1. 58 • 2. 58 

. 60 . 60 

5.00 4. 40 

8. 88 8. 88 

3.00 . 3.00

9. 10 8.46 

10. 38 10. 38 

--- -..... 

- - - 

0•11■■■••••• 

69. 56 

12.04 

81. 60 

DSECR L HAMMIER 

• Structure 

ACTS Stabilization 

Orbit Adjust Propulsion 

• ACTS Electronic 

Electrical Power 

NON RECURRING 

7 Segment 5 Segment 

5. 500 3. 270 

1. 500 1.000 

i 11. 120 8. 210 

18. 800 18. 800 

20. 000 20. 000 

Cryogenics - - - 8.900 

Environmental Control 5.000 8. 660 

Separation . 500 , . 500 

Data Management. 12. 800 12. 800 

. TT&C 17.600 17. 600 

Instrumentation 3.000 3.000 

Assembly & Test 22. 150 21.400 

Sustaining Engineering - -OP . • No 

ST/TE 21.830 4 21.830 

Mockups - Substitutes 3.450 3.450 

01■11•1111Mmil 

SUB-TOTAL 143. 250 149. 420 .• 

Travel, Other Direct, Fee 28.75 28.48 • 

TOTAL CM • 172.00 177.9 • 

61.04 

11. 46 

72.50 
SPEC WHS-311 

Page 107 

COST 

WEAROUT LIFE TESTING REQUIREMENTS 

85 DAY W UM 

SUBSYSTEM LIFE 

DEMONSTRATED REQUIRED 

• BI-PRO THRUSTER 10, 000 SEC. 30, 000 SEC. $ 3. 5M (3 TEST ITEMS) 

IMC MECHANISM =am 250, 000 CYC. $ 6. 5M (25 TEST ITEMS) 

SPECIAL KIIMUNG 

$10. OM 

semme= 

NRO APPROVED FOR 

c

rEASE 1 JULY 2015 
**If LVD Flight Incl. Baseline 

Unmanned Total LVD 

311. S -102 209.9 + 17.0 * 226. 9 

auminimmormalriparr 

SPECIAL PAI 

WHS- 311 

Page 108 

Baseline 

....111111■ Nonrecurring • Recurring 

Total 

411IMEM.111m• 

Dev. GBQ LVD Total Manned (3) Automatic (2) Option 6 Total. 

Titan IUM 164.9 21.0 21.0 206. 9 63. 0 42.0 1os.° 311. 9* 

Option 6 +37. 1 

7 Flt. 3.417.1 

Step 

1 Not ManRated 

-10.0 

134:3 

-21. 0 -21.0 

--cr- 

-52. o 

13-4717 

-1.5 

IT7T 

-1.0 

1T:T 102. S 257. 4 

2 T-III C - 30. o 0 -30.0 -10. - 17.5 

Reliab. TZT7tY 11-474 -ST75 33 -FOY 209.9** 

Step 1. Remove 

Step 2. Remove 

Man/Remove Crew Safety. Remove GBQ and LVD Fits. 

Man/Remove Reliability, i. tr. *except T-III C Reliability. 

Remove Nonrecurring Recurring 

Strap down Guidance Pkg. Gemini Backup 

St 1. Malfunction Detection Kit. GBQ and LVD 

10 + 42 a 52 52.0 0. S Each 

Triple Redundancy Autopilot it go to the 

Step 2. T-III C G &C with stop comp 

30 30. 0 3. S Each 

Total: 311. 9 . (40.0 + 42) a 82 + (S x 4.0 each) a 31.1.9 • 102.0 a 209.9 

*311.9 Includes facilities cost but does not include $37. 1 M of T-III line money. 

-ELEASE 1 JULY 2015 

I i SPEC11A1 HANDLIING 

TITAN III M (OPTION 6) 
NR VE13+044-- 

EASE 1 JULY 2015 

S NEL WHS-311 YA 1IdlNg Page 109 ' • 

Ala 

COST - BENEFIT' COMPARLSONS 

wr 

••■■•■•■•■•• 41■■■•■•••• ••■•• 0.110.1111•15 SPECIAL IYAKDLIJKG 
9 JUNE 

10 

APR 

9 JULY 

\VS AUG 

SEPT Ns% 

FEB 

LAUNCH DAY a 1 JAN N 

10 S 1) 

I 

so 

NRO APPROVED FOR 

RELEAS 

SPECIAL HANDLING 

SUNLIGHT CONSIDERATIONS 

I s 90° 

MISSION DURATION DAYS 

"'''''SEetalri,T SPEC/Ale 

WHS-311 

Page no 
EySLIVR-E.T.-SPECIAL HANDLING 

NRO APPROVED FOR 

RELEASE 

WHS- 311 

Page, ,111 

COMPARISON OF BASELINE AND POTENTIAL RENDEZVOUS VEHICLE 

CAPABILITIES FOR TECHNICAL INTELLIGENCE DATA RETURN 

6 M/AM 6 AM 6 WUM 2 RAM V + 5 ARV 

FLIGHTS FLIGHTS FLIGHTS FLIGHTS 

OIMINIMMIMIIIIONIIIIMI 7 SEG. 

• TOTAL NUMBER OF CLEAR 

PHOTOGRAPHS/YEAR 

• TOTAL NUMBER OF CLEAR, 

SPECIAL PHOTOGRAPHS/YEAR 

• ANNUAL COST - 14$ 

• RELATIVE COST. PER C. S. P. 

13, 308 21, 060 24, 000 29, 200 

1, 344 894 1, 020 2, 540 

520.8 402.0 327.0 34300 

2.9 3.3 2.4 .

.1.0 

RECURRING COST EST. 

414$) 

(ED) 

MAM AM 7 SEG. WUM RAM RRV 

87 67 54.5 67 42 
APPROVED F lifr. 

R EASE 1 JULY 015 WHS- 311 

PECIAL HANDLING Page 112 

fi 

65 DAY AUTOMATIC MODE VEHICLE BRIEFING 
• RELEASE 1 JU 2015 

tsl t RO APPROVED 

WHS- 311 

Page 113 

SPECIAL HANDLING 

65 DAY SESSION SUPPORT MODULE 

INTERNAL ARRANGEMENT 

rwa, CELL (2) 

LU2TANK (2) 

LO2 TANK (2) 

MIA TRANSPORT 

ot PATH 

OXTD

TANK 4% 

ri ACTS 

PRESSURANT 

TANK(4) • 

VZH STA 

746.00 

SUPPORT MODULE I LABORATORY 

FWD. UNPRESS. 

COW' T. FUEL TANK (4) 120.0 

RE-ENTRY 

VEHICLE (6) 

IMO 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

WEIGHT SUMMARY 

AUTOMATIC MODE MOL VEHICLE . 

65 DAY DESIGN LIFE 

SEGMENT WEIGHT, LBS. 

SUPPORT MODULE 8,050 

LAB VEHICLE 12,200 

MISSION MODULE 7,285 

CONTINGENCY 3, 465 

Tote's]. 31, 000 

SPECIAL HANDLING 

D 'L*ei 

SPECIAL HANDLING WHS-311 

Page 114 
NR-0 APPROVED FOR 

RELEASE 1 JULY 2015 

T SPECIAL HANDLING 

WEIGHT ESTIMATE 

SUPPORT MODULE 

(65 DAY DESIGN LIFE) 

• 801180 NM 

ITEM WEIGHT, LBS. 

STRUCTURE (10' LONG) 610 

NOSE CAP (EFFECTIVE) + JETTISON 70 

DRY• (6) 1,860 

DRY SUPPORT STRUCTURE 180 

JETTISONADLE DOORS (6) 120 

TRANSPORT SYSTEM 350 

INTERFACE ATTACH 90 

INSTRUMENTATION/ CABLES 70 

(3, 350) 

• 720 

1,11110 

1100 

SOO 

SOO 

Se050 sonsats 

•PROPELLANT TANKAGE AND RESIDUALS (4 SETS) 

USABLE PROPELLANT 

••CRYOGENIC REACTANT TANKAGE it RESIDUALS (2 SETS) 

USABLE REACTANTS 

"vit. CELLS, INSTALLED (2) 

TOTAL 

•BASELINE MOL HARDWARE 

,••65 DAY THERMAL COVERING 

D T SPECIAL HANDLING 

WHS-311 

Page 115 

• 

• 

- ',"^■■••••••■•,.. - 

1 

- - • 
WHS-311 

Page 116 

PROPELLANT SYSTEM 

REACTANT SYSTEM 

- •Neele• ow.: woman. - =nom* Nome.. maw= a - ammo ermonw ..MO •••••■ 

TWO FUEL CELLS 

• ■••••■ OWN.M. MwOON. eaMaM ••■■■ 

. • • 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

. 17,-SarrettST-31" ECIAL HANDLING 

ADDITIONAL WEIGHT REQUIREMENTS FOR EXTENDED 

AM DESIGN LIFE 

.. 

EXPENDABLE RATE - LBS/DAY 

PROPULSION SYSTEM - ¢0. 8 

CRYOGENIC SYSTEM . 25.7 

TOTAL EXPENDABLES 

NOT INCL. HARDWARE - 116.5 

TOTAL SYSTEMS 

~PM 

0 

i. 

12 16 

1 

20 24 28 32 36 I 

ADDITIONAL DESIGN LIFE. DAYS 

T SPECIAL HANDLING 
SPECIAL HANDLING 

INCREASE IN MEAN MISSION DURATION WITH EXTENDED DESIGN IZFE 

50 

1 45 

40 

35 

30 

MMT MMD X R 611 

. 

o 1 co. .Ino BOOSTER 

I:1 

71. . 765 

N 

I N 

• • 

11 1 

 MMT/ 49.3 X . 93 = 45.9 DAYS 

RAM 2: 

g g 1 to MMT/ = 47. 1 X . 93 = 43. 8 DAYS 

• I 1 a 

RAM = . 730 

t... t .5 .6 . 7 .8 .9 l.0 

RELIABILITY FOR 30 DAY. LIFE 

.1[: „

.................................. 

SPECIAL HANDLING 
SPECIAL HANDLING WHS-311 

Page 118 

EFFECT OF PROGRAMMING FOR ACTIVE INDICATORS TARGETS 

30% CLOUD COVER o .0.09 INCIDENCE OF ACTIVE 

INDICATOR 

st 

ACTIVE INDICATOR TARGET 

E.■ 

14 4 ACTIVE INDICATOR TARGETS 

0 

- SPECIAL HANDLING 

NRO APP FOR 

RELEA 1 JULY 2015 
WHS-311 

Fag? 119 

NRO APPROVED FOR 

RELEASE 1 JULY '15 

SPEC 

VA 

COST - COMPARISONS 

MANNED AND UNMANNED PROGRAMS 

MOL BASELINE $1,784M. 

$1,120M-$1,255M M) WHOLLY UNMANNED PROGRAM 

(35-DAY, TIII 5-SEG) 

(65-DAY, TIII 7-SEG) $1,400M41,570M 

FOLLOW-ON RECURRING 

MOL -'AM 

WHOLLY UNMANNED 

5-SEG 

7-SEG 

it 

$ 67M 

$ 45M 

$ 57M 
o 50% OF TARGETS HAVE TWO ACCESSES PER CLOSURE' 

o No Count town • 

ti 

50 

•■■••••• ••••••• •■■••■ 

10 • 

mai •11.1m■ +wage ••■•••• maw 

0 20 4o 1

6o 80 100 

% ge. FIRST CLOSURE TARGETS WHICH ARE 

HIGH7PRIORITY. . 

1:14filltHOLL - SPECIAL HANDLING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1:YMeR.E.T..... - SPECIAL HANDLING WHS-311 

.Page 120 

• - 

VERIFICATION EFFECTIVENESS FOR TOTAL TAKE 

o 

V AVG s' 0.5 
NRO APPROVED FOR 

RELEASE l iLV 2 

as }MK ,[1NO 

WHS-311 

Page 121 

ORBIT PHASE RESCUE/ESCAPE 

CONSIDERATIONS FOR THE MOL 

0 RESPONSE TO HOUSE COMMITTEE ON SCIENCE & ASTRONAUTICS 

QUESTIONNAIRE: "SPACE FLIGHT EMERGENCIES" 

ESTIMATE CREW ORBITAL STRANDING RISK 

I REVIEW EFFECTIVENESS OF POSSIBLE COUNTERMEASURES 

SPECill NA HUM 

:c' 
D 

NRO APPROVED FOR 

RELEA ■ 

SPEC AI 1:1 

WES-311 

Pp.ge 132 

N2 

APPROACH TO ON-ORBIT STRANDING ESTIMATE 

4 

ABORT EVENTS 

DENIED INGRESS TO GEMINI B 

.t NORMAL RE-ENTRY 

SUCCESSFUL INGRESS 

TO GEMINI B 

► STRANDED ON ORBIT 

COUNTER MEASURES ? 

SPEC1111. HANDLING 
# 3 

,•••■■■•••■••• 

ME WHS- 311 

HANDIER% Page 123,., 

ACCESS ROUTE PROBABILITIES 

(LABORATORY TO GEMINI B) 

GEMINI HATCH 

Z2 EV HATCH 

(EV MODE) 

U 

INTRA• VEHICULAR MODE (IV) 

EVENT PROBABILITY* 

EXTRA- VEHICULAR MODE (EV) 

EVENT PROBABILITY* 

• HATCH INOPERATIVE 

• CRUSHED TUNNEL 

3.0 X 10-6 

X 10- 6 

3.0 X 10. 6 

. 03 x 10" 

6 X 10.6 

* PROBABILITY OF OCCUR 

• DRV TUBE HATCH INOPERATIVE 

O PRESSURE SUIT ASSEMBLY 

INOPERATIVE 

• GEMINI B HATCH INOPERATIVE 

(OPEN) 

CE FOR 30 DAY IN•ORBIT 

NRO APPROVED FOR 

RELEA ULY 2015 
NRO APPROVED FOR 

REL 1 J 

P.C. GENERALLY I. V. WITH E. V. 

BACKUP 

U.C. 

P.C. 

t. V. OR E. V. DEPENDING ON. 

EFFECT ON SYSTEM (POWER 

LOSS, 02LOSS) 

I. V. OR E. V. DEPENDING ON 

EFFECT ON SYSTEM 

SPEC WUNG 

PROBABILITY OF DENIED INGRESS TO GEMINI 13 

4 

WHS-311 

Pane 124 

COMPARTMENT 

ABORT LOCATION OF PROBABILITY OF DENIED 

FAILURE OR HAZARD FAILUREpIAZARD PATH OF INGRESS TO GEM. B INGRESS TO GEM. B 

U. C. I. V. WITH E. V. BACKUP 

E. V. IF TUNNEL DAMAGE 

P.C. I. V. ONLY 

U. C. CRUSHED TUNNEL, USE E. V. 

P.C. I. V. 

P.C. I. V. OR E. V. 

PROBABILITY OF DENIED INGRESS TO GEMINI B IS VERY REMOTE . 

a 

Inv a SEPEPPRI1 ful !mon unite* 

N 

FIRE 

EXPLOSION 

DEPRESSURIZATION 

NOXIOUS GASES 

SUBSYSTEM ANOMOLIES 

• - 50x 10 12 

.6 

15x 10 

3x10 b 

15x 10-6 

3x 10-6 

- 50x 10 12 

1 so 11

0

2 

15 x 10 r 6 

TO 

SO x 10 12 
APPROVED FOR 

ELEASE 1 JULY 2015 WEIL ILLAL WHS- 311 

Page 125 

POSSIBLE CAUSES OF FAILURE OF GEMINI B TO INITIATE NORMAL RE- ENTRY 

ENVIRON. BURSTING OF 02 TANKS CAUSING 02 CONTROL 

SYS TEM- LOSS OR RETRO- ROCKET DAMAGE 

• SYSTEM 

TYPE OF EVENT 

(R E. PRECLUDING FAILURES) 

.. • 

PROBABILITY OF OCCURRENCE 

FOR 30 DAYS IN-ORBIT 

GUIDANCE HAND CONTROLLER INOPERATIVE OR 0.001 X.10. 5 

& CONTROL . • FAILURE IN BOTH DIRECT AND RATE 

COMMAND MODE. 

• 

PROPULSION LEAKAGE OF BOTH RCS RINGS OR BURST 9. 686 X 105 

OF PRESSURE TANK DAMAGING BOTH RINGS. 

0. 200 X 10 5 

- 7.200 X 10 5 

7. 475 x 10-s 

SHORT OR OPEN CIRCUIT - BOTH RINGS 

INOPERATIVE. FAILURE OF MORE THAN 

FOUR RETRO- ROCKETS 

ELECTRICAL SHORT TO GROUND OF COMMON BUS 

POWER CAUSING LOSS OF ALL FUNCTIONS, 

MULTIPLE BATTERY LOSS. 

CREW HEAT SHIELD/PRES.SURE HATCH 

TRANSFER FAILURE OR FAILURE TO SEPARATE 

(I. V.) GEMINI FROM LAB 

TOTAL PROBABILITY OF A GEMINI B 

EQUIPMENT FAILURE WHICH WOULD 

PRECLUDE INITIATION OF RE- ENTRY 

0. 400 X 10-s 

24. 962 X 10- s 
6 

PROBABLE RESCUE OR ESCAPE ESTIMATE SUMMARY 

• 

EVENT 

PROBABLE EVENTS 

PER 10, 000 MISSIONS 

• 

OCCURRENCE PRECLUDING INGRESS TO 

GEMINI B FROM LAD 

MUCH LESS THAN 1 

• OCCURRENCE PRECLUDING. RE- ENTRY AT MOST 

OF GEMINI B 

• • ESTIMATED EVENTS PRECLUDING RESCUE AT LEAST 

OR ESCAPE (CREW FATALTIES, VEHICLE 

DYNAMICS) 

• ESTIMATED RESCUE OR ESCAPE" OPPORTUNITIES AT MOST 

1 SPECIAL NANDLIN2 

NRO APPROVED FOR 

REL 

SPECIIAL HANDU WHS- 311 

Page 126 
RESCUE 

POSSIBLE 

RESCUE NOT 

POSSIBLE 

IORBIT PLANE 

< 1/10.000 CREWS RESCUABLE 

EARTH'S ROTATION 

PECI1AL MEILING 

NRO APPR VtaF23 

REL 1 JULY 2015 MECELSPECE HAMM WHS-311 #7 

Page 12,7 

EARTH BASED RESCUE CONSIDERATIONS 

' • WITH NO CONSTRAINTS ON GEMINI B OR LAUNCH VEHICLE CAPABILITY , 

SYSTEM USED TWICE IN 10.000 MISSIONS 

• CURRENT GEMINI B LOITER AND LAUNCH VEHICLE PAYLOAD 

CONSTRAINTS FURTHER REDUCE EFFECTIVENESS. 
WHS-31174 

• .page 128 

NRO APPROVED FOR 

RELE 1_.161.6144B4i 

SPIEn HANCUNG 

#8 

ON- BOARD ESCAPE SYSTEM CONSIDERATIONS 

• • TECHNOLOGY GENERALLY AVAILABLE 

• SYSTEM COMPATIBILITY REQUIRES EARLY DESIGN INTEGRATION 

(TOTAL SYSTEM DESIGN) 

• LIMITED UTILITY, CONSIDERING ALL CAUSES OF ORBITAL STRANDING 

(DEVICES DISABLED OR NOT AVAILABLE) 

• RE-ENTRY, RECOVERY, RETRIEVAL HAZARDS. 

(UNSOPHISTICATED SUBSYSTEMS, LARGE DISPERSIONS) 

SPECIU NADLER 
• 

• Page 1.294.44 " \

WHS.:311 

09 - - 

MEI HANDING 

NRO APPROVED FOR 

RE 

COMPARISON OF ORBITAL STRANDING RISK WITH 

RISKS OF SOME FAMILIAR ACTIVITIES 

• ACTIVITY 100,000 MAN DAYS 

• DOMESTIC PASSENGER AIR CARRIERS 

• ESTIMATED MOL CREW STRANDING 

• ACCIDENT FATALITY RATE, U.S. , POPULATION 

4. 0 

.T 

.2 

PECK HAMM 
7.-OWTEP WHS-311 

Page 130 

SUMMARY 

MOL BASELINE PROGRAM ORBITAL RESCUE/ESCAPE 

MOL SYSTEM DEVELOPMENT APPROACH 

J RELIABILITY 

j BLOCK. AND FUNCTIONAL REDUNDANCY 

I TESTING 

I SYSTEMS MONITORING 

. .1 EMERGENCY PROCEEDURES AND 'TRAINING 

REMOTE POSSIBILITY OF ORBITAL STRANDING (. 9998 PER MISSION) 

NO SUBSTANTIAL REQUIREMENT FOR RESCUE OR ESCAPE 

SYSTEMS IN THE MOr., DEVELOPMENT PROGRAM. • 

D SPTC[JA If A RIMS 

NfjQlAPPROVED FOR 

LEASE 1 JULY 2015 
NRO APPROVED FOR 

RE 

WHS-311 

SPEC HDLING Par 431 

FOLLOW-ON PROGRAM CONSIDERATIONS 

• MOL MAY HAVE RENDEZVOUS/RESUPPLY CAPABILITY IN 

EARLY SEVENTIES 

• NASA AAP PLANS RENDEZVOUS/RESUPPLY OPERATIONS 

STARTING IN LATE SIXTIES - 

• ELEMENTS OF THESE TWO SYSTEMS MIGHT BE COMBINED 

TO PERMIT AN EARLY SPACE RESCUE SYSTEM 

MEI 1INDUKS 
• iii L 

FEM.= YANDIUINO 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1 

WHS- 311 

Page 132 

• 

MOL /NASA APPLICATIONS "A" _ 

al I 

POSSIBLE UTILIZATION OF MOL FOR ACCOMPLISHMENT OF 

NASA SCIENTIFIC EXPERIMENTS - SPACE APPLICATIONS 

MISSION "A. " 

r• 

• - • • 

f• 

t i•• ••: : 

:1,ntn14en affecting th. neional 

•••• . 'he meaning of the 

• • "", '••• r::on 793 and 794. Its 

..i.5 C)ete.•:S ■41 4.7 

••••";- • 

AT 3 YEAR INTERVALS; 

DECI.1% ........... AFTER 12 YEARS. 

DOD DIR 5200.10 

SPECIAL NA 
PECIJA,, HARIF,LING 

t4..111R0 AF‘P,Re ■;ED FOR 

.„ 0.13F-1FA$E, lAl,2815 

P-• 

MOL/APPLICATIONS "A" 

BACKGROUND 

• NASA'STUDIES/DEFINITION OF "APPLICATIONS A" PKG. jossA) 

• DEVELOPMENT-IMPROVEMENT OF AUTOMATED METEOROLOGICAL SATELLITES 

• ,14 EXPERIMENTS-CURRENT BREADBOARD OR FURTHER ADVANCED 

• EXPERIMENTERS REQUIRE POLAR ORBIT AT 125 N. MI. CIRCULAR 

‘4■ 

• NASA S-1B/APP'sAYINTEGRATION STUDY (MSC) 

' • CAN ATTAIN 50° INCLINATION AT 125 N. MI. CIRCULAR 

o EXPERIMENT VOLUME NECESSITATES SPECIAL CARRIER 

o PERFORMANCE CAPABILITY LIMITS MISSION TO 2 WEEKS 

o SUBSYSTEM PROBLEM AREAS FOR CSM 

POWER 

J DATA 

J THERMAL 

J DISPLAY/ CONTROL 

• COST $32M EXPERIMENTS + $20M FOR SPECIAL CARRIER 

• NASA SUBMITTAL OF "APP A" TO MANNED SPACE FLIGHT EXP. BOARD 6 FEB. '67 

• DOD QUESTIONED NEED FO,J MAN TO CONDUCT EXPERIMENTS 

• ACCOMMODATION OF SOME OR ALL EXPERIMENTS ON MOL FLIGHTS?. 

WHS- 311 

Page 133 

• MOL SYSTEM OFFICE DIRECTIVE 8 FEB. '67 TO MOL/SPO 

• COST & SCHED TO FLY "APP A" ON SEPARATE MOL FLIGHT (POLAR ORBI't)r) 

• ACCOMMODATIONS FOR INDIVIDUAL EXPERIMENTS ON BASELINE FLIGHTS 

J PIGGYBACK BASIS 

,/ MANNED FLIGHT 

./ UNMANNED FLIGHT 

is der, wAnt contains inforgnatiogiatNeting the national 

wit in t e m nin• t., 

• . 0f th0 111■4,1116011 ol,its contents in any 

fspio0:.• 1. -ws, 01* 1 . . ion an- • 

ieorit■ tyr .. L#11111■11,%.1 -et 1 ,,e•son is reakiNieet hy Ir 

DOVV:;'..;,MDED AT 3 YEAR INTERVALS; 

DECLASSIFIED AFTER 12 YEARS. 

DOD DIR 5200.10 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

J 

3 

• WH41-3 

Page EMIL HANDLING 

"APPLICATIONS A" EXPERIMENTS 

OBSERVABLE PHENOMENA - METEOROLOGY 

ATMOSPHERIC PHENOMENA SENSING MODE EXPERIMENTS 

'.CLOUD CHARACTERISTICS PHOTOGRAPHY S-039, 5-040, S-042 

SPECTROMETRY S-050 

RADIOMETRY S-048, S-057 . 

ATMOSPHERIC CIRCULATION 

• 

SPECTROMETRY S-45, S-048, S-049, 

S-050 

SEVERE STORMS PHOTOGRAPHY S-039, S-040, S-042 

SPECTROMETRY S-049 

RADIOMETRY S-057 

VERTICAL PRESSURE PROFILE STAR TRACKING S-047 

VERTICAL TEMPERATURE PROFILE PHOTOGRAPHY S-047 

SPECTROMETRY S-043, S-050, S-049 

RADIOMETRY S-044C, S-060 

HEAT BALANCE SPECTROMETRY S-045 

RADIOMETRY S-057 

WATER VAPOR DISTRIBUTION SPECTROMETRY S-46, 5-049, S-045 

RADIOMETRY S-044B, S-060 

PRECIPITATION DISTRIBUTION RADIOMETRY 5-044A, S-04413 

ATMOSPHERIC ATTENUATION RADAR S-041 

OF MICROWAVES 
4 

• NIA 'AIME WHS-311 

,Page 135 

"APPLICATIONS A" EXPERIMENTS 

SCHEMATIC ARRANGEMENT 

EQUIP. SCALE 

(APPROXIMATE) • 

0 1 2 3 _4 FT. 

S-040 i=d==istz=1==i 

' S-046 

b\N. 130° S-0.44C 

S-044B 

S-042 

S-047 

S-041 S-043 

• . 14- 

- • 

•I ' 

NRO APPROVED FOR 

RELEASE 
NRO APPROVED FOR 

"APPLICATIONS A" EXPERIMENTS Page,136 

TECHNICAL REQUIREMENTS 

EXPERIMENT EQUIP. 

WEIGHT 

(LBS) 

ASC RET 

VOLUME 

(FT 

ASC 

3) 

RET 

POWER DATA 

I FILM DGTL 

WATTS KWH. (FRM` (BPS) (CE-I) 

ANLGiPOINTI 

1 ATT. CONTR 

RATE 

(DEG) (°/SEC) 

'LUANG 

(SEC) 

S-039 - .DAY-KITE CAMERA 75 20 2. 1 O. 5 t 

-i79 110. 25 0 5 I 6 1 

.-- .1 

+5°: . 05 a 1 

S-040 DIELECTRIC TAPE 

CAMERA 

r 

83 0 2.0 0 55 0. 6 0 0 ' 35 

- 

100 . 15 • 

S-041 MILLIMETER WAVE 

PROP 200 5. 0 224 4. 5 0 80 0 - • 1 

_ .... 

S-042 MULTI-SPECTRAL 

PHOTO 1 1, 400 200 39. 0 2. 5 - 900 3. 0 10. 4K 0 - 0. 5° 0. 10 

S-043 IR TEMP 

SaTINDMIC 40 10 1. 8 O. 3 

--**--4 

I 

100 1 

t 

 26. 8 1 1. OK 1. 3K 0 +1o O. 2 0. 4 

S-044 0 & H2 

WAVE 

2 0 MICRO- 260 14.8 0 .16(; 16.6 100 

- 100 2

9 

- 0.005 

S-045 .IR FILTER WEDGE 30 1. 3 0 5 0.04 0 204: 0 +2o 

- 1 

S-046. . POLARIZATION 51 

- 

1 

- 

2.2 0. 1 50. 4.0 100 160 0 0.5° 0.05. 

S-047 STELLAR 

REFRACTION 110 0 4. 5 70 4. 6 0 890 0 0. 5° 0. 05 i 0. 001 

S-048 UHF SFERICS 35 0 0. 7 41 0 10 3, 3 0 50 0 +20 

- 1 

S-049 IR INTERFEROMETER 36 0 1. 4 0 

--........--.-4 

14 1. 6 - 4K 0 +O. 5 0.05 1 

S-050 IR TEMP PROFILE 90 5. 8 0 25 1. 7 1. 5K +1 

S-057 MULTI-CH 

RADIOMETER ' 18 . 0. 8 9 1. 6 - 50K +0. 5 0.05 0. 1 

S-060 CHOPPER , 

RADIOMETER 28 0 1. 7 0 18 6.0 - 42 2

0 1-1.4. 

•

L • • • 

STRTNGENT RAQ41T, 2, 456 231 83. 1 3. 4 1,125 84. 59 1.1. 5K 56. 1K 48 +O. 5°, 

10. 00 +0. 05 i 
HAM 

WHS-311 

. Page.137 

SPEC 

ANALYSIS OF "APPLICATIONS A" BY 

JOINT METEOROLOGY SATELLITE PROGRAM OFFICE 

CONCIDENTIAL 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPONSOR CURRENT PLANS FOR FEASIBILITY OF 

SUBJECT AFFILIATION SAME OR SIMILAR EXPER.. AUTOMATED EXPER. 

VISIBLE RADIATION 

POLARIZATION MEAS. 

FROM ATMOS. 

RADIOMETRIC MAPPING 

CLOUD COVER 

METEOROLOGY TV 

. ATMOS. MEAS. FROM 

STELLAR REFRACTION 

CHOPPER RADIOMETER 

IR FILTER WEDGE 

SPECTROMETER • 

IR TEMP SOUNDING 

DAY/NITE CLOUD COVER 

IMAGE ORTHICON 

IR INTERFEROMETER 

SPECTROMETER 

UHF SFERICS 

IR TEMP. PROFILE • 

. MULTI-SPECTRAL 

PHOTOGRAPHY 

MILLIMETER WAVE 

PROPAGATION 

- - 

NIMBUS D-1970 

NIMBUS D-1970 

NIMBUS B-1967, NIMBUS D-1970 

ATS-D, 1968 

NIMBUS B-1967, NIMBUS D-1970 

NIMBUS D-1970 

NIMBUS B-1967, NIMBUS D-1970 

NOT SPECIFICALLY 

METEOROLOGY 

NOT SPECIFICALLY 

METEOROLOGY 

AT SAKS) INTERVALS 

DE.C.Li,..:C.HZ0 AFTER 12 YEARS.. 

GOD OIR 5200.10 

MICROWAVE RADIOMETER GODDARD 

INST. &MIT 

AUTO 

AUTO 

AUTO 

AUTO 

MAN REQ'D 

AUTO -

AUTO 

AUTO 

AUTO 

AUTO 

AUTO 

AUTO 

MAN REQ'D 

EXP. NO. 

S-044 

S-046 

S-057 

S-040 

S-047 

S-0 60 

S-045 

S-043 

S-:039 

S-049 

S-048 

S-0 50 

S-042 

5-041 

UCLA 

U OF CAL. 

GODDARD 

SFC 

U OF MICH 

OXFORD 'U 

GODDARD 

SFC 

OHIO ST. U 

GODDARD 

SFC 

GODDARD 

U OF WIS 

ESSA 

ARMY 

ENGRS. 

GODDARD 

SFC 

Tp.;) • • mPormeoion affecting the nanonst 

t.1 t - s .to•hil the meaning of the 

:• 793 Ind 794 los 

tr.lft..• ■ Gs. of its come tos m .snY 

iy.4tta.te ta .int,u.h4tizad ?arson is pionibiled by law - *fatal i 

" S C A 'A.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 DIECRET---'-' I. iPEC MEM-• 

o:: DENYIAL WHS-311-77 

Page- 138 

MOL/NASA APPLICATIONS "A" 

CONSIDERATIONS FOR EXPERIMENT INTEGRATION , 

• VEHICLE SUBSYSTEM 

• STRUCTURE 

• POWER 

• COMMUNICATIONS/COMMAND/DATA MANAGEMENT 

• GUIDANCE AND ATTITUDE CONTROL 

PROPULSION • 

• THERMAL CONTROL 

• EXPERIMENT DISPLAY. AND CONTROL 

AGE 

OPERATIONS 

• TEST FLOW 

• LAUNCH/FLIGHT 

• CREW ACTIVITY 

SOFTWARE 

• ON-BOARD COMPUTER PROGRAMMING 

• GROUND BASED COMPUTER PROGRAMS 

ooviNcl: AT 3 YEAR INTERVALS; 

AFTER 12 YEARS. 

COO OIR 5200.10 

' information effecting the national 

within the meaning of the 

r • . • S.C., Section 793 end 794. Its 

of ■ 01 conteme in any 

A ”nAti ad ..tresen is orotebtlad by 14w. 

S PECE 
- - 

APPROVED151?Rd*"""' 

RELEA 

WHS-311 

Page 139 a SPEC 

MOL/APPLICATIONS "A" 

STUDY APPROACH 

FLTS 1, 2 - NOT FEASIBLE FOR APP. A - LACK &EEDED SUBSYSTEM CAPABILITY 

FLTS 3, 4, 5 - INDIVIDUAL EXPERIMENTS PIGGYBACK - WITHIN FLT. CAPABILITY? 

• SELECT FROM 5 EXPERIMENTS RECOMMENDED BY 3MSPO (040, 044, 046, 047, 057) 

• NO INSTALLATION IN MM 

FLTS 6, 7 UP TO COMPLETE APP. A.PKG PIGGYBACK - WITHIN FLT CAPABILITY'? 

• AUTOMATED EXPERIMENTS 

• INSTALL IN SM OR LM • 

SEPARATE MOL VEHICLE FOR APPLICATIONS "A" 

• COMPLETE APP. A PKG. . 

• DURATION UP TO 60 DAYS 

• PtliSIOLOGICAL AND PSYCHOLOGICAL TESTING CAPABILITY 

S 

NU 

• 

PROGRAM, 

DJ Vi:GRADED AT 12' YEAR 

niN ' ". TOMATICALLY 

/4111E4K91, 1 DIR 5200.10 

rlfiis r ankting thy national 

defento' cf .!.- hrn the meaning of the 

ispiernestS.Vnt I l,i 18 J. S. C , Section 793 and 794: Its 

gansmistion or tho reyelstion of its contents in any 

MOWN to an iinatahcrizod person is PeohibiNd by few. S Fll 
legpvgiCCESS REQUIRED TINEDiNG 

WHS-311 

Page 140 

NUMBERi. ;?-144--- 

1180* 

1'60' 

450 

'140 

1t30 

•4 

H 

H 

a) 

1120 

,11.0 

100 

90 

90S 80 70 60 SO 

/his dc.rt,. rein: information affecting the nationsli 

defense, i!!0,1 within the meaning of the 

Till le U.S.C, Section 793 and 794.05 

aniatig:41,-, or the revelation of its contents in any 

ran 

'140 30 20 10 0 10 ;20 

LATITUDE • DEGREES. 

30 40.50) 60 .70 80 90N) 

DOWNGRADED AT 12 YEAR 

INTERVALS; NOT AUTOMATICALLY 

omit DOD D1R 5200.10 

80 

1111111111•11. IiMMOOM 

/ROL BASELINE ORBIT 

S -0,39e 

S-040, 

S7041. 

S-044 

'5-046 

s-0 60 

EXPERIMENT 

NUMBER 

AND PREFERRED 

ALTITUDE 'RANGE 

—,1125 "CIRCULAR" 

ORBIT/ALTITUDE CHARACTERISTICS VS. PREFERRED ALTITUDES 

FOR EXPERIMENTS 

s-a42 

5.-043 

S-045 

S-049 

S-057 

S-0481 

"APPLICATIONS A' I. EXPERIMENTS' 
J 14,iQAPPROVED FOR 

RELEASE 

WHS-311 

Page 141 

• 

DIECRgS?EC 

1p 

MOL /NASA APPLICATIONS "A" 

I. 

Ihis document t'...n.`ains information affecting the national 

derAcv) cc ;IV; i;•ri within the meaning of the 

fusions:le It Nitj, TN' It U.S.C.. Socilon 793 in 794. Its 

transmistit... or h 7 0i, lO1I of its contents in any 

mimeos In all unau.hc.reel aerials is prohibited by law, 

PEClla,, HANCIMI _ 

::.,:-!.F,) ,s.F1 ER 12 YEAR, 

poi) DIU 540040 

MOL DEVELOPMENT PROGRAM 
4ociimer1 roetaleil Tniormation affectIng tEie nafiona1 

defense 1:d .11% within the moaning of Ma 

Esplonal*Lwr, Pk. 18 U. S C., Section 793 and 794. Its 

transmission or Ilia revelation of i1s contents in any 

. mow to an onowhorizod person k prohibited by law, 

DLID AT 3 YEAR INTERVALS; 

DECLASSIFIED AFTER 12 YEARS, 

DOD DIR 5200.10 

RELEASEIM 

NRCAPPRoVED FOR DIEcRET- .ITANDLIIIkrA 

CONFIDENTIAL WHS- 311 

Page 142 

MOL/NASA APPLICATIONS "A" 

FLIGHTS 3, 4, AND 5 (MANNED) 

(30 DAY DURATION) 

S-047 

• S-047 STELLAR REFRACTION EXPERIMENT 

(158 LBS 74 WATTS OPERATING POWER) 

/ 

/ MANUAL OPERATION FOR STAR ACQUISITION 

✓ MINIMUM SUBSYSTEM IMPACT 

✓ INSTALLATION REQUIREMENTS COMPATIBLE WITH 

VEHICLE DESIGN FEATURES 

✓ LESS THAN 1 KWH ELECTRICAL ENERGY PER MISSION 

LESS THAN 4 HOURS OF CREW TIME PER. MISSION 
2 

"e• 

1■14§026444, 0VED FOR 

RELEASE 1 9(11 

WHS- 317. DIEGRET—SPEcllta HANBEFIDENTIAL Page 143 

POSSIBLE S-047 EXPERIMENT INSTALLATION 

(MOL FLIGHTS 3, 4, AND 5) 

• S-047 WEIGHT (INSTALLED) 158 LBS 

• . S-047 VOLUME (STOWAGE) 4. 5 CU. FT. • 

• S-047 ELECTRICAL ENERGY 9.5 KWH 

• • S-047 POWER PEAK 74 WATTS 

• CREW TIME REQUIRED 20 HRS 

• ACTS PROPELLANT REQUIRED 20. LBS 

STOW IN SLEEP POSITION FOR LAUNCH. 

OPERATE FROM DRV TUBE 

V 

DRV TUBE • 

COVER (MODIFIED) 

'EXPERIMENT SUPPORT DRY TUBE 

This eit curptn! .7 ,3 minim information affecting tho national 

defcnso of .In Lt.itcd Stahl within the meaning of the 

ispiona:4 , Laws, Ti I.s U. 5. C., action 793 and 794. Its 

ftansmirsisr. or h e,oll'ion of its contents in any 

OWN Mt roan yam. Is• 1, ! is ,Nohihitisrl by taw. 

STAR TRACKER 

,EVA HATCH • EVA HATCH OPEN 

i.)01`4N:..::<AQiil) Al' 3 YEAR VAL% 

EARS. 
NRO APPROVED FOR 

RELEASE 

WHS-311 

-Page .144 

POSSIBLE S-042 EXPERIMENT INSTALLATION 

(MOL FLIGHTS 3, 4, AND 5) 

DOD SIR 5200.10 

c-- 

. EVA HA.TC1-• 

1 II

fi 

.4 00- 

PERMANENT 

FAIRING 

ASTRONAUT 

ACCESS 

.BY EVA (Y 

PERMANENT 

JETTISONABLE 

FAIRING Ayr CAMERA i(6. REQUIRED) 

• S-042 WEIGHT (INSTALLED) /w2000 LBS , 

• S-042 ELECTRICAL ENERGY 3. 2 KWH 

• S-042 POWER PEAK 945 WATTS 

• EVA REQUIRED FOR EXPERIMENT 

SUPPORT PO 1 *5 HRS 

• CREW EXPERIMENT' OPERATING TIME 2 HRS 

• DATA RETURN 200 LBS 

ibi document r.oniains information &fleeting the national 

Espiona, c Title 12 U.S.C., Section 793 and 794. Its 

00Vt'i'.; ',.i;'■it I.X. .. A I i Y. L:i81% 1141 t:tiVALS4 

, • . • 

defers cf ,•hz lli,i...(1 Star" within the meaning of the 

transmioion or t rove A ion n — ,-: 

manner to en unewhoeimf *arson is orohiltited by trur-ig. 

- '4 1 /3 1 SPECI4 KAKELI1KG 

.1) 

HANDLIING 
NRO APiRROVED FORR 

RELEASE ria 

SPECM HAN:1

r HS- 31 1 

11\1 7'

,, 

 ge 145 

AVAILABLE VOLUME FOR EXPERIMENTS 

(MOL FLIGHTS 6 AND 7) 

SECTION A-A SEC ON C-C SECTION D-D 

o.........••■•••••■•■•/.0 

SUPPORT MODULE U. P. .COMPARTMENT DRV TUBE AREA EXTERNAL FAIRINGS 

B ri- C D 

D DOWNGRADED AT 12 YEAR 

INTERVAL,;; NOT AUTOMATICALLY 

• AVAILABLE VOLUME DEC!. DOD DIR 5200.10 

SUPPORT MODULE 366 CU. FT. 

U.P. COMPARTMENT 33 CU. FT. 

DRV TUBE AREA 23 CU. FT. 5PIEC! 1.? ACCESS REQUIRED 

ED SPACE PROGRAM EXTERNAL FAIRING (2) 36 CU. FT. CLA:;. iFi 

This docnnlea; :.utryism sinformation affecting the national 

delnnsci t S.a.es within the moaning of the 

Ispione7a or:, Title If U. Saction 793 and 794. Its 

Ienuni!rill or th3 osvolation of its contents in any 

manner io an onakehniileil person is prohibited by law. 

Yy.P.,■!` . 

1. 

NUMBER 

}ADM 

Cy..2 

\\s 

4Ms 
''-- 

NRO APPROVED FOR 

RELEASE 1 JU D SPIECOAL WHS- 311 

‘-U Page 146 snum. ACCESS REQUIRED 

CLASSIFiED SPACE PROGRAM 

NUMBER-. 4. 312 

MOL / NASA APPLICATIONS "A" 

FLIGHT 6 OR 7 (UNMANNED) 

(30 DAY DURATION) 

• 

CAPABILITY FOR ALL EXPERIMENTS EXCEPT S-042 AND S-047 

AMPLE VOLUME AVAILABLE IN SUPPORT MODULE. FOR 

EXPERIMENT INSTALLATION 

ADEQUATE PAYLOAD MARGIN FOR EXPERIMENT WEIGHT 

REQUIREMENTS 

• ADEQUATE POWER AVAILABLE FOR EXPERIMENT REQUIREMENTS 

this gloom 'It rusi!hins ;nitration allotting the isosienii 

defense of wi,hiti the mooning of Oho 

lispione2o 1.7 IC C • Soction 793 and 794. hi 

transmission rH revocation of its contents in any 

to ton-oustA 

SYSTEM IMPACT 

SUPPORT MODULE DESIGN MODIFICATIONS 

DATA MANAGEMENT SUBSYSTEM AUGMENTATION 

ON-BOARD SOFTWARE REVISION 

SYSTEM TEST FLOW/AGE REVISIONS DO t:v ,'...111ADCD AT .12 YEAR 

INTERVN, S; N01' AUTOMATICALLY 

DECLAS::::FIED. DOD DIR 5200.10 

Me0,107,,,PMe^". 
J 14:- 

NRC,trAh — !' VEDPFeR"--- 

REAS 

aWHS - 311 

4,7Page 147 tJ REQUIRED SPEC'AL ACCESS 

PROGRAM St, tit6.11iL 

CLA!..;SIF:ED SPACE 

NIP '3ER 

NASA APPLICATIONS "A" EXPERIMENTS ON FLIGHT 6 OR 7 

PROPOSED CONFIGURATION 

044C 

050 

STOWED-7-'1.: 

060 

DEPLOYED ----''• EXPERIMENTS PACKAGE 'EXPERIMENTS PACKAGE • 

'DEPLOYMENT .> DEPLOYMENT 

(ALTERNATE "A") (ALTERNATE "B") • 

039 044B044A •046040 045 1 

avfLSSICTU-DZIRATKODI 

AVAILABLE PAYLOAD MARGIN / . 7460 

EXPERIM TS PAYLOAD WEIGHT 1440 

T deroment contains informaiki..atessuse she na I 

de of the United States wi:hin the assailing of the 

Espio Title 111 U.S.C.. Section 793 and 794. Ifs 

transmission or revs a ton o s con en s in an 

manner to an unauthorized person is prohibited by lawny 

ADED AT 12 YEA 

, 

;:e.)D EAR 5200.10 

„ gie.m.te 
Iii d" 'S ∎ nf.trmVwn rwn allotting that national 

i,. 'd the meaning of the 

ill'iL",' ;' i :71, Saction 793 and 794. Its 

v; ? t. or tht: eoll4lien of its contents ih any 

frit1141): RI an tuiagtheritad wenn is pcohibiltd by law. 

SPECIA1 NARI 

WHS- 311 . 

4.11.i Page 14$ 

SEM IrANDLIINg 

.1 . 

• 

—NRO 4eP;ROVED FOR 

REL 

ELECTRICAL POWER CONSUMPTION 

POSSIBLE FLTS 6/7 WITH NASA APPLICATIONS "A" EXP. INTEGRATED 

CONTINUOUS 

AVERAGE* 

(WATTS) 

PEAK 

(WATTS) 

ENERGY* 

(KWH) ' 

• BASELINE POWER - SUBSYSTEM • 2,170 4,500 ,1,567 • 

CAPABILITY 

• ELECTRICAL POWER LOAD ESTIMATE 

NORMAL FUNCTIONS 1,510 3,500 1,087 

„/ APPLICATIONS "A" EXP. 130 . 979 85 

MAXIMUM LOAD CONDITION 1, 640 3,500 1,172 

• POWER MARGIN 530 1,000 395.. 

*SHOWN FOR 30 DAY TIME PERIOD 

AT 3 YEAR INTERVALS: 

SS;FIED AFTER 12 YEARS. 

• 

DOD DM 5200.10 • 
NRO s ED FOR 

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• 

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COMMAID/DATAPNIANAGEMENT SUBSYSTEM AUGMEIITA.TION* " 

WHS- 311 

Page 149 

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BASELINE 

(EQUIP. 

MAIL& HANOLDIG 

• 

. dedvnsc 'ct .k. d Ai:4 within the meaning of the 

Espionso 1t- Lt. S. C., Section 793 and 794. hs 

hansmissicn OW 0111,111•11011 of its contents in any 

manner 10 an unaishoiieed ow'son is prohibited bY law. 

' . A I 3 YEAR IN1ERVAL4P, 10.114." 

DL II' I LD AFTER 2 VOW TIP' 

DOD DIR $2 

, 

‘I I 
NRO APPROVED FOR 

RELEASE 1 J 

SPECIAL ACCESS REQUIRED 

7.t.) .s,l'ACE PROGRAM MOL/NASA APPLICATIONS "A" 

FLIGHT 6/7 IMPACT 

T SPE111E HANDUNCge1:

• APPLICATIONS "A" EXPERIMENTS 

• FLY 12 OUT OF 14 (S-047 AND S-042 AS PRESENTED REQUIRE MAN) 

• ADD NIMBUS VIDICON SUBSYSTEM TO SUPPLE' VISIBLE IMAGING FOR IR GROUP. 

• EXPERIMENT AUTOMATION FEASIBLE (INHERENT IN THE SELECTED la) 

• IMPACT ON VEHICLE SUBSYSTEMS 

' • I STRUCTURE - MODIFY SUPPORT MODULE FOR INSTALLATION 

• ELECTRICAL - ACCOMMODATE THROUGH PROPER OPS SCHEDULING 

• COMMUNICATIONS/DATA 

- ADD REMOTE MULTIPLEXER FOR EXPERIMENTS 

- ADD ANALOG RECORDERS 

COMMAND/CONTROL 

ADD DECODER/CONTROLLERS FOR EXPERIMENT OPS. ' 

• ATTITUDE CONTROL - CAPABLE OF HANDLING EXPERIMENT REQMTS. 

• • PROPULSION - 1001LB A DRAG PROPELLANT / C) 

• IMPACT ON AGE/SYSTEM TEST 

SIGNIFICANT INTEGRATION EFFORT EXPECTED FOR. SYSTEM TESTS (FACTORY & 

LAUNCH BASE) 

• COMPATIBILITY OF EXPERIMENT/VEHICLE CHECKOUT EQUIP MUST BE ASSURED. 

• MISSION SOFTWARE 

• ON-BOARD SOFTWARE MAY BE SIGNIFICANTLY IMPACTED 

/ TIMING AND STATE OF DEVELOPMENT OF EXECUTIVE PROGRAM 

• • AUGMENTATION OF GROUND COMPUTER SOFTWARE REQUIRED 

• 

DID AT 12 YEAR 

14111MT AUTOMATICALLY 

UMW n 0 I) 9 

/ COMMAND PROGRAMS 

Thip / TELEMETRY FORMAT -.1-tAint information Obtain oki3 :1 the national "kiln Meeferrg of the 1046414.1 &Alft.. t.; S.C., Suction 793 and 794. Its tronstili „. .h of as contents in t.r. .any ,n.h• ad 'meson is gvahibited by bfw 

it 4?", !!,-. • ' SPEDIIAL 
r 

ORO APPROVED FOR 

RELEASE 1 JULY 

`(FESS REQUIRED 

:;FACE PROGRAM 

63 

YErdikLiHPFULLEKA 

WHS - 311 

Page 151 

MOL ASA APPLICATIONS Q "A" 

COST ESTIMATE SUMMARY 

MODIFICATIONS TO FLIGHT 6 OR 7 

(R. O. M.) 

$27. OM • DEVELOPMENT AND MODIFICATIONS 

• SUPPORT MODULE MODIFICATIONS (14.0) 

ENG. - DESIGN CHANGES 4. 0 

/ MODIFIED SM 4.0 

/ TEST QUAL. VEH.. FOR #6 4. 0 

/ STATIC & DEVELOPMENT TESTS 2. 0 

LM MODIFICATIONS (13.0) 

ENG. - DESIGN CHANGES 5. 0 

MODIFICATIONS TO LM (ADD. HDWR) 4. 0 

/ AUGMENTED QUAL. TEST 2. 0 

/ STATIC & DEVELOPMENT TESTS 2.0, 

• REVISION OF ON-BOARD SOFTWARE PROGRAMS 

• SYSTEMS IENGINEERING*tr 

• • GgELTDd T.1:0 2. 0 

• SYSTEMS g:./'Avl 8. 0 

eA6Et41.4..> 7. 0 

----- 

FISCAL YEAR 1968 1969 1970 

MILLION DOLLARS $10. 0 $25. 0 $14. 0 

$ 5. OM 

$17. OM • 

TOTAL $49. OM 

DOES NOT INCLUDE NASA PECULIAR COSTS 

• 1:04e. Iho ..• 1 f.farmairan'affacting naltona • I 

''.4.1•ss wchin 'the mooning of filo• • .- t 

:1111tist.*72" 

• ED AT 12 YEAR 

l=07 AUTOMATICALLY 

PECUWS!Fir:D. D00 DIR 5200.10 

ftlf. ! .•"'f" 

!)oldt. 4:•• •• 

••■••!—.— •••.r 4ir of ifs consols in any 1111 1:elaigh::1■ ?tJ. parson is prohthiled.by, law: 
stej 

„, • 

NRO APPROVED FOR .• 

RELEAS 44./LY "Nilci 

• SPE,011.,i;NAY 

WHS-311 DLEINg Page 152 

MOL/NASA APPLICATIONS "A” 

PRELIMINARY CONCLUSIONS 

BASELINE1DEVELOPMENT PROGRAM 

• MANNED FLIGHTS #3/4/OR 5: 

I' 

✓ S-047, STELLER REFRACTION EXPERIMENT, APPEARS TO BE 

COMPATIBLE WITH MOL FLIGHTS 3/4/OR 5 AND WOULD REQUIRE 

MODEST INTEGRATION EFFORT. 

O AUTOMATIC MODE FLIGHTS #6 OR 7: 

/ CAPABILITY FOR ALL EXPERIMENTS EXCEPT S-042 & S-047 

J SIGNIFICANT IMPACT ON SYSTEM DESIGN AND TEST 

✓ EARLIEST LAUNCH DATE APPEARS TO FALL IN LAST. 

QUARTER OF CY 1971 

• 

, 

• SPEC!'" . C.CESS REQUIRED 

CLC-, PROGRAM 

,::R 

Nis +.4.; • niktunda../. Jnecting the nation& 

: I. i s within the meaning of the 

EiCionke., t . , U. S.C., Section 793 and 794. Its 

trens.ri:.1...4. co: fl: rehlImion of its contents in any 

mann*, to A.1 unculitcrized Person is prohibited by law. 

DO tiCoED AT 12 YEAR 

t:OT AUTCVAT5IC 

R Oq g 
• NRO APPROVED FOR 

RELEASE 1 J 

1.•"11 

I • 

SYM 

WHS- 311 

Page 153 . 

.4 

• 

MOL/ NASA APPLICATIONS "A" 

POSSIBLE SEPARATE VEHICLE CONCEPTS 

SPEML HANKINS 

.. h f ,:, MIERVALS; 

.isiL0 AFTER 12 YEARS.: 

uU DIR ,5200.10 

H• • - il:f ntlocting the national 

. ^s •A;i•Sin the meaning of the 

Espis.n.0 v 1. ;•. S.C... Section 793 and 794. Its • 

tray,n.;,-11, . :oeole■ Ion of its contents in any 

monncr ro An unauthorised -person it prohibited by law. 
I do thrormtton Aftcring tht national 

:Nose,' ret.O.s within the meaning of the 

ion, I S stnis!k►h .x ,rave. 3.son of its contents in saying». to ai onciAritti,11,911.4rssr is oushibilell by bow.. 

—TMMt tiff fikt— 

SPEtak HARD 

1)0WM. .t Al 3 I ooi iN'IERVALS; 

..,;1-1:if) AFTER 12 YEARS. 

oOD DM 5200.10 

-.NROAPkOVED FOR 

RE At !•9.,.h 

YANDLING 

WHS - 311 

Page 154 ,., 

• :1, • 

AIN 

MOL/NASA APPLICATIONS "A" 

POSSIBLE SEPARATE VEHICLE APPLICATION CONCEPTS 

• • CONCEPT A 

1. BASELINE VEHICLE 

(LESS MISSION P/L EQUIP) 

2. .30 DAY SYSTEMS QUAL 

3. APP. "A" PACKAGE 

4. BIO- TEST (P11 AND P12) 

5.. AIRLOCK 

CONCEPT B 

1. BASELINE VEHICLE 

(LESS MISSION P/L EQUIP) 

2. 30 DAY SYSTEMS QUAL 

3. APP. "A" PACKAGE 

4. BIO-TEST (P11 AND P12) 

5. AIRLOCK 

6. EXTENDED DURATION CAPABILITY (A..30 DAYS) 

/ ELECTRICAL POWER (CRYOGENIC TANKS AND FUEL CELLS) 

/ POWER CONDITIONING. AND DISTRIBUTION 

EC/LS EXPENDABLES ' 
SEC TI 

A RLOCK 

048 

NRO AI-PROVED FOR 

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J A I -T 

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Page 155 

POSSIBLE SEPARATE VEHICLE APPLICATION CONCEPT A 

illAHD.51 

EXPERrMENTS P11 AND P12 

(BIOMEDICAL AND PHYSIOLOGICAL 

EVALUATION) 

0 50 

44C 

044A 

057 

041 

ADDITIONAL 

A VAI LAB LE 

• VOI AIME 

049 

046 

LB 043 '47 c0 

is 'MISSION DURA.TION' t 30 DAY t{;111(141WateEiri 

fltESSI.TRIED)V9I.,,IJME arrc,;..vpri■Tp AIRLOCK) 

• EXPERIMENT pAYIAPAP 

0 f'"ri€44 ' ADDITIONAL AVAILABLE VOLUME 

011\IP4PtSP.I4 1?) if don/ 4onlains ink/motion affecting the nation.( 

fense of :h. '' 1:,d • his within the mean 

■ianase, L. I • chon • a • . lid 

c: it 4.4 ion of its contents in Mk. 

"Ike to yo,o h ..ses is prohibited by 1.1.4: 

1 r 

cat 

1125 

.tAtii„+,pu + P12 

••• 1700

wt 

Xj,:7 7Tc.i.,. r. 

\tilAbo XT 3 YEAR 
NRO APPROVED FOR 

RELE 

AT 12 YEAR 

" UTOMATICALLY 

OIR 5200.10 

DO 

na.. SL 

POSSIBLE SEPARATE VEHICLE PERFORMANCE 

CONCEPT A 

• ORBIT ALTITUDE 125 N. MI. CIRCULAR 

• ORBIT INCLINATION 5 80o 

• T-III M (PAYLOAD SELF INJECT) 32, 500 LBS 

ORBITING VEHICLE 

/ MISSION DURATION 30 DAYS 

/ O. V. DRY WEIGHT 19, 100 LBS 

/ NASA APPLICATIONS "A" PKG 3, 500 LBS 

/ BIO- TEST PKG (P11, P12) 600 LBS 

/ 30 DAY EXPENDABLES / 2, 200 LBS 

/ AVAILABLE DISCRETIONARY PAYLOAD 7, 100 LBS 

• SPECiAs.. f•CCESS i•iEQUIRED 

CLASS::::: SPACE PROGRAM 

NUMBER 

This docuT;iero c?ntsins informition allecting she national 

defense. a in Slates within the meaning of the 

Lip's:nal:le Laws, fi,1.• >fJ U.S.C.,Ser.tion 793 ansi 794.1ts 

tvanstr.itti,:ht o th- e..zlation of its contents in any 

na.nner to en emu h., i.e4 Nation is Prohibited by few. 

4,0 • 
4-) 

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AmasIlaml■•••••... 

.WHS-311 

Page 157, 

POSSIBLE SEPARATE VEHICLE APPLICATION - CONCEPT:A_ 

SPECNI RINDINO 

• 

EXPERIMENTS P11 AND P12 

(BIOMEDICAL AND. PHYSIOLOGICAL 

EVALUATION) 

049 

046 

'SECTION A-A 

- SPARES r-A 

TION C-C 

EXTENDED .DURATION 

CAPABILITY 

LA 18 1 3 FT 042 LB 043 047 L. 04 48 

MISSI,9N DURATION 

I • j i/t 1 Ai( t.. t.P.) • - /-'t e.),c/c) 

• PRESSURIZED VOLUME (INCLUDING AIRLOCK) 

• eXPAriaNt stt.ktLdAiYi 

60 DJ).y. ra-jrz,Naltuodrater-1-. , 

1125 CCU T. 

ad "NI 14 /A E .4 t 

NASA APP. "A" + PIP+ P12 

/1V 

• ADDITIONAL AVAILABLE VOLUME 

1400 CU. 

CIO CU 

snot 

lta7A 

.mistio.1 of 

wr to an unauthaelred nerson is prohibited by law. 

(.UNPRESSURIZED) 

On. netItirt,

11 iftforfuet.ui..11001f11) inG rhino. 

Sthita in* Meaning of 'hi 

I; 14 18 U.S.C., Section 793 and 794.1ts hlti cs% AC 

''.10 

DECLti;.7`..;;, ILL) 3 11 

HAN1LING 
60 DAYS 

21, 000 LBS 

3, 500 LBS 

600 LBS 

4, 400 LBS 

3, 000 LBS 

NRQ:OPROVED'FaR 

RELEASE 

1912 111 YLANff,UNL:

H

g

S

e

-311 

17: 1 58 

POSSIBLE SEPARATE VEHICLE PERFORMANCE 

CONCEPT B 

• ORBIT ALTITUDE 125 N. MI. CIRCULAR 

• ORBIT INCLINATION 80

o 

• T-III M (PAYLOAD SELF INJECT). 32, 500 LBS 

ORBITING VEHICLE 

1 MISSION DURATION 

/ 0. V. DRY WEIGHT 

1 NASA APPLICATIONS "A" PKG 

BIO- TEST PKG (P11, P12) 

60 DAY EXPENDABLES 

1 AVAILABLE DISCRETIONARY PAYLOAD 

SPEC.", ACCESS REQUIRED 

CLiQS;Fia'D SPACE PROGRAM: 

t`!!!' ''3ER 

This docu7n;i7 ‘..tonri4ns informatiorrattecting the nationel 

defense ..)1 ■11.• .U.Pcd Siates within the meaning of the 

Esploriara Laws, Tide 18 U.S.C.. Section 793 and 794. Its 

transmission or the revelation of its contents in any 

manner to en unauthorised parson Is prohibited by law. 

DOV -C:QADED Al 12 YEAR FE6.11 4E LI A MATICALLY 

IR 5200.10 
MOUIRED 

AC.E PROGRAM 

...,) t.r 12 YEAR 

N 

' 'eph ^. ;'\11CALlef 

• •• •NRO'APPROVED FOR 

•• : 1h u D WHS -31 1 

Ile159 

POSSIBLE SEPARATE VEHICLE 

COST ESTIMATE SUMMARY 

FY 68 69 70 71 TOTAL 

• VEHICLE 

« 

DEVELOPMENT 66.5 79.0 30.5 1.0 177. 0 

FLIGHT SYSTEM .2 29.5 39.0 16.3 85. 0 

6677 gig.5 69.5 1177 262.0 ** 

• B/L PROGRAM 58.0* 

SCHEDULE IMPACT 

TOTAL REQMTS '68 124.7 magi=gem 

. . 

. 

: 

* B/L PROGRAM FUNDS FROM FISCAL YEARS 69 - 71 REQUIRED IN FISCAL YEAR '68 

DUE TO INCLUSION OF ADDITIONAL NASA LAUNCH VEHICLE IN FISCAL YEAR '71. 

** DOES NOT INCLUDE ANY NASA - PECULIAR HARDWARE, SUPPORT EQUIPMENT,. 

SOFTWARE, OR PROGRAM MANAGEMENT COSTS. 

• 

ciefet • I' 

" 

martricir 

• 

; • • •( •J-1•4t/zcting the national 

It:: mr...unng of the 

•.4S. C., ftetlion 793 and 794. Its 

fan of ils con;ents in any 

i•ge: ;arson if prohibited by larl 

• • 1 A . 

. pele:•40.•••r!".1.rverennho.r, 
SPED 

- DEV. 60 DAY ON-ORBIT STORAGE 4.0 5.0 3. 0 

ADDN' L PROD. FACILITIES - 

- PIRXEMSTARMCroaLING 

t I SP54141; HANK 

5.0 

66. 5 0. 

c, AP -Vf_ \- t83 O 

0*-11 'FZIELEASE) .4,0114021)1 ROGRAM 

,;•f 

.■,;* L 

:sic n 

to 

Lx_ . 

INTER V OF 

C. 

71 

nittem Jitectino the nations., 

, : '•. oti•hin the meaning of the 

• !: ....S.C., Section 793 and 794. Its 

Cr ,:,.1;:ion of its contents in any 

par ma, h.4 L1 

POSSIBLE SEPARATE VEHICLE 

DEVELOPMENT COST ESTIMATE 

FY 68 69 70 

.• AT 12 17(04 

AUTOMATICALLY 

• p., a.. 11 

TOTALS 

LAB. VEHICLE 

ENG. DEV, & TEST 

6. o 1.5 .5 

1. 0 

5. 0 

2. 0 

1.0 

. 1.0 

15. 0 

25. 0 

15. 0 

5. 0 

10. 0 

15. 0 

5. 0 

- SYSTEMS ENG. & INTEGRATION 7.0 

- SUB-SYSTEMS ENGR. (EPS, CRYO, MM)14. 0 

- SUB-SYSTEM TEST 

- AGE INTEGRATION 

- MISSION SIMULATOR ADAPTER 4.0 

- QUALIFICATION TESTING 6.0 

- AIR LOCK DEVELOPMENT 3. 0 

10. 0 

10. 0 

3. 0 

5. 0 

8. 0 

2. 0 90. 0 

' HARDWARE 

-. SUB-SYSTEM DEV. HARDWARE 

- SIMULATORS 

- SUBSTITUTES 

- OTHER (SPEC. TOOLING, 

TEST EQUIP. ) 

- QUAL TEST VEHICLE AND 

MM STATIC 

OTHER 

- TEST OPERATIONS 

- PROGRAM MANAGEMENT 

(CONTRACTOR) 

GSE/TD 

10.0 10. 0 

1.0 

1. 0 

1. 5 

2. 5 

2. 0 

4. 0 

•1.0 

5. 0 

1.0 

2. 5 

2. 5 r 

5.Ô 

4. 0 

7. 5 

2. 5 

.10..0 

25. 0 49. 0 

2.0 '3.0 

3. 5 3.0 

2.0 2. 0 

2. 0 

2. 0 

1. 0 

' 5 

7. 0 ' 

9. 0 

5.0 21. 0 

GEMINI B 

12. 0 

5.0 

12.0 

5. 0 

1 
- LAUNCH OPS, NOT INCLUDED OM tab 41, 

68 69 70. 71 

5. 2 41.0 3, 0 

18. 0 15.7 4.0 

6.0 12.0 3.0 

6.0 

2 .3 .3 .3 

NOT INCLUDED 

6. 0 

TOTALS 

19. 2 

37. 7 

21.0 

FY 

GEMINI 

LAB, VEHICLE 

T-III M 

RECOVERY, TRACKING, 

ETC, 

GSE/TD 

NASA PECULIAR 

- HARDWARE 

4., :I .40 

NRO APPROVED•FC/R"`' 

RELEASE 1 JUL 

PECU. 1. ik!:CESS REQUIRED 

CLAS3411ED SPACE PROGRAM 

NUMBER /44'-• 

SP-E6LAL RANDJRCge311 161 

POSSIBLE SEPARATE VEHICLE 

FLIGHT SYSTEM COST ESTIMATE 

Lfr 

•• 

this documels iontains information affecting the national: 

Moose cf 11:i:n4 Statcs within this meaning of die 

(spkstuls, 1,s-v s, '.S U.S.C., Section 793 and 794. bs 

i 'h •■ v«-.,1 stion of its contents in any 

onAr.neir h- 1-AO 'warn is DtPhibilid by Iasi, 

DOWNGRADED •AT 12 'YEAR 

AUTOMATICALLY 

OD DIR 5200.10 
NRO APPROVED FOR 

REL MUNI WHS-311 

Page 162 

POSSIBLE SEPARATE VEHICLE 

MOLL FUNDING SHIFT DUE TO RESCHEDULING 

PROGRAM SCHEDULE IMPACT FY 1968 

GEMINI ' 8.0 

- LAB VEHICLE 39.0 

- T-III 11. 0 

• '58. 0 

SPECIAL ACCESS REQUIRED 

CLASS1FiED SPACE. PROGRAM 

DOWNGRADED AT 12 YEAR 

INTERVAL:=, NOT AUTOMATICALLY 

DOD DIR 5200.10 

This document cOntelns informatiOn effecting the national 

defense of the United States within the meaning of the 

Espionage taws, Title 18 U.S.C.. Section 793 and 794. Its 

transmission or thy revelation of its contents in any 

meow to an unsisilwi .e4 -orson it prohibited by law. SPE 

. ' • •■■.• • 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

MOL BASELINE PROGRAM 

SEPARATE FLIGHT VEHICLE 

SCHEDULE ESTIMATES 

'AV-HS-30 

Pake .163 • 

FY1 68 I FY1 69 FY'70 FY'71 FY'72 FY'73 

CY'67 CY'68 C Y ' 69 CY'70 CY'71 CY'72 

"APPLICATIONS A" EXPERIMENTS 

(14 EXPERIMENTS) 

FLT. HDWE. DEVELOPMENT 

DELIVERY OF FLT. HDWE. 

EXPERIMENT INTEGRATION 

POSSIBLE LAUNCH DATES 

SATURN/APOLLO (SIVB REVISIT) 

METEOROLOGICAL SATELLITES 

NIMBUS-8 

NIMBUS-D 

ATS-D 

11=2222Z:=2 

SPECIAL HAMMING 
• DO Vi i4GRAUED AT 12 `iiAR 

ER I MAliCALLY 

VIR 5200.10 

cROVd6f 

L JO 

S REQUIRED 

CLAS :ED SPACE PROGRAM 

N MEER FE-A, 

GROUND RULES FOR COSTS SCHEDULES 

POSSIBLE SEPARATE VEHICLE 

• NASA FLIGHT (FV-8) IN SEPT. 1970 

• NASA VEHICLE (FV-8) AND AIR FORCE VEHICLE (FV-3) ARE BOTH MANNED 

SAME PREFLIGHT TEST OBJECTIVES 

%/ COMPLETE DYNAMICS TEST FOR FV-8 LAB"VEHICLE 

ACOUSTIC AND STATIC TEST FOR FV-8 MISSION MODULE 

✓ SEPARATE NASA MISSION MODULE QUALIFICATION ARTICLE 

ELECTROMAGNETIC COMPATIBILITY TEST MUST BE IN FV-8 FLOW 

f AT LEAST TWO COMPLETE SETS OF NASA EXPTS REQUIRED 

(COMPATIBILITY TESTS & FLT. ITEMS + BACKUPS) 

• QUALIFICATION OF NASA VEHICLE FOR 30 DAY MISSION DURATION ONLY 

• SCHEDULING INTERFERENCES REQUIRE 

PROVISION OF SEPARATE NASA ASSEMBLY AREA @ DAC, HUNTINGTOWBEACH 

,/ SEPARATE NASA MISSION SIMULATOR ADAPTER 

✓ TWO STATIC TEST FACILITIES REQUIRED 

✓ NO THERMO VACUUM FACILITY DOWN TIME OVER SPAN OF 20' MONTHS 

J . ECLS ACCELERATION (5 MONTHS IN ADVANCE OF 12 MONTH SCHEDULE) 

• COSTS INCLUDE AEROSPACE GSE AND TD 

O. NASA EXPERIMENTS WILL BE. 

 AVAILABLE JANUARY 1969, FOR INTERFACE COMPATIBILITY 

TESTS .• • • 

• ONE LAUNCH - NO FOLLOW.-ON SCHED. OR DOLLARS • 

• 

This'clecvninnt 'leo:tains information allocting the national 

' '..dafenie cl 'h U. ilo.d wi-hin the meanino of the 

Elpionopot Tiiie 18 U.S. C., Section 793 and 794. Its 

transmission a ths roolotion of its coolants in any 

Matinee lo an LIftwthorized 0011100 is prohibited by 

'7'4. .,••■• ••••■*--- ,,,,, :•.- • • • 

-1771[0.7 
NRO APPROVED FOR 

. RELE 

DOW"if )._u A 1 3 r LAN IN I EliVALS, 

DM; AFTER 12 YEARS. 

DUD UIR 5200.10 

CON7:DENTIAI 

SPEIAIL HANBUNG 

WHS-311 

Page 1.65. 

4 . • 

PROGRAM MANAGEMENT INTERFACE CONSIDERATIONS: NASA/DOD 

• • SPECIFIC RESPONSIBILITIES/DEGREE OF PARTICIPATION HAS NOT BEEN 

k 

DEFINED 

• ASSUME NASA TO.SUPPLY (FOR PURPOSES OF STUDY) 

• EXPERIMENTS QUALIFIED TO MOL SPECIFICATIONS 

• f APPLICATIONS "A" EXPERIMENTS 

J PHYSIOLOGICAL AND PSYCHOLOGICAL TESTING EXPERIMENTS 

• MANAGEMENT OF EXPERIMENTS DEVELOPMENT, TEST AND 

ACCEPTANCE 

INTERFACE REQUIREMENTS 

CONFIGURATION CONTROL 

./ INTEGRATION ACTIVITIES, SCHEDULES, MILESTONES 

• EXPERIMENT AGE & SUPPORT REQUIRED AT FACTORY AND 

LAUNCH SITE I* 

• EXPERIMENT DATA REDUCTION AND DOCUMENTATION 

( 

D 

This docunuso;

• 

influnatiOn affecting the,nattonw 

defense cf Uoitocl s within the mooning of the 

ftplonsgi: U s.C.,'Section 793 and 794. Its 

• Issolunittioo or III.' :.(rf <Melon of its contents in any 

Manna, to On siossuibosisod aatson.is wohibibad by law. 

SIM HAN 

CONIIMAL 
4(4! tiv, ‘.4• • r Er;(:, r-- 

WO AP, P 

:e1.! 'iREtEASE•1 

—311 

166 

SPEC! ACCESS REQUIRED 

CLI.,MED SPACE PROGRAM 

MOL/NASA APPLICATIONS "A" 

POSSIBLE SEPARATE VEHICLE 

PRELIMINARY CONCLUSIONS 

SEPARATE MOL VEHICLE FOR COMBINED NASA APPLICATIONS "A" EXPERIMENTS 

' AND PROLONGED BIOMEDICAL TESTING IS TECHNICALLYFEASIBLE. 

LAUNCH IN LAST QUARTER OF CY 1970 APPEARS POSSIBLE, BUT WOULD REQUIRE 

RESCHEDULING OF MOL DEVELOPMENT FLIGHTS #1 & #2, & SIGNIFICANT TEST 

FLOW MODIFICATIONS. 

.UNRESOLVED PROBLEMS REQUIRING FURTHER CONSIDERATION 

LAUNCH DELAY OR FLIGHT FAILURE.:OF:T.HE FLIGHT!WOULD 

RESULT IN. MOL 'PROGRAM SLIP; 

SERIOUS DIVERSION OF EFFORT DURING EARLY, CRITICAL PHASE 

.OF MOL PROGRAM; 

LARGE—SCALE ENGINEERING AND MANAGEMENT RESOURCES 

REQUIRED TO MAINTAIN SEPARATE DESIGN, TEST, INTERFACE, 

TRAINING, AND PROGRAM DOCUMENTATION 

IMPLICATIONS OF "COST SHARING" APPROACH: 

PROGRAM MANAGEMENT AUTHORITY AND RESPONSIBILITY 

DOD/NASA INTERFACE' STRUCTURE 

IMPACT ON MOL DEVELOPMENT PROGRAM FUNDING 

r Lk!.ERFACEIDEFINITIONS INV6LVED IN PROGRAMS YiriT.P1 j, ) . 

DIFFERENT OBJECTIVES. 

re.o.• 

.,.Pvlillit,iatorreasitteafteeting the national %%Ain the meaning of the 

kipon■dt Titt It U.S.C.. Section 793 and 794.14 • 

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• 

SUBSYSTEM LIFE EXTENSION 

TYSECREQPIECIAL MAIM 

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1471.7SPECE HANDLEINO 

OUTLINE 

SUBSYSTEM LIFE EXTENSION 

WHS-311 

.Page 168 

• STUDY OBJECTIVES 

• LIFE EXTENSION APPROACH 

• STUDY ROADMAP 

• SUMMARY OF EARLY STUDIES 

• SUMMARY OF RECENT STUDIES 

• LIFE EXTENSION CONCEPTS 

• FAILURE EVENT AND EFFECTS SUMMARY 

• LIFE EXTENS1ON'APPROACH BY SUBSYSTEM 

• LABORATORY RELIABILITY AS FUNCTION OF MISSION DURATION 

• WEIGHT CONSIDERATIONS FOR SUBSYSTEM LIFE EXTENSION 

• COST ESTIMATE FOR EXTENDED LIFE SUBSYSTEMS 

/ NON-RECURRING 

/ RECURRING 

MAINT/REPAIR/REPLACEMENT TIME VS MISSION DURATION 

• IMPORTANCE OF MAN'S ROLE 

/ MAN VS REDUNDANCY 

UNIQUE ABILITIES FOR TROUBLE SHOOTING/CORRECTIVE ACTION 

/ SPECIFIC EXAMPLES FOR AIRCRAFT AND SPACE FLIGHTS 

• CONCEPT OF MEAN MISSION DURATION 

• SUMMARY SPEW, MMHG 

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SUBSYSTEM LIFE EXTENSION STUDIES 

o OBJECTIVES 

I DEFINE MEANS TO EXTEND SUBSYSTEM OPERATING TIMES TO ACCOMMODATE 

MISSION DURATIONS OF 60 DAYS OR LONGER WITH NO APPRECIABLE DEGRADATION 

IN THE PROBABILITY OF MISSION SUCCESS. 

/ IDENTIFY LIMITATIONS DUE TO FAILURE-RATE, WEAR OUT, Si STORES, DEPLETION. 

DETERMINE OPTIMUM DESIGN MIX BETWEEN ON-ORBIT MAINTENANCE/REPAIR/ 

SPARES REPLACEMENT AND REDUNDANCY. 

I ESTIMATE COSTS TO ATTAIN EXTENDED OPERATING TIME FOR SUBSYSTEMS 

APPROACH . 

SUBSYSTEM-BY-SUBSYSTEM ANALYSIS TO DETERMINE METHOD(S) UTILIZED 

SUCH AS: 

I "STRETCH" QUALIFICATION TESTING AND DESIGN MODIFICATION/UPRATING 

EXPLOIT OVERDESIGNED CAPABILITY WHEREVER PRACTICAL 

IMPROVE ACCESSIBILITY FOR MAINTENANCE 

REDUCE WEAR-OUT RATE 

I ON-ORBIT MAINTENANCE/REPLACEMENT/REPAIR BY FLIGHT CREW 

PREVENTIVE MAINTENANCE FOR WEAR-OUT LIMITED ITEMS 

CORRECTIVE MAINTENANCE BY REPLACING FAILED ITEMS WITH SPARES 

MALFUNCTION DIAGNOSIS AND REPAIR WHERE FEASIBLE 

I ADD REDUNDANCY 

MALFUNCTION REQUIRES IMMEDIATE SWITCHING FOR SAFETY OR MISSION 

MAINTENANCE NOT "PRACTICAL BY REASON OF COMPLEXITY OR TIME 

✓ ADDITIONAL DEVELOPMENT 

WHERE OBJECTIVES CANNOT BE ATTAINED BY OTHER METHODS 

PECIAL HANDUNG 

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MAINTAINABLE TV, tare BAND RECORDER, TATA AND vrea RECORIER ( COVUEXCATION5 ) 

REDMAN FUEL CELLS (PMER) 

REDUNDANT TIME PROGRAMMER; TINE CODE GENMATORNTRANSCEIVERS S.BAND 

BEACON, HEADSETS, MORMONS (COMMUNICATIONS) 

REDU=ANT SUPERCRITICAL TALE BEATERS, TRANSDUCELE. PLUS commas AND 

PLUS= (EC/IS ) 

MOUNT NEAT TRANSFER LOOP WM) 

ila DAC APR31• •64 

Wit SZPR. '64 ' I 

SPEAL1Li. 1a IDLING 
N RPRoLFn FOR 

WEIGHT PENALTIES FOR TWO TYPES OF WHS- 311 

Page, 186 

• .1, 

(0.0n.13,Q.A I 

ELEASE 1 JULY 2015 

REDUNDANCY AS A FUNCTION OF 

MISSION DURATION 

30 40 50 60 

MISSION DURATION IN DAYS , 

15 20 

. 

. 

i .■ 

• 

. 

10,3 

OW% E:11004t. 

141 f‘1% 

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IN-FLIGHT MAINTAINABLE SYSTEM 

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. 

. 

• 

1 ' 

. • BASIC SYS. CONSISTS OF APOLLO 

SCS + HORIZON SCANNER + PWR. 

INVERTER WEIGHT: 250 LBS. 

I I 

. 

120 

110 

100 

90 

80 

70 

60 

50 

40 

30 

20 

.10 

0 

SPECUI NAKOLIIK1 
NRO APPROVED FOR 

RELEASF Y 7n1 

WHS-311. 

Page 187 . 

RECENT STUDIES SUBSYSTEM LIFE EXTENSION 

ALL ASSOCIATE CONTRACTORS 

/ DETERMINATION OF COMPONENT ON-ORBIT ACCESSIBILITY 

• DAC 

1 LIFE EXTENSION TRADES OF ALTERNATE SUBSYSTEM CONCEPTS 

/ UPDATING OF COMPUTERIZED SYSTEM MODEL AND RELIABILITY 

EVALUATION 

AEROSPACE 

I ANALYSES OF ON-ORBIT SPARES PROVISIONING 

I/ EVALUATION OF ACCESSIBILITY OF SUBSYSTEM COMPONENTS 

I CAPITALIZATION OF MEAN MISSION DURATION CONCEPT BY 

PROPER DESIGNATION OF STORES DEPLETION TIME FOR CERTAIN 

SUBSYSTEMS • 

ROLE OF MAN. .BACKUP MODES ANALYSES, .FUNCTIONAL VERSUS 

BLOCK REDUNDANCY 

DETERMINATION OF THE PROBABILITY OF SYSTEM BEING OUT•OF• 

COMMISSION. SUBSYSTEMS AFFECTED BY WEAROUT AND STORES 

DEPLETION REPLACED BY RENDEZVOUS AND RESUPPLY. 

DIVIELsnaL vilull 
SPIEML fad d Vir IS- 311 

Pagle 18.8 

Ili Ulf. 0.411.1 cl-s,14.ii 

1016;' 

ALP •-• 

- NRO APPROVED FOR 

RELEASE 1 JULY 2015 

FAILURE DIST BUTION FUNCTIONS FOR VEHICLE SUBSYSTEMS 

'TYPICAL CURVE FOR A 

SUBSYSTEM AFFECTED 

BY STORES DEPLETION 

(EXPENDABLES) • 

FAILURE RATE SUBSYSTEM 

FOR PARTICULAR USEFUL LIFE 

§UBSYSTrika RANDOM OR CHANCE 

FAILURES . • 

TYPICAL CURVE FOR A 

SUBSYSTEM AFFECTED 

BY WICAROUT FAILURES 

MEAN MISSION 

DURATION 

EARLY .../‘ 

FAILURES . 

MISSION 

START 

VEHICLE 

DESIGN LIFE 

DL tEXP 

two 

ktosstoN TIME .0. 

SP= NB. I 
PROBABILITY 

OF SYSTEM 

BEING OUT OF 

' COMMISSION 

Q (t) 

NRO APPROVED FOR 

REJ. t I JLYLY GU I 

SUBSYSTEM RELIABILITY AND PROBABILITY OF BEING Ov T-OF-COMMISSION 

D 4 

WHS-317.\ 

Page 189 

(E)SUBSYSTEM WITH REDUNDANT PATH AND. 

INFINITE SPARING CAPABILITY 

(D)SUBSYSTEM AFFECi ED BY WEAROUT OR 

S TOR ES DEP LF.T foN 

(c)SuiSYsTEM WIflI REDUNDANT PATH ON. 

COLD STANDBY 

1.0 

RELIABU.dTi 

R (tk 

(B)SUBSYSTEM WITH REDUNDANT PATH 

OPERATING AcTivKLY 

--- (A) SINGLE COMPONENT OR SUBSYSTEM PATH 

MISSION DURATION, t .Vi Zak. 

MISSION DURATION t 

Ft& 211. 
tub 

ttv 4AOf' S 

2/17/67, 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

TYPICAL 

SIMSYSTEM SCHEMATIC 

SUB-ASSEMBLY CONTRIBUTIONS TO SYSTEM T)ROI3ABILITY OF FAILURE 

LIFE EXTENSION OR 

M/R/R* CONCEPT OF 

COMPONENT ASSEMBLY 

COMM 

ECS- FAN 

SW- NOT APPLICABLE 

TO ALL COMPONENTS 

ttrrt 

ACTS- SCE 

P 

'T 

SINGLE PATH .' 

AFTER FAILURE 

pF SAME 

* M/R/R a MAINTENANCE/REPLACEMENT/REPAIR 

WEIS-.311 

Page 190 

PROBABILITY 

FUNCTION 

I. NO SPARING OR REPAIR POSSIBLE 

MAY HAVE REDUNDANCY TO ACHIEVE 

PART/AL PERFORMANCE 

(UNIMPROVABLES) 

2. REDUNDANT PATHS PLUS SWITCHING 

3. SPARING/REPAIR ONLY (SUBSYSTEM DOWN DURING SPARING/- 

REPAIRING) 

REDUNDANCY PLUS SPARING/REPAIRING 

(FINITE SOURCE OF REPLACEMENT UNITS) 

5. SAME AS 4. WITH INFINITE SOURCE OF 

REPLACEMENT UNITS 

LAST GOOD 

PrUNIT 

o 

4 

SINGLE PATH 

/DUAL 

• COOLANT LOOP, 

PROPULSION --r1 

r i 

t 

- .....4 p....- 

1... .....1 

trs-}1 

100 

P

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0 

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DUAL PATH 

NANDLIINI 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SP LIAR 1.tiB 

ACHIEVEMENT OF 60 DAY MISSION DURATION FROM BASELINE DESIGN 

Page 191 

COMPONENTS AFFECTED BY WEAROUT 

AT LEAST ONE COMPONENT (FUEL CELL) HAS BEEN IDENTIFIED FOR 

WHICH WEAROUT LIFE MAY BE < 60 DAYS. 

3 B. L. CELLS WILL BE SUPPLEMENTED WITH 3 ADDITIONAL CELLS ON 

COLD STANDBY. 

SUBSYSTEMS WITH STORES DEPLETION 

1/ PROPELLANTS - IMPULSE REQUIREMENT MET WITH B. L. STORED 

CAPACITY. 

j REACTANTS, OXYGEN, He -• 60 DAY REQUIREMENTS MET BY ADDITIONAL 

TANKAGE. 

COMPONENTS AFFECTED BY RANDOM OR CHANCE FAILURES 

GROWTH CAPABILITY INHERENT IN B. L. (REDUNDANCY, BACKUP MODES) 

IS FULLY UTILIZED. 

ADDITIONAL SPARES, TOOLS AND CREW TIME ARE PROVIDED FOR 

PLANNED MAINTENANCE/REPLACEMENT/REPAIR. 

SPECEIL HANDLEG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

(00010■•••••••■••■•0 IPEGRL11.—L' SPEalL Hi111,ndulAti 

SUBSYS'i em LIFE EXTENSION 

fir. V .4 , . 

3/10/67 

ALP 

WHS-3,11 

• Page 192 

SUBSYSTEM/ 

. COMPONENT 

EPS 

FUEL CELL 

DISTRIB. it 

CONTROL 

EC/IS 

CRYO STORAGE 

FLUID LOOPS 

MOLEC. SIEVE 

FAN, VALVES, 

TRANSDUCER 

TIMER, P. P. SENSOR 

ACTS- ELECTRONICS 

CIRCUIT CARDS 

GYRO it ELECT. 

H/S 4 ELECT. 

ACTS- PROPULSION 

' TCA'S 

TANKS it PROP. 

DISTRIBUTION 

LIFE EXTENSION APPROACH AND MIR/R PROVISIONS 

ADD 3 FUEL CELLS ON COLD STANDBY. NO ACCESS. ADDITIONAL 

SENSORS AND SWITCHING FOR STARTUP. 

SPARE TIMER. INVERTER AND 0. LOAD DEVICES. PROVIDE 

ADDITIONAL TEST POINTS AND ACCESS DOORS. 

ADD TANKAGE; SYS. SEGMENTATION MINIMIZES LOSS. NO ACCESS 

GROWTH CAPABILITY INHERENT IN B. L. REDUNDANCY. NO ACCESS 

B. L. HAS TRIPLE REDUNDANCY. CYCLE TO VACUUM. 

ADDITIONAL SPARING. EXTEND B. L. M/R/R PROVISIONS 

ADDITIONAL SPARING; CANNIBALIZATION WITHIN SUBSYSTEM• Added to B 

USE B. L. REDUNDANCY AND COMMON SPARING 

EXTENDED

/ BASELINE 

USE B. L. REDUNDANT HEADS AND CIRCUITRY PROVISIONS 

USE B. L. REDUNDANT MODES. NO ACCESS 

B. L. HAS REDUNDANCY; SYSTEM SEGMENTATION MINIMIZES LASS 

NO ACCESS 

COMM 

REC•VR, DTU ETC. 

RECORDERS 

DATA MANAGEMENT 

INSTR it MON/ALARM 

STRUCTURE 

USE B. L. REDUNDANCY, MULTPPATHS. PROVIDE SPARING 

MAINTAIN. POSSIBLE REPLACEMENT, PROVIDE ACCESS 

USE B. L. REDUNDANCY. M/R/R NOT UTILIZED IN 60 DAY DESIGN 

USE B. L. REDUNDANCY ON CRITICAL PATHS. UTILIZE COMMON SPARING. 

PROVIDE ADDITIONAL SEALS 4 LATCH KIT TO REPAIR HATCH. 

egudt:AL AKIBLCIKG 
NRO APPROVED FOR 

WHSO- 311 

Page 193 S] AL HAMM 

SUBSYSTEM LIFE EXTENSION 

ACCESSIBILITY FOR MAINTENANCE/REPLACEMENT/REPAIR 

GEMINI 13 

, 1111SYSIEM/ 

COMPONENT 

POSSIBLE PROVISIONS FOR 

TROUBLE SkIOOTING M/R/R(1) 

LOCATION ACCESSIBLE REQUIREMENTS 

:SAT TERIES ADAPTER NO REMOTE ACTT - 

VATE REDUNDANT 

UNIT 

PARACHUTE • NOSE NO NONE 

RETRO ROCKETS ADAPTER NO REDUNDANT 

ECS PUMPS CABIN SEC. NO . REDUNDANT 

NSTRUMENT. VARIOUS SOME REDUNDANT ON 

CRIT. COMP. 

:CS PROP.. TANKS NOSE SEC. NO NONE 

PROVIDE ACCESS PANELS 

• 

DD1TIONAL CONSIDERATIONS 

GEMINI STATUS MUST BE MONITORED 

. LOW PRESSURE WILL BE MAINTAINED IN VEHICLE TO ELIMINATE HARD VACUUM 

) M/R/R s MAINTENANCE/REPLACEMENT/REPAIR 
ALP - 5/18/66 

WHS-311 • 

Page 194, 

FAILURE EVENT ANL) EFFECTS SUMMARY 

•II 

CRITICALITY 

OF FAILURE 

-rarlawasaawrewc.v.a.ear.r.47.r.. 

• MISSION AI3ORT 

:DEGRADATION 

ESTIMATED 

TIME FOR 

CORR. ACTION 

•na-r14::7,.,r% mr• 

‹.'.24 HRS. 

REMARKS . 

I 

......4.1LV.Cit ,Pare • 

SWITCH TO STANDBY 

UNIT MAN BACK-U 

11 

DEGRADATION 

CREW SAFETY 

DEGRADATION <90 MIN. 

SHORTENS MISSION 

SAVE PROPELLANT 

TANK RUPTURE MAY 

RESULT 

SWITCH TANKS 

IMMEDIATELY 

DEGRADATION IMMEDIATELY 

rI 4 411 

11 

am. :#1:41114.404. 4Ik eni1011.01.4.441•1•41.000100... 

o POWER PLANT 

o CONTR/PROTECT UNIT 

o INVERTER 

o 7)C/DG CONVERTERS 

• CRYOGENIC 

41.41144,4*.•401.4.411110 14.••••••,..0 • 

PROTECT FUEL CELL 

SWITCH INVERTER 

SWITCH CONVERTER 

ISOLATE MALFUNCTIONED CR YO. 

LOOP 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

.......41,40.0111.•10..•■■••■■•=4.00.1 • 

o GYRO & ELECTRONICS 

• o CONTROL ELECTRONIC 

ASSEMBLY 

. LOSS OF ./',V CAPABILITY 

o THRUST CHAMB. ASSEM. 

o PROP. PRESSURIZATION 

o PROP. STORAGE/FEED 

1. LOSS OF ATTITUDE CONTROL 

• o NOR. SINS. & ELECTRONICS 

• 

ir • 

• .....44111..44■10 Zr.021•11•2146.114nrowmahrw pa. IrAteM•OWN•ainioNaftWasmole....10.114.010. 

EVENT/CRITICAL COMPONENT 

• Pr. ..-store.m.v.,.".1,....cort......-WYdr., 

3. LOSS OF ELECTRICAL POWER MISSION ABORT AFFECTS CREW 

SAFETY IN SHORT 

TIME 
CREW CONTINUES 

WITH TELEPRINTER 

AND COMPUTER/ 

DATA MANAGEMENT 

EQUIPMENT 

EVENT AND EITECTS SUMMARY (CONVI) 

I.JR0 APPROVED FOR 

, RELEASE 1 JULY 2015 

FA I LU 11.11 

ALP - Ii/Z0/66 • 

WHS- 317I 

Page 195 

•••■•■urao.....weaso unowslinsn. ,Im000r .....a.onaseammosat, 

ESTIMATED 

CRITICALITY, TIME FOR 

EVENT/CRITICAL COMPONENT OF FAILURE CORR. ACTION 

4. LOSS OF COMMAND & DATA 

IIANDLING 

o SIGNAL COND/PROCESSOR 

o TRANSMITTER 

'o RECEIVER 

o MULTIPLEXER 

o CONVERTER 

. o RECORDER & TELEPRINTER 

o COMPUT.F.:R 

REMARKS • 

...====wiagziammougnomsta 

CREW CONTINUES . 

WITH VOICE LANK 

DEGRADATION 

11 

It 

11 

DEGRADATION 

11 

11 

to 

11 

11 

<90 MIN. 

11 

11 

II 

11 

11 

11 

LOSS OF VOICE COMM. 

o SIGNAL COND/PROCESSOR 

o TRANSMITTER 

o RECEIVER 

o MULTIPLEXER 

o CONVERTER 

o VOCODER COMPONENTS 

o VOICE CONTROL CENTER 

<90 MIN. 

11 

*1 

II • 

11 

'IMMEDIATELY 

SPIECILIL WIELING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

ALP - 5/20/66 

WHS-311 

Page 196 

FAILURE EVENT AND Hi:TEC:TS SUMMARY (CONT'D) 

t. 

P ; 

.• 

1! 

• ' 

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• 

• 

Ft VENT/CRITICAL COMPONENT /

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ESTIMATED 

TIME FOR 

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REMARKS 

---,=--- -..1.-=`' .-...7. -. • - -......-. -

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• 

6. LOSS OF CABIN ATMOSPHERE 

. • ••• ' • • • ■ „ 

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DEGRADATION 

- II 

,1 

11 . 

IMMEDIATELY 

<90 MIN. • 

IMMEDIATELY 

<90 MIN. 

IMMEDIATELY 

MiNTROL- . 

. 

• 

. o FAN • 

o MOLECULAR SIEVE 

o P02 SENSOR 

o REGULATOR/VALVING 

o CRYOGENICS 

7. LOSS OF THERMAL CONTROL DEGRADATION 

. 

el 

n 

<90 MIN. 

11 

PROVOKES FAILURE 

OF TEMP. CRITICAL 

. EQUIPMENT... 

o PUMP 

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8. LOSS OF MONITOR & ALARM 

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WITHOUT INSTR. 

• 

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o' CONTROLLERS 

o ELECTRONIC CIRCUITS 

o DISPLAYS 

o TRANSDUCERS 

. . . 
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EC/LS 

INTERFACE 

•■••■••••••■•■■••■■••■•••••■•••••!•••■■■•••• 

FUEL CELL 

SYSTEM 

DISPLAYS 

CONTROL 

FUNCTIONS 

[ 

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STORAGE SYSTEM -:---" 

--- ------- 

LOAD 

CON TROL 

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CCT 13 REAK Ere' 

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REDUNDANT 

DC UNIT 

CONTROL 

• 

LOADS

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EVIAL DUNG 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

WHS-31 1 

SPETALNhirOLER Page 197 

F,LEcTRI(_AL, POW Ea sti)');;YSTI:;:M 

BLOCIC DIAGRAM 

WIIMMOM1101411.11~0~1111.11~0 •

As sIMMOMMOI 
ALP - 5/18/66 

liga.11KG 

k;LECTRICAL POWER SUBSYSTEM 

LIFE EXTENSION SUMMARY 

WHS-311 

Page 198 

ITEMS FOR STRETCH TESTING - FUEL CELL POWERPLANT 

-• PURGE TIMER 

- ELECTRICAL CONTROL AND PROTECTION UNIT(ECPU)i 

- INVERTERS AND DC/DC CONVERTERS - 

- ADDITIONAL STANDBY FUEL CELL MODULES • 

FOR 60 DAYS (INCLUDES ECPU) 

- VOLTAGE LIMITER SENSOR 

- INVERTERS 

- DC/DC CONVERTERS. 

- INVERTERS 

- PURGE TIMER . 

, • 

- ELECTRICAL CONTROL AND PROTECTION UNIT (ECPU). 

- SWITCHING AND OVERLOAD DEVICES (DISTRIBUTION) 

• -, DC/DC CONVERTERS 

• MINOR MODS DISCLOSED BY STRETCH TESTING 

.- NONE EXPECTED FOR 60 DAYS 

- CONSIDER USE OF LONGER LIFE FUEL CELLS 

NOW UNDER DEVELOPMENT 

REDUNDANT ITEMS 

SPARED ITEMS 

DESIGN MODIFICATIONS 

NEW DEVELOPMENT 

■••••■■■■••...... 

SPIECOAL HAMBURG 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 l*WP. 

laMAIAMOINC 

WHS-311 ..ftNN 

Page 199 

hwy. dr, *41 ft...WM .10 

UNPRESSURIZED COMP'2' I PRESSURIZED COMP'T 

REDUNDANCY AND SPARE UEPLACEMENT 

FUEL CELL POWER SOURCE 

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UNPRESSURIZED COMPARTMENT 

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FAILURE OF ECPU • 

POSSIBLE UNAVAILABILITY 

OF FUEL CELL POWER 

I SPARE THIS ITEM 

I A COMMONALITY OF EQUIPMENT 

*ACCESSIBLE IN PRES. COMP'T 

o FAILURE COULD BE CRITICAL. 

I TO MISSION SUCCESS • 

.1 o APPRECIABLE WT. ITEM 20 LB 

* X te FAILURE RATE/106Mums 

•■•••• 

/vs 1p • • v.., 

PIC4 HANDLING 

• -- - • ■ - • • • • • • ■ • - • ■ • .. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

FUEL CELL POWER SOURCE 

RELIABILITY VS MISSION DURATIONBASED ON FAILURE RATES 

WHS-311 

Page 200 

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WHS - 31 1 

1)0W1.:RS(.► ) IS YSTJ:1■4. Page 201 

REDICTED RELIABIUTY 'VERSUS ADDED SPARES AND REDUNDA.MGY 

FOR. VARIOUS MISSION DURATIONS 

1413 - 5/19766 

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ATTITUDE CONTROL A N D711, A tiSLATIQN SUBSYSTEM 

BLOCK DIAGRAM 
ITEMS FOR STRETCH TESTING - HORIZON SENSOR (H. S. ) 

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Arl'ITIME CONTROL AND TRANSLATION SUBSYSTEM 

LIFE EXTENSION SUMMARY 

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ENVIRONMENTAL CONTROL/L1FE SUP.PORT SUBSYSTEM 

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• •• •• •••••••• • ••••• .•••••,•••••••••••••••••••• •••••••••••••••■•••• a...B..4c. • • • • •• • • • • •• • • • ••• • .•••••■ ••• • • • •Ao.■• • ...••••••••,,,,e••••• •••••••••••••••• •■•■••••••. ••••••••■••••••••••••• 

UL G • 
5/18/66 

NRO APPROVED FOR 

RELEASE .1. JULY 2015 

SHEA.. YLAII.EA 

• 

• mrammisams.~...••■•••■•••••••■••••■••••••••••••V••••• 

ITEMS FOR STRETCH TESTING 

REDUNDANT ITEMS 

SPARED ITEMS 

DESIGN MODIFICATIONS 

NEW DEVELOPMENT 

' 

• POWER CONVERSION/CONDITIONING 

CONVERTERS (D-TO-A) 

EXCITERS 

I3ASEBAND ASSEMBLY 

DTU 

TWT 

- CREW CAN ESSENTIALLY "SPARE" BY 

SWAPPING CHANNELS 

. o SIGNAL CONDITIONING 

O REMOTE MULTIPLEXERS 

- NONE EXPECTED FOR 60 DAYS 

- NONE EXPECTED FOR 60 DAYS 

UHF TRANSMITTERS 

- SECURE DEVICES 

r 

1 

• •••••••••••••••• ■•••••••■••••••••••••••••••••••••••••• mow 

, 1r". ,..•=4.4...-nr 

\VHS - 311 

Page 212 

IN:intUNI E.:. N T ION / M ON I TO R. 7ALA Y FM 

LIFE EXTENSION SUMMARY 
NRO APPROVED FOR 

RELEASE 1. JULY 2015 

•■■•■•••■•■00000.0.00.0.0........0. • 

INSTRUMENTATION/MONITOR -ALARM SUBSYSTE:M Pa e 213 

SPE= HAN1 H2 FW13 5/19/66 

WHS-3771 

PREDICTED RELIABILITY VERSUS ADDED SPARES AND REDUNDANCY 

FOR VARIOUS MISSION DURATION S 

' 998 

.999 

• '1' 

. 40 .11 r' I to . - I L 

.30 V.I .._ 

..70 

. 60 

.50 

. 80 

. 95 

. 90 

. 99 

. 98 

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•••••• 

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0 240 . 27 0 3 0 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

FEU.- YANDIUNG . 5/18/66 

••••••■•••mws••■••■••• ats.s.•■••••••■■.....e.r...............•••••••■••••••••••••••••••• .••••••••••••••••••••••••••••••••••••••••••••••••.•••• ""*...' 

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Page 214 

• PIt..*.DICTED RELIABILITY VERSUS ADDED SPARES AND REDUNDANCY 

FOR VARIOUS MISSION DURATIONS 

DATA MANAGEMENT SUBSYSTEM WHS-311 

999 

' 

. 998 

rc

ry ! -r-irt, I , 1, 

11.4 • :IL 1-1-t 

• 

!- • r" 

1.11 ' 1111:1!1--1011. 

, • ; 

• .!i 1;t;1;1.:'• I 

• . • 11'i:111i! !It I s it 1. 

il! 0.14. 

' . • -; ;1* : ' . . 

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. 99 

. 93 

.90 

.t..1.!.1- :, !•1 

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.. I.; , .1 ....1.,.1,-.! .1 i.1..:;: !.:111 i"....i:....11 ..f.1.2-..;:d .1. :1: ,..i. I..... 

70 

..60 

50 

. 40 

'; • ! ' 

.30 J. 

0 50 450 

. .1.. 1..,..i..__'l.y;.... .i.:.i .1.-1.-:.--..••:: "-....-...::•:—.:. 1.': .": T. 27... t.ii::::" : 

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;.■ : - • ,.,'.1,' ,." .•.1 

i 

is 

..,. I il ',..:. . ••• 71 I' :........i17.i :... .. ■ . t. 

150 200 250 300 • 350 

400 .. :..:.....r..1... : ......:...., ...0.••• ,:.:.•!.. -...:.;.,.,. :•11 . 11- • '...!:' t•••• - ' 

AN (LBS) OF SPARES AND REDUNDANCY .. 

100 

SPCA LAG 

• 
NRO APPROVED FOR 

• RELEASE 1 JULY 2015 I 

PEIL HARIBLIINI ALP 5/18/66 

WHS- 311 

Page 215 

SERUCTLIILES SUBSYSTEM 

LIFE EXTENSION SUMMARY 

ITEMS FOR STRETCH TESTING 

REDUNDANT ITEMS 

SPARED ITEMS 

- RADIATOR 

- UTILIZE BASIC SYSTEM AS IS 

- DOOR SEALS 

- LEAK KIT. 

- DOOR LATCH KIT 

• DESIGN MODIFICATIONS 

NE ri DEVELOPMENT 

INCREASE WALL THICKNESS LAB AND RADIATOR 

FOR MISSIONS > 60 DAYS (MICROMETEOROID) 

CRITERIA) TO MAINTAIN Po= . 995 

- LENGTHEN FWD UNPRESSURIZED COMPARTMENT 

- NONE EXPECTED FOR 60 DAYS 

SPEC,AIL 
IN'HS-3 1 1 

Page 216 

• 999 

0 

L.4 998 

• .997 4- 

04 

0 .995 - 

O .

• 

993 

. >1 .990 ---- 

-7" 

30 DAY 

REQUIREMENT I , 

Ot• 74Ir •110 •• • no 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

paLifialAg FWB - 5-Z0-66 

-SUBSYSTEM LIFE EXTENSION 

S TRU CTUR E 

METEOROID CRITERIA IMPACT ON LABORATORY DESIGN 

!).1 • • "IVOMMIPMAIVIOIMMONW...0.S.CNIMISMISIONNIWIMIIIIIIIMP.M...••••••••••■•••••■■••■••ftrar.wwww.~....w

▪ 

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PROBABILITY OF NO PENETRATION VERSUS TIME 

1 

4 

• 

- Z. I LB/FT 

STRUCTURE 

..}71 

• 980 

ri 0 .970; 

o • 950 

a. 

.930 

.900 30 "-.66 1.(kr Z06 . 300 

ON-ORBIT DURATION.- DAYS 
.• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

S/40166 

WHS- 311 

LALIORATORT :mccun. 1 • Page 217 

PREDICTID =LIABILITY =MOS ADDITD SPAR AND LISDUNDANCT 

wort VARIOUS MISSION DURATIONS 

• 

• 

999 

.990 

. . • 

.99 

90 

.90 

:

11

• 

AO 

00 

.60 

. .90 

.40 

.30 

0 

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MI (MB) OT SPARMS AND ItIMUNDANCT, 

ELI HANDLING •••••••• •• 1111.. .....• • ..•-• 

""*.•••"!••••• ''••••-• • —ley 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 • 

ra",3 - 3.40,05 PE& WAD' IJN 

W1-1S-Ill 

Page 218 

VATZGHT COZI3.CDERAVON3 3UBSY3TE2.1 LIFE EXTralSZON 

LALIORATORY VEHICLE 

' 3000 

• PR! D/CTED /UCLIADILITY r011 LABORATORY MU= • SO 

, • ViE/GHTS INCLUDE 20% CONTINGENCY FACTOR 

.

• 

• 

2500 

2000 

! • • 

WEIGHT OF • 

SPARES ♦ REDUNDANCY 

1.500 

WEIGHT OT REDUNDANT 

COUPON EDITS 

3 

1000 

WEIGHT OF SPARES 

• 

500 

•r•ArNS=Ca•=t3- 4

▪ 

11•1•UMMIPSZW*AIMMUNSIMMIIIM:L.•••••••.... i;ro 

30 

▪ f:=2014 DURATION,‘,DAYS 

. . 

• •0 

Am•••••••••••• •10.4111••••■•••••••■■••••. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HARITTLIEG • FWD - 5/17/66 

WHS-;-311 

Page219 

SUBSYSTEM LIFE EXTENSICN 

NON-RECURRING A COST ESTIMATE FOR 60 DAY SUBSYSTEMS 

SUBSYSTEM NON RECURRING a COST 

o ATTITUDE CONTROL 7, 000, 000 

o • PROPULSION 10, 000, 000 • 

o ENVIRONMENTAL CONTROL/LIFE SUPPORT 6, 000, 000 

o COMMUNICATIONS/DATA HANDLING 4, 000, 000 

o ELECTRICAL POWER • 13, 000, 000 

FUEL CELLS . '5, dm 000 

CRYOGENIC SYSTEM 8,000, 000 

o MISSION P/L EQUIPMENT • .10, 000, 000 

o INSTRUMENTATION 1, 000, boo 

o 

STRUCTURE, PRIMARY AND SUPPORT 

GEMINI B 

7, 000, 000 

• - • 

60, 000, 000 

• 

• ^. 

Ulla 

k 
r \I 

SPE HAH.I0sJ 

WHS.-311. 

Page 220 

SUBSYSTEM LIFE EXTENSION 

RECURRING 6, COST ESTIMATE FOR 60 DAY SUBSYSTEMS 

rws - 5-19-66 I 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3 0 

SUBSYSTEM 

0 ATTITUDE CONTROL AND PROPULSION 1, 800, 000. 

0 ENVIRONMENTAL CONTROL/LIFE SUpPORT. 

291, 000 

0 COMMUNICATIONS/DATA IIANDLING 830, 000 • 

0 ELECTRICAL POWER SUBSYSTEM 1, 200, 000 ' 

(CRYOGENICS AND FUEL CELLS) 

0 MISSION P/L EQUIPMENT 700,000 

O INSTRUMENTATION 150,000 

• , 

0 STRUCTURE 600,000 

0 GEMINI 90, 000 

TOTAL 5, 661,000 

• 

SPE MIL NA 

• 

c r, pt. 4.1,6 t• t 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 71113 6/17/66 

On..1317ZIG VEVICLE SUBSYSTIZI LI73 MITEMETY.C.1 .

WHS- 311 

Page 221. 

MAUI=IANCE/REPALVREPLACZNENT TalE VERSUS • 

• • • MISSION DUIAATION 

1•111•11111111.111■11111111M110•11•110•1111■111111101110, 

NOTES: 

•UNSCHEDULED MAUITENANCE 

CALCULATED TM& reit WARE ZOITIPLIENT 1112PLACEMENT 

RASED OU PREDICTED vaunt= roa SPECIITTED MISS= 

DATION 

160. . O SCIODULED UALITENANCE • 

ESTMIATED AT 0.5 Hrt. PZR EMS= DAY tAVERAGO 

INSPECT/ON, PREVENTATIVE MAINTENANCE 

AVERAGE EXPECTED TINti 

PER MISS/ON DAY is 1.0 MAMMA. 

roa MAINTENANCE, REPAIR 

AND REPLACEMENT TAMCS 

• 

ECAL FAN/DRAPE 
NRO APPROVED FOR 

,RELEASE 1 JULY 2015 

• 

WHS- 311 

Page 222 NAKILE 

• ON-ORBIT MAINTENANCE/REPLACEMENT/REPAIR 

(BASELINE VEHICLE) 

ON-ORBIT MAINTENANCE/ 

REPLACEMENT/REPAIR 

PRELAUNCH CHECKOUT/ 

TEST/CORRECTIVE ACTION 

• ACCESSIBILITY 

• INTERCHANGEABILITY 

DESIGN PROVISIONS 

• ACCESSIBILITY 

• INTERCHANGEABILITY 

STATUS AN D OPERATING DATA 

• INSTRUMENTATION 

• MONITOR/ALARM & TELEMETRY & 

UMBILICAL 

• INSTRUMENTATION 

• MONITOR/ALARM & TELEMETRY 

TROU 

• EQUIP. TEST POINTS 

• PANEL & J-BOX ACCESS PANELS 

• CIRCUIT & PIN DIAGRAM & DATA 

1 . 

BLE SHOOTING 

• EQUIP. TEST POINTS 

• PANEL & J-BOX ACCESS PANELS 

• CIRCUIT & PIN DIAGRAM & DATA 

• AGE • 

• 

• 

• 

REPLACE FAULTY EQUIPMENT

• DISCONNECT & PLUG-IN FEATURES , 

AVAILABLE SPARE REPLACEMENT 

TOOLS AND TEST CHECK EQUIP. 

• 

• 

• 

DISCONNECT & PLUG-IN FEATURES 

AVAILABLE SPARE REPLACEMENT 

TOOLS AND TEST CHECK EQUIP. 

• THE DESIGN PROVISIONS, AND PROCEDURES TO PERFORM ON-ORBIT MAINTENANCE/REPLACEMENT/REPAIR ARE BASICALLY THE SAME AS REQUIRED FOR PRE-LAUNCH TEST AND CHECKOUT OPERATIONS. THUS, FOR ALL PRACTICAL PURPOSES, THE IMPLEMENTATION TO 

ACCOMPLISH ON-ORBIT TROUBLE SHOOTING AND CORRECTIVE ACTION IS INHERENT IN THE 

BASIC VEHICLE IF ADEQUATE SPARES ARE PROVIDED ON-ORBIT. 

'HANOURS 
FWD 5-20-66 

SFP111 Prirlfil\ 

SUBSYSTEM LIFE EXTENSION 

MAN VF.RSUS REDUNDANCY 

WES-311 

Page 223 

NRib APPROVED FOR 

RELEASE 1 JULY 2015 

1 

O MAN AND EQUIPMENT REDUNDANCY ARE. COMPLEMENTARY 

o SWITCH TO STANDBY UNIT WHEN TIME IS VITAL 

o MAN CAN FIX FAILED REDUNDANT UNIT WITHOUT SHUTTING DOW( SUBSYS. 

o REDUNDANT UNIT ON LO-DUTY CYCLE COULD PROVIDE SOURCE OF COMMON 

PARTS NEEDED IN MORE CRITICAL SUBSYSTEM. 

O WITHOUT REDUNDANCY 

• o CREW MUST NECESSARILY DEVOTE HIGHER DEGREE OF ATTENTION TO 

EQUIPMENT OPERATING STATUS AND "STATE-OF-HEALTH" - LESSENS . , 

TIME FOR OPERATIONS AND OUTSIDE OBSERVATION. 

0 HOW MUCH REDUNDANCY? 

; • • .7. 

• 

".: • 

o REDUNDANCY/SPARES SHOULD OPTIMIZE. CREW TIME FOR OPERATIONS, 

MONITORING AND CORRECTIVE/PREVENTATIVE MAINTENANCE. 

TIME CRITICAL FUNCTIONS FOR CREW SAFETY AND MISSION OBIECT/VES 

SHOULD BE BACKED UP WITH REDUNDANCY. 

AVOID CASCADING REDUNDANT COMPONENTS THAT WILL. REQUIRE . 

COMPLICATED VOTING LOGIC AND SWITCHING SCHEMES.' 

O. CREW MANAGEMENT OP REDUNDANCY . 

o CREW MUST MAINTAIN COGNIZANCE OF PRIMARY/STANDBY STATUS AND 

OPERATING TIME FOR REDUNDANT UNITS. 

AUTOMATIC SWITCHING MUST 13E "FLAGGED" FOR CREW ATTENTION 

AVOID SWITCHING BACK AND FORTH BETWEEN PRIMARY AND STANDBY 

UNITS (Elm LAW OF NEWTON EFFECT). 

. 

HANDLiNC 
17) 

p7P-- r 

.L0 5/19/66 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

WHS - 31 1 

Page 224 

SUBSYSTEM LIFE EXTENSION .* 

IMPORTANCE OF MAN'S ROLE 

UNIQUE ABILITIES FOR TROUBLE SHOOTING/ COMESTIVE ION 

I. MAN HAS REASONING ABILITY (UNMATCHED BY MACH/NE), 

REPROGRAM), AND VERSATILITY (CAN CORRECT ERRORS). 

ADAtp•fikeurrY CAN 

2. QUICKLY SENSES AND REACTS TO UNEXPECTED FAILURE 

3. IS CAPABLE OF REPLACING ANY OF A LARGE NUMBER OF 

IUMSELF AS A MULTI-PURPOSE SPARE). • 

4. IS SELECTIVE IN INSTALLING SPARES. • 

5.. CAN SENSE INCIPIENT FAILURES AND TAKE ALTERNATIVE STEPS PRIOR TO THE 

FAILURE OCCURRING AND PERHAPS SPREADING OUT IN SYSTEM. • 

Ah. DETERMINES WHERE OR WHAT FAILURE ACTUALLY IS (NOT JUST SYSTEM, WHICH! IS 

INSTRUMENTED, BUT AT PART LEVEL). 

7. CAN UTILIZE MAN /,GROUND COORDINATION TO DEFINE CORRECTIVE ACTION. • 

S. PROVIDES AN UNDERSTANDING OF REASONS FOR FAILURE. 

9. HAS ABILITY TO BY-PASS MALFUNCTIONS OF FAULT DETECTION.AND ISOLATION 

SYSTEM. 

10. CAN CANNIBALIZE PARTS OR COMPONENTS FROM ONE SYSTEM (NOT NEEDED AT 

THAT MOMENT) FOR USE IN A CURRENT CRITICAL SYSTEM. 

II, CAA CONTINUE UNDER CONDITIONS OF DEGRADED PERFOR1vLANCE, ATTAIN OPERATION 

WHERE AUTOMATIC SYSTEM WOULD JUST SI-TUT DOWN (OR WOULD NAVE TO AWAIT 

ANALYSIS AND SPECIAL INSTRUCTIONS). 

12. PROVIDES DETAIL INFORMATION FOR DESIGN IMPROVEMENT & FUTURE DEVELOPMENT. 

MODES. 

COMPONENTS (USING 
UNIQUE ABILITIES FOR TROUBLE SHOOTING/CO .... AC

• WHS-311 

Page 225 

. SUBSYSTEM LIFE EXTENSION 

IMPORTANCE OF MAN'S ROLE • 

t• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

OUR 5 / 19 / 66 

C ) 

'11 1. MAN HAS REASONING ABILITY (UNMATCHED BY MACHINE); ADAPTABILITY (CAN 

REPROGRAM), AND VERSATILITY (CAN CORRECT ERRORS). 

2. QUICKLY SENSES AND REACTS TO UNEXPECTED FAILURE MODES. 

3. IS CAPABLE OF REPLACING ANY OF A LARGE NUMBER OF COMPONENTS (USING 

HIMSELF AS A MULTI-PURPOSE SPARE). 

. . 

4. IS SELECTIVE DI INSTALLING SPARES. • 

• 

5.. CAN SENSE INCIPIENT FAILURES AND TAKE ALTERNATIVE STEPS PRIOR TO THE. 

FAILURE OCCURRING AND PERHAPS SPREADING OUT IN SYSTEM. • 

DETERMINES WHERE OR WHAT FAILURE ACTUALLY IS (NOT JUST SYSTEM, WHICH IS 

INSTRUMENTED, BUT AT PART LEVEL). 

p . 

• ,. 

' 7. CAN UTILIZE MAN ,GROUND COORDINATION TO DEFINE CORRECTIVE ACTION. 

S. PROVIDES AN UNDERSTANDING OF REASONS FOR FAILURE. '. 

. 

. 

. 9. HAS ABILITY TO BY-PASS MALFUNCTIONS OF FAULT DETECTION AND ISOLATION 

SYSTEM. ' , • 

. 

10. CAN CANNIBALIZE PARTS OR COMPONENTS FROM ONE SYSTEM (NOT NEEDED AT 

' • THAT MOMENT) FOR USE IN A CURRENT CRITICAL SYSTEM. 

11. CAN CONTINUE UNDER CONDITIONS OF DEGRADED PERFORMANCE, ATTAIN OPERATION 

WHERE AUTOMATIC SYSTEM WOULD JUST SHUT DOWN (OR. WOULD HAVE TO AWAIT 

ANALYSIS AND SPECIAL INSTRUCTIONS). . 

12. PROVIDES DETAIL INFORMATION FOR DESIGN IMPROVEMENT St FUTURE DEVELOPMENT. 

.11■••••■••• 0114.11.1111111Pe 

PptIAIL. ILIA.8 
• I 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

OP 44% F' E C i a .-01,EN F!ii) • S-19-66. 

WHS-311. 

Page 226 

P.ZISMITA74C I IE:T'0171v7r1.?;;ITN 

RSOIOLNE 

SPECIFIC EXAMPLES FOR A/RCRAKT AND SPACE FLIGHTS 

0 X• 15 EXPERIENCE 

o FLIGHT 22 • PILOT SUCCESSFULLY RESET CONTROLS AND STARTED UPPER 

ENGINE AFTER INITIAL START FAILURE - MISSION SAVED. 

o FLIGHT 25 •• PILOT MANUALLY RESET ALL CHANNELS AFTER STABILITY • 

AUGMENTATION S'.4'.3TEM TRIPPED OUT - MISSION SAVED. 

o FLIGHT 50 • PILOT DIAGNOSED FROZEN LNz VALVE PROBLEM, CHANGED 

COOLING MODES AND THAWED VALVE - MISSION COMPLETED. 

.0 GEMINI EXPERIENCE 

o GEMINI S • COOPER DISASSEMBLED, TROUBLE SHOT, AND REPAIRED 

RETICLE SIGHT FOR EXPERIMENTS. REPLACED FRAYED POWER 

CORD SHORTING OUT LIGHTING ELEMENTS WITH SPARE AND 

REASSEMBLED. 

• 

o GEMINI S • ASTRONAUT REPLACED FRAYED 0-RING SEAL FOR BLOOD PRESSURE 

CUFF IN PRESSURE SUIT WITH SPARE ITEM. 

o GEMINI 7 r ELECTRICAL CONNECTOR BETWEEN COMMAND PILOT SUIT AND 

SEAT UNLOCKED DURING MISSION, WAS RECONNECTED AND LOCKED 

BY ASTRONAUT. 

o GEMINI $ • CREW INSERTED ALUMINUM FOIL FROM FOOD PACKAGE BETWEEN 

WINDOW AND FILTER TO BLOCK HEAT AND LIGHT DURING SLEEP 

'PERIODS. . • 

0 B•70 EXPERIENCE 

o NOSE GEAR JAMMED DY DOORS IMPROPERLY SEQUENCED BY COMPUTER MALrUNCT/01% 

CREW WITH. GROUND ASSISTANCE DIAGNOSED PROBLEM, SHORTED-OU'r HOLDING 

CIRCUIT WITH METAL CLIP ALLOWING GEAR TO BE LOWERED - AIRCRAPT SAVED. • 

$P8114. HANDllmq 

_ 1 
• (BASELINE) 

INTEGRAL T-IIIC(U) 

ORBITING VEH. 

30 DAYS 

MANNED 

AUTOMATIC OPS CAPAB 

REDUNDANCY 

ALL CRTEren SUBSYS 

SPARE~ 

MAINLY 

FOR r.cas SUBSYS 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 .1 

SPECEIL NAHLEINI FWB 5.40-66 

WHS- 31 1 

SUBSYSTEM LIFE EXTENSION Page 227 

APPLICATION OF 60 DAY "BUILDING BLOCK" SUBSYSTEMS 

TO POSSIBLE GROWTH VEHICLE CONFIGURATICAS 

STRUCTURE 

Ph, EQUIP 

INSTRUM/MOW 

COMM/DATA MGT. 

ELECT PWR IC DISTR. 

ACTS ELECT & PROP. 

EC/LS . 

CREW PROV & EQUIP 

SPARES 

GEMINI B 

EXPENDABLES 

. . 

INTEGRAL LDC4 

ORBITING VER. 

60 DAYS 

STRUCTURE 

P/L EQUIP 

INSTRUM/MON•ALARN 

COMM/DATA MGT.. . 

ELECT PWR Sc DISTR. 

ACTS ELECT Sc PROP. 

ZC/LS 

CREW PROV Sc EQUIP 

SPARES 

GEMINI B 

EXPENDABLES 

STRUCTURE. •••••""'"'"! 

ECT PWR 

ACTS PROPULSION 

CRYOGENICS • 

CREW EQUIP CREW PROVISIONS 

SPARES •••••••"•""'""'":" • SPARES . • 

GEMINI B 

EXPENDABLES 

RENDEZVOUS 

RESUPPLY VEFI. 

50-60 DAYS 

-"IITOEKI 714.61. 

- MANNED 

REDUNDANCY • • 

ALL Cartien. SUBSYS 

SPARES 

ALL CRITICAL SUBSYS 

1%.IAINT Et REPAIR 

REPAIR AIDS 

MANNED (GEMINI B) 

AscErer 

REDUNDANCY 

"CRITCALTUBSYS 

SPARES 

TirAMPORT FOR 

ALL SUBSYS ROI/ 

AS REVD. ON 50 

DAY CYCLES. 

444:1%.1............1•••■■••••••■■■~1 011•9111•0~~0.-. *. • •■••••■ ■••■•■••••■•••••■■••■•■1111+ 

RENDEZVOUS 4 

ORBITING VEIL 

6.0 .. 300 DAYS 

NTiiiiiiCE) 

'i STRUCTURE 

P/L EQUIP. 

INSTRUM/ MON....A L.AR 

COMM/DATA MGT 

:' 

 r

ELECT DISTR. 

ACTS ELECTRONICS. 

• EC/LS 

MANNED 

rigtSrisle CREW ROT.) 

REDUNDANCY rR SUBSYS.e 

SPARES • 

WEL CRITICAL SUBSYS.. 

REPLENISH ON 50 DAY 

CYCLE 

MAINT & REPAIR 

YO1W-rirr.SarEnol.P. 

REPAIR AIDS 

EC110, NallikANG 
WHS- 311 714%4 \ 

Page 228 

NRO APP 

RELE 1 JULY 2015 

MEAN MISSION DURATION CONCEPT 

Design Life, L. 

MEAN MISSION DURATION,MMD R(t) tit ROVI1 

0 

FOR A SINGLE THREADED SYSTEM: 

MMD * A( 1- e 

WHERE 9 = MEAN-TIME- TO- FAILURE OF THE SYSTEM 

FOR A BASIC SYSTEM WITH STANDBY REDUNDANCY: 

MMD = 20 [1 - e 9 ( 1 +) I 29 

THE RENDEZVOUS ORBITING VEHICLE, WITH SOME SPARING AND MULTIPLE 

REDUNDANCY. OPERATES SIMILARLY TO THE SECOND EQUATION FOR A 

SYSTEM WITH STANDBY REDUNDANCY. 

IVO 
14ROAPPR1VED FFIR. _ 

RELEASE 1 JULY 2015 8/24/66 

J 

SPEC.E HAMBLIN -

50 

• 

MEAN MISSION DURATION 

• WI-1-311. 

Page 22-9 

. SIMPLIFIED RELIABILITY MODEL • STANDBY REDUNDANCY. 

'DESIGN 

LIFE, DAYS 

90 

80 - 

• 70 - 

60 

• ..•• 

40 

30 

20 • 

10 • 

0 • 3' 

RELIABILITY 'FOR.30 DAY DESIGN LIFE 
j 

8 f 24166 7: 

W145-31'1 \ 

MEAN MISSION DURATION• Page 230 

MOL - AM 

® COMPUTER MODEL 

DESIGN 

LIFE, DAYS 

, . • 

• 

RELIADILITY FOR 30 DAY DESIGN LIFE 

11, 

••••••••• -d"." 

PEfiriE.NA 

NRO APPROVED FOR 

RETEXSE"rluLy 

• 
3/10/ 67 

ALP 

a. 

NRO APPROVED FOR.. 

RELEASE 1 JULY 2015 

— 

WHS- 3 1 1 

ESTIMATED VEHICLE RELLAB/LiTIES AND SPARE ALLOTMENT Page 23 1 \ 

SUBSYSTEM 

BASELINE 30 DAY DESIGN 

RELIABILITY WT - SPARIM 

JLBS) 

60 DAY VEHICLE DESIGN 

RELIABILITY ' WT - SPARES 

(LDS) 

0 

. 991 

• 999 

• 9911 

• 999 

. 996 

• 9999 

• 

33.3 

..m.M.1• 

36. 5 

.• ■••• ■• 

fair 

EPS 

FUEL CELLS .99'1 

DISTRID. & CONTROL 

EC/LS 

L. S. /ATMOS CNTRL 

THERMAL CNTRL 

CRYOGENICS 

CRYOGENICS 

ACTS 

ELECTRONICS 

PROPULSION 

COMM 

DATA MANAGEMENT .985 

INSTR Sc MON/ALARM • 99Z 

STRUCTURE • 9991 

LAB. VEIL. SEG. .9c0 

EXPERIMENTS . 96b 

GEMINI-8 • 990 

• .. 99P) • 

• 968 . 60.0 • 

98$ 

a 995(2) 

a a., 

• 996 

.996 

72.0 

im a 

• 999/ • 90.0 

.944 

.991 44.0 

• 9996 8.0 

orsoomml* 

• .890, . : 300.0 

es • a -.-r 

.988 

gaga 

18.0 

. • ! 

20.4 

1.5 

anaa.allt 

• a 

Mao* 

TOTAL • 4903 • 884. 300.0 

(I) CONSIDERS 3 F. CELLS ON COLD STANDBY, ADDITIONAL SENSORS/SWITCHING FOR 

STARTUP AND PARTS OF DISTRIBUTION SYSTEM USED COMMONLY. 

(2) DOUBLE TANKAGE OF BASELINE, BUT LESS DUTY CYCLE PER TANK SINCE NEAR 

SAMARE.PEMAN.P. 

WM HANDLES 
4/6/67 

ALP 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 1 

• D vms_311 

PICARIE 

VEHICLE ESTIMATED PROBABILITIES OF SUCCESSFUL OPERATION 

Page Z32 SECRET S 

Ps(30 DAYS) ■ .95 (LAB) X • 96 (M/M) X • 99 

(GEM) 

INITIAL LAUNCH 

RN (I) 

BASELINE 

M/AM 

Pe(30 DAYS) ' . 68 (LAB) X . 87 (M/M)• • . 765 

at 993 

M/A.M(2) , Ps(30 DAYS) is .960 (LAB) X . 96 (M/M) . 922 

RIV Pa (60 DAYS) ■ (60 DAY DESIGN, SPARES IN 808 

WT. a 375 LI3S) 

RAY P. (60 DAYS) • . 988 (GEM) X . 979 (MODULE . 958 

LESS DATA) 'X .99 (DATA) 

ROV Pe(60 DAYS) . 888 (RIV) X . 958 (RAY) •. 851 

(1) UNATTENDED, WITHOUT GEMINI 

(2) 1PROPULSION, CRYOGENICS, FUEL CELLS AND GEMINI REMOVED FROM 

BASELINE M/AM 

MAL ELM 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

RENDEZVOUS ORBITING VEIIICLE AVAILABILITY FOR LONG DURATION 

wils-311 

1:14(31 233 

• 

SYSTEM UP 

SYSTEM DOWN 

r 

I t 

I 

• LJ i 1 

• 1.00 

• 90 

t SYSTEM DOWN DURING 11 

rod I DOCKING &.MOORING ..,J 11SYSTEM DOWN FOR REPAIR 

(TYPICAL EACH REV 1 I 1AFTER MAJOR FAILURE 

I CYCLE) 

PROBABILITY OF 

FAILURE INCREASE 

DUE TO CHECKOUT 

1 I 

I 

I 

I 

I 

I 

EFFECT OF REPLACEMENT 

BY RESUPPLY 

PROBABILITY 

OF SY.,TEM so 

BEING OUT OF 

COMMISSION 

IF NO CHECKOUT 

MADE 1 • . - 

• .24(Ps us .76 

20 )11 j 

/ . 

DOFM190iFFECT 

Ps. .09 

10 

EFFECT OF UNIMPROVABLES 

4011101.01.0.•■■■•••• 

0 60 120 180 

t'iRoir "Pi 

240 300 360 

MISSION TIME FROM INITIAL LAUNCH.P•PDAYI 
NRO APPROVED FOR 

L 

RELEASE 1 JULY 2015 

11 

19--(Dd i LL 

CONCEPT OF EXTENDETJ LIFE SYSTEMS 

(RESUPPLY SYSTEM) 

• COMPLETE REPLACEMENT EACH RESUPPLY CYCLE 

/ FUEL CELLS 

CRYOGENIC TANKAGE 

THRUST CHAMBER ASSY. 

/ PROPELLENT TANKS/FUEL SYSTEMS 

• INTENSE APPLICATION OF SPARES FOR MANNED MAINTENANCE/ 

REPAIRS/REPLACEMENT. 

UTILIZATION OF MAN IN TROUBLre SHOOTER ROLE 

• ELIMINATION OF MAJOR EQUIPMENT PROBLEMS DURING INITIAL 

MOL DEVELOPMENT PROGRAM. 

4 

t. 

311 

Page 234 

fa, 

I 11;1 4, ,SPEC[lAr NAKOLIIKG 
irtiff-J 

nc[A_. HANIPLING 

§UBSYSTEM LIFE EXTENSION SUMMARY 

• COMBINATIONS OF LIFE EXTENSION METHODS APPEAR MOST EFFECTIVE FOR MOL 

AND FURTHER STUDIES ARE REQUIRED TO DEFINE OPTIMUM APPROACHES 

• M/AM ORBITING VEHICLE DESIGN INCORPORATES MUCH REDUNDANCY 

• FOLLOW-ON ,LONGER- LIFE ORBITING VEHICLES SHOULD UTILIZE M/AM REDUNDANCY 

TO GREATEST ADVANTAGE 

• REDUNDANT EQUIPMENT BACKED-UP' WITH SPARES FOR 60 DAYS OR LONGER 

• PROVIDE FOR "PLUG-IN" REPLACEMENT CAPABILITY AT MODULE LEVEL 

• MODULES TO PROVIDE FOR COMPONENT REPLACEMENT WHERE ADVANTAGEOUS 

OPTIMIZED FOR WEIGHT/COMPLEXITY/REPAIR TIME/FAILURE MODES 

MAXIMIZE USE OF PART COMMONALITY (CIRCUIT CARDS, SWITCHES) 

• RETAIN AUTO AND REMOTE CONTROL SWITCHING FEATURES OF M/AM WHERE 

ADVANTAGEOUS 

/ CREW ROTATION DURING RENDEZVOUS/DOCKING ' 

• 60 DAY SUBSYSTEMS WITH SPARES PROVISIONING APPEAR TO BE "BUILDING BLOCKS" 

• INTEGRAL LAUNCH WITH LDC- 1 

• RENDEZVOUS/RESUPPLY VEHICLE WITH (U) 

• MAINTAINABLE SUBSYSTEMS FOR 60-300 DAY RENDEZVOUS ORBITING VEHICLE 

• SPECIAL CONSIDERATIONS FOR '60- 300 DAY RENDEZVOUS ORBITING VEHICLE INCLUDE 

• METEOROID CRITERIA 

i ADD APPROX 200 LB. (PRES. STRUCT. & RADIATOR) OR ACCEPT 0.990 PROS.

OF NO PUNCTURE 

PLAN FOR ACCOMPLISHMENT OF MORE EXTENSIVE MAINTENANCE BY CREW 

/ EVA FOR ACCESS AND REPLACEMENT FOR EXTERNALLY MOUNTED EQUIPMENT 

,/ LIQUID LOOP COMPONENT REPLACEMENT (VALVES/PUMPS/FILTERS). 

• IMPLEMENTATION 

• GROUND TEST PROGRAM FOR EQUIPMENT AND COMPONENTS 

I DEFINE LIFE AND DETERMINE WEAK POINTS 

MAKE NECESSARY IMPROVEMENTS FROM ANALYSIS AND TEST DATA 

ADDITIONAL QUALIFICATION PROGRAM FOR IN SPACE START FUEL CELLS & TANKS 

• FWD LOOKING DESIGN APPROACH FOR M/AM TO FACILITATE MAINT. & 

INSTALL. SPARES 

NRO APPROVED FOR 

JC rjuLy zuip 

WHS-311 

Page 235. 

MU HANDLING 

4-r 
D WHS-311 

Page 236 

.SPECIAIL NAKDom 

1 

NRO APPROVED FOR 

SUMMARY OF EXTENDED VEHICLE LIFE 

O MEAN MISSION DURATION FOR MAJORITY OF BASELINE SUBSYSTEM 

EQUIPMENT APPROACHES 60 DAYS. 

• 

O UNFIXABLE VEHICLE EQUIPMENTS ARE FEW, TEND TO BE PASSIVE 

ELEMENTS OR HAVE EXTREMELY LOW PROBABILITY OF FAILURE ,. 

O COMPLETELY REPLACE LIFE- LIMITED EQUIPMENT AND WiAR.OUT 

ITEMS AT RESUPPLY INTERVALS. 

O INTENSE APPLICATION OF SPARES FOR MANNED MAINTENANCE/REPAIRS/ 

. . 

REPLACEMENT WITH SPARES UPDATED AND REPLENISHED AT EACH 

RESUPPLY CYCLE. 

0 CREW TROUBLE SHOOTS PROBLEMS IN CONJUNCTION WITH GROUND TO 

PROVIDE A HIGHLY EFFECTIVE TEAM FOR DIAGNOSIS AND CORRECTIVE 

ACTION. 

O PROJECTED VEHICLES AVAILABILITIES SHOULD BE ATTAINABLE WITH 

MINIMUM CHANGES TO BASELINE SUBSYSTEMS. 

o S FULL DEVELOPMENT FLIGHTS IN BASELINE PROGRAM 
NRO APPROVED FOR 

RELEA 1 JULY 2015 

DITCR-raSPECIAL HANDLING WHS.-311 

Pa:ge 237 

UNFIXABLE VEHICLE EQUIPMENT EXAMPLES 

• ITEMS AFFECTING MISSION ABORT 

'i MALFUNCTION OF INACCESSIBLE COMPONENTS 

✓ PROPELLANT/CRYOGENIC FLUID LINE AND TANK LEAKAGE 

s/ WATER LINE, TANK AND HEAT EXCHANGER LEAKAGE 

/ DEBRIS TRAP MALFUNCTION 

✓ LEAKAGE OF STRUCTURAL SHELL 

INACCESSIBLE TERMINALS AND WIRING FAILURE 

• MULTIPLE FAILURES OF REDUNDANT EQUIPMENT 

• LOSS OF PRIMARY COMPONENT AND EXHAUSTION OF SPARED 

EQUIPMENT STOCK 

• ITEMS AFFECTING SYSTEM PERFORMANCE 

• FAILURE OF EQUIPMENT WHICH IS INHERENTLY INCOMPATIBLE WITH 

REDUNDANCY 

DRIVE MIRROR 

FLAT MIRROR 

ROSS CORRECTOR SYSTEM 

THERMAL DOORS° 

• LOSS OF EQUIPMENT WITH SUCH HIGH RELIABILITY THAT REDUNDANCY 

IS NOT ECONOMICAL 

SIMILAR COMMENTS AS ABOVE FOR INACCESSIBLE, REDUNDANT AND 

SPARED EQUIPMENT 

THE UNRELIABILITY OF SINGLE UNFIXABLE COMPONENTS IS EXTREMELY SMALL; BUT 

A FINITE UNRELIABILITY FOR SUMMED UNFIXABLE EQUIPMENT EXISTS. 

SPECIAL HANDLING