NRO APPROVED 

RELEASE 1 JULY. • 

AEROSPACE 

LIBRARY 

Document No. 6 /4 Pe4 

Copy 

U1GLASSFED 

SYSTEMS RESEARCH AND PLANNING DIVISION 

AEROSPACE RAT TION 

ASSgREED 
(0) 

NRO APPROV R 

RELEASE 1 JU 2015 • 

111=1111111111 

UNCLASSIFIED 

VAULT NUMBER 

- D18796 

TITLE MOL RENDEZVOUS ' 

LLAEROSPACE CORPORATION .

PRESENTATION 

AUTHOR L. M. WEEKS DATE OCT. 15, 1964 

AUDIENCE DR. B. P. LEONARD DR. W. C. WILLIAMS,_ 

S. M. TENNANT, C. L. OLSON 

LOCATION E. S. 0. 

DISTRIBUTION CONTROLLED BY /T.:. M. WEEKS 

DOWNGRADED AT 3 YEAR INTERVALS; 

DECLASSIFIED AFTER 12 YEARS. 

DOD DIR 5200.10 

This document contains information affecting the national defense of the United States within the 

meaning of the Espionage Laws, Title 18, U.S.C.. Sections 793 and 794, the transmission or revelation of which in any manner to an unauthorized person is prohibited by law. MJO : 5107-10 

CCC : 2130 

# UNCLASSIFIED 
NRO APPROV 

RELEASE 1 JU 

BRIEFING 

'VOL RENDEZVOUS 

OUTLINE 

SIAMESE TWIN ALTERNATIVE 

EXPERIMENT - RESUPPLY - 60 DAYS 

DOCKING CONSIDERATIONS 

IvIOL RELIABILITY ESTIMATES 

PRESENT INTEGRAL LAUNCH EXTENSIONS 

TITAN III GROWTH POTENTIAL 

THE INTEGRAL LAUNCH WITH TITAN III GROWTH 

SOME RENDEZVOUS PAYLOAD - DURATION CONFIGURATIONS 

A RENDEZVOUS RELIABILITY ESTIMATE 

MOL RENDEZVOUS MISSION MECHANICS 

IMPACT OF RENDEZVOUS ON TEST AND OPERATIONS 

AN EXPERIMENT ALLOCATION 

MOL RENDEZVOUS INCREMENTAL COST ESTIMATE 

A COST-EFFECTIVENESS COMPARISON OF RENDEZVOUS AND INTEGRAL LAUNCH 

IMPROVING LAUNCH VEHICLE CAPABILITY 

SOME SUMMARY RENDEZVOUS CONSIDERATIONS 

CONCLUSIONS ON MOL RENDEZVOUS 

SOME OTHER NATIONAL SPACE PROGRAMS 

RECOMMENDATIONS AND ACTION ITEMS 
•• 

y. 

NRO APPRO pR 

RELEASE 1.1 015 

MOL RENDEZVOUS 

RENDEZVOUS ALTERNATIVES 

A. SIAMESE TWIN 

B. EXPERIMENT - RESUPPLY . 60 DAYS 

• • ,,• N • • 
RELEASE 1 J 

NRO APPROVOIDR 

2015 • • 

MOL RENDEZVOUS 

ALTERNATE A 

SIAMESE TWINS 

OBJECTIVE: 

o TRADE ONE CREW MEMBER 

o KEEP ONE CREW MEMBER ON ORBIT 45 TO 60 DAYS 

o ONE SET EXP. FIRST 30 DAYS (3000#) 

o ANOTHER SET EXP. SECOND 30 DAYS (-2000#) 

CONFIGURATION: 

o BAREST MINIMUM CHANGE TO MOL 

o NO UMBILICAL OR COMPATIBLE DISPLAYS BETWEEN 

TARGET AND CHASER 

o QUALIFIED SUB-SYSTEMS TO ONLY 30 DAYS 
RELEASE 1J 

NRO APPROV 

015 • • 

RENDEZVOUS ALTERNATE A (SIAMESE) 

TARGET VEHICLE 

• STANDARD MOL CONFIGURATION PLUS 

/ DOCKING RING AND SHELL 

/ RADAR TRANSPONDER 

/ TUNNEL TO CHASER VEHICLE 

o APPROXIMATE 3000# EXPERIMENTS 
NRO APPROV 

RELEASE 1 JU 2111 

RENDEZVOUS ALTERNATE A (SIAMESE) 

CHASER VEHICLE 

• STANDARD MOL CONFIGURATION PLUS 

450 FPS EXTRA IN TRANSTAGE 

50 FPS DOCKING IN LABORATORY 

FORK AND SHELL DOCKING (MALE) 

GEMINI B RADAR 

GEMINI B COMPUTER OPERATIVE IN RENDEZVOUS MODE 

/ TUNNEL 

OPTICS AND/OR TV FOR TERMINAL RENDEZVOUS AND 

DOCKING 

• APPROXIMATELY 2000 POUNDS EXP. PAYLOAD 
NRO APPROV R 

RELEASE j4 2015 

RENDEZVOUS ALTERNATE A 

SIAMESE TWIN - EXTRA VEHICULAR 
NRO APPRO 

RELEASE 1 J 2015 

, MOL RENDEZVOUS 

ALTERNATIVE B 

'LARGE EXPERIMENT (NAVY ?) 

AND 

RESUPPLY - 60 DAYS 
NRO APPROV 

RELEASE 1 JU 

MOL RENDEZVOUS 

MISSION 

ALTERNATE B 

OBJECTIVE: 

o TO SHOW MILITARY MAN CAN OPERATE EQUIPMENT ON ORBIT -60 DAYS 

CONFIGURATION: (TAIL TO TAIL DOCKING) 

o TARGET VEHICLE 

/ 60 DAY QUALIFIED ECS, EXPERIMENTS 

/ FEMALE DOCKING, TUNNEL, DISPLAYS FOR DOCKED CONFIGURATION 

/ 3000# EXPERIMENTS (NAVY) 

o CHASER VEHICLE (RESUPPLY) 

45 TO 60 DAY QUALIFIED SUBSYSTEMS 

MALE DOCKING, TUNNEL, DISPLAYS, ETC. 

-400 FPS EXTRA FUEL IN TRANSTAGE 

-100 FPS DOCKING FUEL IN LABORATORY 

1000# ADDITIONAL EXPERIMENTS 

3 

f. 
NRO APPROVE•R 

RELEASE 1J 

RENDEZVOUS 

TARGET VEHICLE CONFIGURATION 

ALTERNATE B 

o STANDARD MOL CONFIGURATION PLUS 

DOCKING RING AND SHELL 

RADAR TRANSPONDER (AGENA TARGET) 

TUNNEL TO CHASE VEHICLE 

DISPLAYS TO MONITOR CHASER VEHICLE 

CONTROLS TO MONITOR CHASER VEHICLE 

60 DAY QUALIFIED ECS, EXPERIMENTS 

TWO WAY VOICE LINK TO CHASER 

TWO WAY DATA LINK TO CHASER 

o APPROXIMATELY 3000# EXPERIMENTAL PAYLOAD 

/ (SAY) NAVY EXPERIMENT 
NRO APPROV 

RELEASE 1 

RENDEZVOUS 

CHASER VEHICLE CONFIGURATION 

ALTERNATE B 

o STANDARD MOL CONFIGURATION PLUS 

/ 45 TO 60 DAY QUALIFIED ECS, POWER, ATTITUDE, EXPERIMENTS 

/ 400 FPS EXTRA FUEL IN TRANSTAGE 

/ 100 FPS EXTRA DOCKING FUEL IN LABORATORY 

/ -I000# EXPERIMENTS DIFFERENT FROM CHASER VEHICLE 

/ EXPENDABLES FOR 45 DAYS DOCKED 

/ FORK AND SHELL DOCKING (MALE) 

/ GEMINI B RADAR INSTALLED 

/ GEMINI B COMPUTER OPERATIVE IN RENDEZVOUS MODE 

/ TUNNEL AND DISPLAYS TO OPERATE DOCKED CHASER 

/ OPTICS AND/OR TV FOR TERMINAL RENDEZVOUS AND DOCKING 

t 
NRO APPRO 

RELEASE 1 

MOL RENDEZVOUS 

OPER AT ION 

ALTERNATE B 

TARGET 

o NIGHT-LAUNCH 

o OPERATES EXPERIMENTS FOR 15 DAYS 

o TRIMS TO ALTITUDE FOR RENDEZVOUS COMPATIBLE ORBIT (31 /2) 

o PREPARES FOR RENDEZVOUS 

o TERMINAL RENDEZVOUS AND DOCKING ASSIST TO CHASER 

CHASER 

o LAUNCH (DAYLIGHT 15, 17, 19, 21 DAYS LATER) 

o LAUNCH ON FIXED AZIMUTH (WINDOW -15 MINUTES) 

o STAYS IN PHASING ELLIPSE (80 TO 160 N. M. ) 

o KILLS OUT OF PLANE ERROR 

o KILLS PHASING 

o COMPUTES AND EXECUTES FINAL RENDEZVOUS MANEUVER 

o COMPLETES TERMINAL RENDEZVOUS AND DOCKING 

1 
NRO APPRO 

RELEASE 1 J 

MOL RENDEZVOUS 

OPERATION (cont. ) 

TARGET AND CHASER DOCKED 

o BOTH CREWS ASSESS SITUATION 

(POWER, ECS, ATTITUDE FUEL, EXPERIMENT STATUS) 

o CREWS PREPARE TO SEPARATE AND DE-ORBIT 

APPROPRIATE CREW AND GEMINI B 

o SEPARATE LABORATORIES (IF APPROPRIATE) 

o ONE CREW CONTINUES TO OPERATE EXPERIMENTS IN 

LABORATORIES #1 AND #2 

o MONITOR AND OPERATE 

DUAL ATTITUDE SYSTEM 

DUAL ECS SYSTEM 

DUAL POWER SYSTEM 

REMAINING GEMINI B 

• 

9 

I 
NRO APPROV111)R 

RELEASE 1 JUL 2015 __ • 

LOAD ANALYSIS - RENDEZVOUS 

F3ASELINE: TARGET VEHICLE: 

205 

18 

45 

100 

12 

22 

205 

236 

59 

362 

207. 5 

87..5 

295 

150 

120 120 

250 250 

110 ,I ,- 110 

360 

60 60 

60 60 

, 553 1, 159 

CHASE VF1IICLE 

COMMUNICATIONS 

VOICE 18 

INSTRUMENTATION 20 

DATA MGT. 

TLM XMITTERS 

COMMAND 

TRACKING 

38 

ATTITUDE CONTROL 

251/0 DUTY CYCLE 

EC/LS (SHIRT SLEEVE) 

ATM CONTROL 

THERMAL CONTROL 

87 5 

GEMINI 1 50 

LIGHTING 

EXPERIMENTS 

COMPUTER 

DISPLAY 

MISCELLANEOUS 60 

TOTALS 335. 5 
#2 #1 )13 

10000 

154 N. MI. loop HR 4--- 

ORBIT ALT. QUAL. CAPABILITY 

— #2-+ — 

i 

- 

#1 + RANSTMIE 

- 

T 

, . .._ 

L' .

8000 

600 

PAYLOAD - 

LBS 

4000 160-N. MI. 

INITIAL ORBIT ALT. 

• 

1 11 DAY.- 

151 N MI ORBIT ALT 

RENDEZVOUS 

2000 PERIQD. 

140 N MI. — 

NRO APPROV 

RELEASE 1 JUL 2015 • 

MOL RENDEZVOUS CONFIGURATION 

PAYLOAD VS. ON-ORBIT DURATION 

o SUBSYSTEMS QUALIFIED TO 1000 HR. 

o NO ORBIT MAINTENANCE 

10 20 30 40 50 60 

ON-ORBIT DURATION - DAYS 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

DOCKING KIT 

WEIGHT ESTIMATE 

ITEM 

TARGET VEH. 

(LES)/ 

CHASE VEH. 

(LBS) 

SHELL STRUCTURE 410 410 

TRANSTAGE SEPARATION PROVISIONS 35 35 

TUNNELS AND SEALS . 44 44 

N2 TANKAGE AND SUPPORTS 65 

02 AND N2 PLUMBING 10 10 

PROVISIONS FOR CRYOGENIC MANIFOLDING 150 150 

DOCKING MECHANISM SUPPORTS (ARMS) 90 MI SO 

DOCKING ARM ASSEMBLY (4) 80 

RING SEGMENTS (4) 30 

DOCKING CONTROL PACKAGE AND 

PLUMBING 6 

INSTALLATION PROVISIONS 10 4 

ELECTRICAL DISTRIBUTION 15 17 

(HARNESS ASSEM. ) 

MONITOR & CONTROL 30 30 

(HARNESS ASSEM. ) 

ELECTRICAL DISTRIBUTION (UMBILICAL) 15 

MONITOR & CONTROL (UMBILICAL) 15 

CONTROL & MONITORING INSTRUMENTATION 60 60 

REMOTE TV CAMERAS 40 

'RENDEZVOUS RADAR & CONTROLS 120 

HATCHES & MECHANISM 20 20 

TOTAL KIT WEIGHT 990 1,035 

4 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

MOL RENDEZVOUS AND DOCKING WEIGHT PENALTIES 

ITEM TARGET VEH. CHASE VEH. 

W (LB) w (LB) 

o HARDWARE P W T. 

REMOVE TEST SECTION -410 -410 

ADD DOCKING SECTION 910 795 

CONTROL & MONITORING INSTRUMENTATION 60 60 

HATCHES & MECHANISMS 20 20 

RENDEZVOUS RADAR & CONTROLS (GEM. B) 120 

REMOTE TV CAMERAS 40 

NET HARDWARE TOTAL 580 625 

o EXPENDABLESnW(NITROGEN LEAKAGE 85 

MAKE-UP) 

o PROPELLANT w 

PLANE & PHASE CHANGE 1120 

(TRANSTAGE - 450 FPS) 

FINAL DOCKING (LABORATORY - 50 FPS) 150 

TOTAL W 580 1980 

■•■■•■■•••■• 
RELEASE 1 *015 

NRO APPROR • 

DOCKING CONSIDERATIONS 
,-24,,4 l'ocuy Fc.e.e..,.,e.,,,A.4-, 

Afripoze- ticaorize /1 

ArrauDE . 

. 1 

/ 

Pe ORO C. 510&) 

CoipA.27-tycAJT . 

7.:.5 7 ‘, /IGO/4% C •, 

\ - - 

Are Locic 

cave,4,,z7,147,4.,,r 

- . 4 ..7.:4 Preg' 

\

CT,CeJ 

"a4fP9rtie-A.17 

ATT/TUOE —7 ./ (,c.41/:34.2r/yrAr ADAP762 ..5(e.:pav 

Liw/i i ■--. 

CayRenfe , ---- 

l 1, 

(26:414,0 

/7675T -

/ /10Due. 

/ 

/ C-)6 

....s7 

TARGET VEHICLE • -.. 

L CHASE VEHICLE 

NRO APPROV R 

RELEASE 1 JUL 2015 

IMPACT OF DOCKING ON BASELINE VEHICLE 

o ESTIMATED WEIGHT PENALTY 

FOR RING AND FORK CONCEPT (CONSIDERED A REPRESENTATIVE 

SYSTEM) 

TARGET VEHICLE 

. RING ASSEMBLY AND SHELL STRUCTURE 250 

• CREW TRANSFER AND HATCH 110 

• UMBILICAL CONNECTION PROVISIONS 10 

TOTAL 376 LBS 

CHASE VEHICLE 

. FORK ASSEMBLY AND SHELL STRUCTURE 320 

. CREW TRANSFER AND HATCH 110 

. UMBILICAL AND CONNECTION PROVISIONS 30 

TOTAL 74600 LBS 
NRO APPROVER 

RELEASE 1 

IMPACT OF DOCKING ON BASELINE VEHICLE 

o BASELINE DOCKING CONCEPT 

TAIL - TO - TAIL SELECTED OVER OTHER METHODS 

- REQUIRES MINIMUM MODIFICATIONS TO GEMINI 

PROVIDES FOR EASY CREW TRANSFER BETWEEN VEHICLES 

- HAS MINIMUM ON-ORBIT DRAG CONFIGURATION 

DOCKING MANEUVER IS CONSIDERED RELATIVELY SIMPLE 

PROVIDES UNENCUMBERED SEPARATION OF GEMINI FROM 

LABORATORY VEHICLE 

o DOCKING SYSTEM REQUIREMENTS 

DISSIPATE IMPACT ENERGY WITH LOW ACCELERATIONS 

IMMEDIATE ACQUISITION OF OTHER VEHICLE 

ACCURATE CENTERING AND ALIGNMENT 

POSITIVE LOCKING TOGETHER OF VEHICLES 

FAST AND RELIABLE RELEASE 

o CONCEPTS PROPOSED 

RING AND FORK MECHANISM (MAC) 

- PASSIVE RING ON TARGET VEHICLE 

- ACQUISITION FORK AND ENERGY DISSIPATION DEVICE ON CHASE VEHICLE 

RING AND MOVABLE ARM MECHANISM (MMC) 

- PASSIVE RING ON TARGET VEHICLE 

- ACQUISITION ARM AND ENERGY DISSIPATION DEVICE ON CHASE VEHICLE 
CHASE VEHICLE 

DOCKING RING AND FORK CONCEPT 

RING LOCKS 

ENERGY DISIPATION 

MECHANISM 

FORK - MOORED POSITION 

FORK - ACQUISITION POSITION 

FORK - PRE-DEPLOYMENT POSITION 

TARGET VEHICLE 

RING ASSEMBLY 7 

NRO APPROVER 

RELEASE Ldi7Lr2015 
DOCKING RING AND ARM CONCEPT 

ARM - STOWED AND 

MOORING POSITION 

CHASE VEHICLE 

TARGET VEHICLE 

RING ASSEMBLY 

ARM - ACQUISITION-/ 

POSITION 

ENERGY DISIPATION 

AND ARM LOCKING 

DEVICE 

RING ENGAGEMENT HOOK 

NRO APPROV 

RELEASE 1J 
NRO APPROV 

RELEASE LY 2015 

MOL WEIGHT SUMMARY 

RENDEZVOUS CONFIGURATION 

GEMINI B + RETRO 

LAB 

TARGET 

VEHICLE 

6,000 

7,910 

STRUCTURE 2,840 

RCS 560 

ELECTRICAL POWER (FUEL CELL) 2,100 

COMMUNICATIONS 200 

ECS 950 

INSTRUMENTATION 130 

PERSONNEL ACCOMMODATIONS 740 

DOCKING RING + PROVISIONS (TARGET) 390 

DOCKING FORK + PROVISIONS (CHASE) 

DISCRETIONARY PAYLOAD 5,490 

SPARE PARTS + MAINT. E.QUEPMENT 140 

ACS PROPELLANTS 260 

SERVICE ITEMS 1,760 

EXPERIMENT-WEIGHT AVAILABLE 3,330 

CONTINGENCY 2,000 

ON-ORBIT WEIGHT 21,400 

EXPENDABLES RATE (FOR 30 DAY MISSION) 70#/DAY 

CHASE 

VEHICLE 

6,000 

8,920 

2,840 

560 

2,100 

200 

950 

130 

740 

1,400 4 

4,480 

140 

260 

1,760 

2,320 

2,000 

21,400 
NRO APPRO 

RELEASE 

RENDEZVOUS 

TERMINAL DOCKING PHASE CONCEPT 

ON-ORBIT 1 - TARGET VEHICLE - STABILIZED 

PRE-RENDEZVOUS 2 - CHASE VEHICLE - MANEUVERING 

1 

1 

1:47'-" EJECT TRANSTAGE 

GEMINI RADAR 

VREL. 10 FPS 

—D Z-25 o-Nr-mr REL. 

Q T 2 HR. 

VREL. 4.10 FPS 

D

REL...C250 N. MI. 

AT HR 

VREL. Z_ 10 FPS 

REL.G100 N. MI. 

T 1 HR. 

 VREL. Z.. 10 FPS 

D

REL< 100 N. MI. 

4 T HR.7.0. • **\ 

1 VREL 4 2 FPS.a.1 

 REL 71 MI. 

AT . .30 MIN. 

:11111111K10••• 

2 

TRANSFER 1 CREWMAN 

2 

Au EJECT TRANSTAGE 

• 

TARGET VEHICLE AND CHASE VEHICLE - DOCKED 2 

.4 

• 
NRO APPRO 

RELEASE 1 JU 2015 

ti 

MOL 

THE RELIABILITY (EFFECTIVENESS) 

ESTIMATES 

.:; 
9

5 

9

5 

9

5 

3 9 = 

9

4 

9

3 

(. 99) 

— - 

9

4 

(. 99) 

9

2

5 

9

3 

9

3 

9

5 

94 

. 95 

94 3 9 

9

4 

9

4 

9

3 

NRO APPROV 

RELEASEiYJO 2015 • 

EFFECTIVENESS ALLOCATIONS 

CD 

o 

< 

Cl

fD 

• 

tx1 (") (") 

fb .)1 11 

CA 01 

g r :d 

$-4 —V

r 

ti 

1°0 A 

0 t b0 Et co .0 oci 0

▪ 

CD 0 0 

O a) 

7d n 

O < 

m cn " 

. 9969 - 

9

3 

(92

4 

9

4 * 

SAFETY (NO CASUALTY) . 9918 .99941.9858 

PRELAUNCH 9

3

88 95 

BOOST 9238 94 

ORBITAL 9

2

82 (93

5) 

DEORBIT 

RECOVERY 

MISSION COMP. (NO ABORT) I. 9561 19889 . 9829 

9

4 

9

2

5 

9

4 

9

2

5 

9

2

5 

.;999/7 

. 9890 

9

5 

9

4 

9

4 

. 9919 

.9959 

9

4 

9

3 

9

3 

9

3 

9

3 

. 8293 . 9850 

. 9980 

9

3 

9

3 

. 9963 

• 9968 

9

4 

9

3 

9

3 

9

3 

94

. 

. 99TZ 

• 9988 

9

5 

9

4 

9

4 

9

3 

. 9989 

. 9989 

. 9712 

. 9976 

. 9897 

.9971 

. 9920 

. 9929 

.7752 

9

5 

9

3 

. 99 

PRELAUNCH 9

3

7 

BOOST . 983 

ORBITAL . 973 

DEORBIT 

RECOVERY 

9

3 

(. 831) 

9

3 * 

- - - 

9

4 

9

3

5 

9

4 

9

4 

• 99 

9

2

5 

9

3

5 

9

3 

9

3 

9

3 

9

4 

. 9881 

9

5 . 8123 

9

5 . 9719 

9

5 9969 

9

3 . 9969 

9

4 

9

2

5 

9

3 

9

3 

9

3 

DES. ADEQUACY (NO DEGRAD) . 9171 

PRELAUNCH 9

3

3 

BOOST 9

2

69 

ORBITAL . 9206 

DEORBIT 

RECOVERY 

. 9499 . 9987 . 9790 . 9834 . 9880 . 9890 . 9928 .9939 . 9949 . 8752 

. 9883 

. 9799 

. 9151 

. 9987 

. 9889 

9

5 

9

3 

98 

95 

9

2

5 

9

3 

9

4 

. 99 

9

3 

MO 00 ON. AM 

9

3

5 

9

3 

. 99 

9

4 

9

2

5 

9

3 

. 99 

9

3 * 

■■•• 

es. 

9

4 

93 

9

2

5 

9

3 

94 

9

5 

9

5 

9

5 

9

2

5 

it SEGMENTS . 8626 

AVAILABILITY 9 

. 987 

9 

.9676 

93 

. 9679 

925 

. 9314 

9 

. 8.167 

9 5 

. 9722 

945 

. 9q59 

9 

. 92 1 9 

9 5 

. 9927 

945 

ti 

SEGMENT E . 8609 . 9378. 9667 9629 . 9704 . 8126 . 9673 . 9849 . 9869 . 9877 .6392 

* TRANSTAGE AFTER INJECTION ("Jr= - 9989, A = 93

) 
NRO APPROV 

RELEASE 1 JULL 2015 

E i.ECTIVENESS ALLOCATION 

OV LAB GEM. B EXP. CREW TII IC 

PRE -L . 

& 

LAUNCH MCC RANGE RECOVERY 

.86 .94 .97 .96 .97 .81 .97 .98 .99 .99 

SYSTEM EFFECTIVENESS .64 

PROGRAM EFFECTIVENESS > .85 

( 3 SUCCESSES IN 6 MANNED MISSIONS) 

FIGURE 10 

et 
NRO APPRO 

RELEASE 1J 

THE PRESENT INTEGRAL LAUNCH 

EXTENSIONS 

ALT, 

c:7‹ • CREW DURATION WITH EXPERIMENTS 

te 

• THE RADIOISOTOPE THERMO-ELECTRIC GENERATOR 

EXTENSION (RTG) 

• THE POWER DOWN APPROACH 

• THE SEVERE WEIGHT CONTROL APPROACH 
NRO APPRO i R 

RELEASE 1 J 2r3-1 

INTEGRAL A LT. Ci< 

CREW DURATION WITHOUT EXP. 

® PRESENT MOL CAN GO "-' 60 DAYS WITH 400 # EXP. 

BIOMEDICAL ONLY 

o PRESENT MOL CAN LOAD 60-DAY EXPENDABLES IN MOL 

PRESENT 30-DAY - SYSTEM RELIABILITY 64 

60-DAY - REQUIRES MUCH IMPROVEMENT 

(MAINTENANCE - ETR) 
• • • m 0 

> > W M M 

" C-. < C m 0 

m 

O 

0 O 

O 

0 

O 

O 

O 

0' OO

O 

co 

O 

O 

O 

(sAra)uol4Pancf41qao 

y ourrel yeAalui o 

t 

ri 

z O tri 

0 < 

o 

bi 

• L-9 "- 

O 0 

> H[ O;:1 z9 

0 

z 
NRO APPRO R 

RELEASE 1 m 

ALT. 49 

RTG EXTENSION 

• . 2500 # EXP. (NAVY?) 

• 60 DAYS 

• MOLECULAR SIEVE 

PROBLEMS 

RELIABILITY FOR 60 DAYS 

RTG DEVELOPMENT - 30 TO 50 M$ 

- 30 TO 40 MONTHS 
NRO APPRO 

RELEASE 1 

ALT. 

THE POWER- DOWN APPROACH 

LABORATORY ELECTRICAL LOAD ANALYSIS 

LOAD 

STANDBY AVE. 

WATTS 

MIN. PEAK EMERGENCY 

COMM. , INSTR. , DATA MGT. _: 17.1 205 171 367 171 

ATTITUDE CONTROL 232 232 232 260 0 

LIGHTING 60 120 60 120 60 

E. C. & L. S. 420 540 420 655 420 

DISPLAY 5 10 5 15 5 

MISCELLANEOUS 30 60 30 90 0 

GEMINI 200 200 100 600 400 

EXPERIMENTS 136 250 136 976 0 

TOTAL 1,254 1, 617 1, 154 3, 092 1, 056 
NRO APPRO 

RELEASE 1J 2015 

ALT.r 

THE POWER-DOWN APPROACH 

POWER 

DOWN 

MOL 

A VE. PWR. 

COMM. INSTR. & DATA MGMT. 205 100 

ATTITUDE CONTROL 232 100 

LIGHTING 120 80 

ECS AND LSS 540 320 

DISPLAY 10 10 

MISCELLANEOUS 60 60 

GEMINI B 200 200 

TRANSTAGE 200 

EXPERIMENTS 250 100 

1,817 WATTS 970 WATTS 

SAVING OF 670 # 
NRO APPRO R • 

RELEASE 1 2015 

A LT . cr 

BACKGROUND 

EXPENDABLES FOR BASIC MOL VEHICLE 

(30 DAY + 10% 160 N.M. ORBIT ALT. ) 

2 MAN CREW 

ITEM EXPENDABLE (LBS) TANKS, ETC. (LBS) 

PROPELLANTS 360 128 

REACTANTS 

0

2 1,103 . 347 

H2 138 307 

ATMOSPHERE 

PRIMARY 02 340 132 

SECONDARY (H. P.) Oz 21 68 

LITHIUM HYDROXIDE AND ACTIVATED CHARC. 215 25 

WATER 16 4 

WATER PURIFYING CHEM. 3 

FOOD 121 12 

CLEANING TISSUES 12 2 

DISPOSABLE CLOTHING 12 2 

TOTAL 2,341 1,027 

RATE OF EXPENDITURE 78 LBS/DAY 34 LBS/DAY 

"RUBBARIZED" EXPENDABLES 112 LBS/DAY 

MK 
NRO APPRO 

RELEASE 1J _91115 

ALT. e 

THE POWER-DOWN APPROACH 

ti 

• SAVE 670# ON ELECTRICAL POWER 

• DRIFT 1/2 TIME TO SAVE ATT. FUEL 

SAVE 300 # 

• WEIGHT SAVING 

1ST 2ND 

30 DAYS 30 DAYS 

POWER 670 670 + 330 

ATTITUDE 300 300 + 120 

TOTAL 

• EXPERIMENTAL PAYLOAD FOR 60 DAYS 

APPROXIMATELY 2800# 

41, 
NRO APPRO 

RELEASE 1J 

ALT. rf 

SEVERE WEIGHT CONTROL APPROACH 

• PRESENT WEIGHT MARGIN IS ^3000 # 

o PRESENT COST/LAUNCH $70, 000, 000 

• PRESENT EXP. PAYLOAD --...3500 # 

• VALUE OF # SAVED = 20,000 $/# 

• NON-RECURRING MAXIMUM PERMISSIBLE COST 

120, 000 $/# (6 LAUNCHES) 

o VALUE OF WATT SAVED = 10,000 $/WATT (30 DAY) 

20,000 $/WATT (60 DAY) 

• NON-RECURRING MAXIMUM PERMISSIBLE COST 

60,000 TO 120,000 $/WATT 

• ATTRACTIVE WEIGHT SAVINGS POSSIBILITIES 

400 # FUEL CELLS 

# MAGNESIUM STRUCTURES 
NRO APPRO' 

RELEASE 1 J 

MOL FUEL CELL POWER SYSTEM SUMMARY 

ALLIS 

CHALMERS 

1,000 Hour 

PRATT AND WHITNEY 

"Apollo" 1,000 Hour 

(400 Hr. ) 

GENERAL ELECTRIC 

"Gemini" 1, 000 Hour 

(400 Hr. ) 

WEIGHT (LBS! ) 4110 3472 3360 2982 2741 

VOLUME (FT. 3) 156. 8 131.6 112.4 102.8 93.8 

DEVELOPMENT 

FUNDING TO DATE 4 M -Z20 M :7,-4 5 M 

Production Facilities Production Facilities 

Producing "Apollo" F. C . Producing "Gemini" F. C . 

HARDWARE STATUS 

PRODUCTION CAPABILITY 

Qual. In Proposal 

Dec. 64 to NASA 

Qual. In Presently In 

Oct. 64 Life Test 

In Design 

(Funded) 

BASELINE: "GEMINI" FUEL CELL 
NRO APPRO\ 

RELEASE 1J 

ALT. cr 

1,000 HOUR FUEL CELL STATUS 

GENERAL ELECTRIC 

FUEL CELL TEST PROGRAM 

STACK 

AVE. LOAD 

AMPS/STACK 

COOLANT INLET 

TEMP. °F. TEST HOURS COMMENTS 

83 3K 75 820 9-25-64 STILL ON TEST 

84 5K 75 446 9-25-64 STILL ON TEST 

82A 5 75 648 9-25-64 STILL ON TEST 

R4 5/15 75 735 9-25-64 STILL ON TEST 

R3 5 62 891 9-25-64 STILL ON TEST 

224 5 75 900 9-25-64 STILL ON TEST 

241 5 75 785 9-24-64 FAILED 

257 5 75 692 9-25-64 STILL ON TEST 

SECTION 

11 3.1 75 715 0.2 VOLT AGE DROP 

STILL ON TEST 
NRO APPRO OR 

RELEASE 1 

ALT. 8-- 

SEVERE WEIGHT CONTROL APPROACH 

SUMMARY 

• 60 DAY POSSIBLE WITH EXP. PAYLOAD 

• NOW 400 it 

PLUS 3000 # MARGIN 

• PLUS 400 # FUEL CELLS 

• PLUS 400 # MAG. STRUCTURE 

4200 # 

IF HALF (2100#) COULD BE REALIZED A 

REASONABLE 60-DAY MISSION RESULTS 
NRO APPRO R 

RELEASE 1 J 2015 

INTEGRAL LAUNCH SUMMARY 

• CREW DURATION 

MINIMUM CHANGE TO MOL 

400 # EXP. 

• RTG - 2500 # EXP. 

• POWER DOWN - 2800 # EXP. 

• WEIGHT CONTROL - 2100 # EXP. 

• A NUMBER OF POSSIBLE APPROACHES SEEM TO EXIST TO 

OBTAIN 60 DAYS WITH EXPERIMENTS WITHOUT THE USE OF 

RENDEZVOUS 
401011 

NRO APPROVOR 

RELEASE 1 JULY 2015 • 

TITAN IBC GROWTH POTENTIAL 

- 

. 

• 

VEHICLE 

CONFIGURATION 

• 

MINIMUM PERFORMANCE 

PAYLOAD - LB 

EAST AMR SOUTH PMR 

100 N. M. ORBIT 100 N.M. ORBIT 

STANDARD TITAN MC 23, 800 19, 550 

TITAN LIIC/6 SEGMENT SOLID MOTORS 28, 830 23, 520 

TITAN llIC/7 SEGMENT SOLID MOTORS 

t' 

31, 450 25, 700 

. 

TITAN IIIC/ 156 IN. MOTORS 39,700 32, 700 

. . 

• 
NRO APPRO R 

RELEASE 1J 2015 

I 

INTEGRAL LAUNCH 

WITH 

GROWTH TITAN III 
30 90 120 

8000 

RTG POWER SYSTEM 

150 180 

MOL GROWTH 

o INTEGRAL LAUNCH 

o POLAR ORBIT (160 N. Mi.) 

G 7 SEGMENT SRM 

FUEL CPU', POWER SYSTEM 

ON-ORBIT DURATION (DAYS) 

10000 

MISS ION 

PAYLOAD 

4000 

NRO APPRO 

RELEASE 1 J 2(11 
FUEL CPT.T, POWER SYSTEM 

RTG POWER SYSTEM 

NRO APPRO aR 

RELEASE 1J 

M OL GROWTH 

e INTEGRAL LAUNCH 

o POLAR ORBIT (160 N. Mi.) 

e 156 in. SRM 

20000 

15000 

MISSION 11500 

PAYLOAD 

(LBS) 10000 

7500 

N.. 

5000 

.N■ 

0 

282 DAYS 

0 30 6o 8o 120 150 

ON-ORBIT DURATION (DAYS) 
NRO APPRO 

RELEASE 1 JU 2015 

INTEGRAL LAUNCH - T III GROWTH 

SUMMARY 

o 11,500# MISSION EQUIPMENT 

0 90 DAYS 

THIS CONFIGURATION SEEMS ATTRACTIVE 

BOTH AS AN INTEGRAL LAUNCH PROGRAM. 

AND AS A FIRST LAUNCH OF A RENDEZVOUS 

PROGRAM 
NRO APPRO R 

RELEASE 1 J 2015 

SOME RENDEZVOUS PAYLOAD - DURATION 

CONFIGURATIONS 

4 
1 

16000 

.12000 

USEFUL PAYLOAD 

(LBS) 

8000 

117i1.13/Day 

2 ;Men 

7

-162j Lb/Day 

4IMen 

4000 

3. 0 60 90 120 150 180 

ON-ORBIT DURATION (DAYS) 

RELEASE 1 J 

NRO APPROI1OR 

2015 • 

PAYLOAD vs ON-ORBIT DURATION 

o DUAL LAUNCH MISSION 

AMR 

PRESENT TIIIC 
USEFUL PAYLOAD 

(LBS) 

800 

30 60 90 120 150 180 

ON-ORBIT DURATION (DAYS) 

NRO APPROlikR 

RELEASE 1 JULY 2015 

PAYLOAD vs ON-ORBIT DURATION 

o RE-SUPPLY MISSION 

AMR 

PRESENT TIIIC 
1 25000 PRESENT TIIIC 

2000 

-4) 

150o0 

USEFUL 

PAYLOAD 

(LB) 10000 

5000 

50 Days 

.4 

• 4.:?) 

Resupply Cycle 

lie gay 

Resupply cle 

30 60 90 120 

I 

180 210 

NRO APPROVR 

RELEASE 1 JULY 2015 • 

PAYLOAD vs ON-ORBIT DURATION 

• AMR MISSION 

MOL UNMANNED MOL 

ON-ORBIT DURATION (DAYS) 
RELEASE 1 J 

NRO APPROlp,R 

2015 • 

MOL RENDEZVOUS CONFIGURATION PAYLOAD CAPABILITY 

60 

• o WTR (160 N. MI. ) 

T-111C L 156 IN. SltM 

50 

40 _ 

136 DAY RESUPPLY CYCLE 

PAYLOAD. 

30 _S...., (1, 000 LBS. ) 

20 .,. 

10 _ 

78 -DAY 

REUPPLY CY L 

0 

0 30 60 90 120 150 

ON-ORBIT DURATION (DAYS) 
NRO APPRO 

RELEASE 1J 

A RENDEZVOUS RELIABILITY ESTIMATE 

TARGET CHASER 

LAUNCH VEHICLE .81 .81 

LAB. (30 DAYS) .94 .94 

GEMINI B .97 .97 

CREW .97 .97 

PRE-LAUNCH AND LAUNCH .97 .97 

LAUNCH IN 15 MINUTE WINDOW -- .97 SAY 

RENDEZVOUS AND DOCK ...... .95 SAY 

. 69 .64 

COMBINED 

A4 

EXP. , MCC, RANGE, RECOVERY OMMITTED 
NRO APPRO\JR 

RELEASE 1 JULY 2015 S 

MOL RENDEZVOUS MISSION MECHANICS 

o PROCEDURES 

o LAUNCH WINDOWS 

o GROUND SUPPORT 

o CONCLUSIONS 

o RECOMMENDATIONS FOR FURTHER WORK 

4/ 

7' 
NRO APPRO R 

RELEASE 1 J 615 

RENDEZVOUS PROCEDURES 

ra:

ASSUMED PHASE DIFFERENCE AT 

CHASER INSERTION 

1(00 14.N1, 

(a) - 0 MIN. - CHASER 

INSERTED 

(b) 22 MIN. - CHASER 

MAKES PLANE 

CHANGE 

(c) - 45 MIN. - FIRST 

APOGEE; CHASER 

CHANGES ORBIT 

(d) - 65 MIN. - CHASER 

BEGINS CLOSURE 

CORRECTIONS 

NEXT APOGEE - 135 MIN. - CATCH-UP 
NRO APPRO 

RELEASE 1 

PLANE CHANGE AV REQUIREMENTS 

FOR: i = 28.34° AND FIXED LAUNCH AZIMUTH 

AT (FOR AV < 400 FPS) = 20 MIN, 

+100 
NRO APPRO IR 

RELEASE 1 2015 

PLANE CHANGE AV REQUIREMENTS 

FOR: i = 28.34° AND VARIABLE LAUNCH AZIMUTH 

0 100 200 

TIME - MINUTES 

AT(FOR AV < 400 FPS) = 120 MIN. 

USEABLE AT = 36 MIN. 

LAUNCH AZIMUTH 

RESTRICTIONS FOR CREW 

AND RANGE SAFETY 

77 90 • 103 

LAUNCH AZIMUTH - DEGREES 
PLANE CHANGE AV REQUIREMENTS 

FOR: i = 32° AND VARIABLE LAUNCH AZIMUTH 

0 

TIME - MINUTES 

0 105 

LAUNCH AZIMUTH - DEGREES 

7 

-200 -100 200 

1500 - 

AV -FPS 

1000 - 

500 - 

AT (FOR AV < 400 FPS) = 64 MIN. 

USEABLE AT = 32 MIN. 

LAUNCH AZIMUTH 

ESTRICTIONS FOR 

CREW AND RANGE 

SAFETY 

RELEASE 1 11) NRO APPRO RP 
NRO APPRO 

RELEASE 1J 

LAUNCH WINDOWS IN 30-DAY PERIOD 

FOR i = 28. 34°; AV (PLANE CHANGE) = 400 FPS 

LAUNCH FROM ETR 

MAXIMUM 

1 DAY 

TIME 

2 DAYS i 

TO CATCH-UP 

3 DAYS 5 DAYS 

AVERAGE NUMBER OF ''-'18 : 2 5 30 30 

LAUNCH-DAYS 

AVERAGE LENGTH OF '12 "17 '21 36 

LAUNCH WINDOW (MIN. ) 

RANGE OF LAUNCH 0-17 0-36 0-36 36 (CONSTANT) 

WINDOWS (MIN. ) 

% NIGHT LAUNCHES 

- A. M. TARGET LAUNCH : 7 0 % : 7 0% 1:70% 2170% 

- P. M. TARGET LAUNCH =30% =30% Z30% :30% 
NRO APPRO 

RELEASE 1J 

RENDEZVOUS WINDOWS 

ALLOWABLE PLANE CHANGE AV = 400 fps 

30 DAY PERIOD 

TYPICAL NUMBER OF LAUNCH DAYS 

VARIABLE 

LAUNCH AZIMUTH 

i = 28.34° * 

FIXED 

LAUNCH AZIMUTH 

i = 32° ** 

FOR 1 DAY CATCH-UP 18 DAYS 10 DAYS 

FOR 2 DAY CATCH-UP 25 DAYS 17 DAYS 

FOR 3 DAY CATCH-UP 30 DAYS 22 DAYS 

FOR. 5 DAY CATCH-UP 30 DAYS 30 DAYS 

TYPICAL LENGTH OF LAUNCH WINDOWS 

FOR 1 DAY CATCH-UP 12 MIN. 8 MIN. 

FOR 2 DAY CATCH-UP 17 MIN. 9 MIN. 

FOR 3 DAY CATCH-UP 21 MIN. 11 MIN. 

FOR 5 DAY CATCH-UP 36 MIN. 13.5 MIN. 

MAXIMUM WINDOW LENGTH 

FOR 1 DAY CATCH-UP 17 MIN. 13.5 MIN. 

FOR 2 DAY CATCH-UP 36 MIN. 13.5 MIN. 

FOR 3 DAY CATCH-UP 36 MIN. 13.5 MIN. 

FOR 5 DAY CATCH-UP 36 MIN. 13.5 MIN. 

* BEST TARGET PLANE INCLINATION FOR MAXIMUM WINDOWS. 

** FOR 106° LAUNCH AZIMUTH - ASSUMING RANGE AND PILOT SAFETY RESTRICTIONS ON 

\\,...., LAUNCH AZIMUTH. 

• 0.1 , 
TARGET LAUNCHED AT 3 P. M. 

/ ---- / APPROX. 

/ '-'--. 2 HOURS 

• 7-'---..,4, ... VARIATION 

WITH 

DARKNESS SEASON 

r 

1 

/ 

•• f. 

/ / .."....• .,. 

/ 

' '' 

 t -....., 

"•-••. 1/ 

/ // 

••••• • 

/ , ./ 

1 / / 

/ / ../ / 

4 A. M.- / 

MIDNIGHT1 

8 P. MI 

// 

• / 

/ 

4 P. M. - 

NRO APPROVOR 

RELEASE 1 J 

I. 

• 

TIME OF CHASER LAUNCH 

4 P. 

NOON 

8 A. M. /- TARGET LAUNCHED AT'- 6._A. M. 

5 10 15 20 25 30 

LAUNCH DAY OF CHASER 
NRO APPROlikR 

RELEASE 1 J 

GROUND SUPPORT 

o PROVIDE TIME AND AZIMUTH OF LAUNCH 

o PROVIDE CHASER REQUIRED INSERTION CONDITIONS 

o DETERMINE IF DIRECT ASCENT IS POSSIBLE 

o PROVIDE DATA FOR PLANE CHANGES 

TIME OF THRUSTING 

ATTITUDE FOR THRUSTING 

AV REQUIRED 

o PROVIDE DATA FOR ALTITUDE ADJUSTMENTS 

o DETERMINE CATCH-UP POINT AND PROVIDE PHASE ADJUSTMENT 

DATA TO CHASER 

o PERFORM CLOSURE CALCULATIONS SIMILAR TO AIRBORNE COMPUTER 

AND PROVIDE CHECKPOINTS TO PILOTS 

C.6 
NRO APPRO 

RELEASE 1 • 2015 

GROUND EQUIPMENT 

o WORLD-WIDE TRACKING NETWORK 

o LARGE HIGH-SPEED, GENERAL PURPOSE COMPUTER 

o COMMUNICATION LINKS TO PILOTS AT DIVERSE POINTS 

o ROLL PROGRAM A. G. E. 

o POSSIBLE ADDITIONAL LAUNCH PAD 

/ IF CHASER LAUNCHED WITHIN 8 DAYS OF TARGET 
RELEASE 1 

NRO APPRO 

• 2015 

iR • 

3. CONCLUSIONS 

o RENDEZVOUS FEASIBLE WITH REASONABLE TOTAL AV (600 - 800 FPS) 

/ TOTAL AV = AV1 (FOR PLANE CHANGE) + AV2(CLOSURE MANEUVERS) 

o VARIABLE LAUNCH AZIMUTH DEEMED NECESSARY 

o TIME TO CATCH-UP CAN BE LONG (UP TO 5 DAYS) 

o ON-TIME LAUNCHES IMPORTANT (WITHIN A FEW MINUTES) 

o EITHER TARGET OR CHASER WILL BE LAUNCHED AT NIGHT IN 

MAJORITY OF CASES 

o GROUND SUPPORT REQUIREMENTS MAJOR 

o NEED CAPABILITY OF MODIFYING ROLL PROGRAM FEW MINUTES 

BEFORE LAUNCH 
RELEASE 1 Ilk 

NRO APPROR 

RECOMMENDATIONS FOR FURTHER STUDY 

o REVIEW CLOSURE TECHNIQUE AND DETERMINE AV REQUIREMENTS 

FOR THIS PHASE 

o STUDY ON-TIME LAUNCH CAPABILITY OF TITAN IIIC 

o REVIEW AND ESTABLISH ACCURATELY THE LAUNCH AZIMUTH RANGE 

AND PILOT SAFETY RESTRICTIONS 

o ASSESS IMPACT OF LONG CATCH-UP TIMES 

o ASSESS IMPACT OF NIGHT LAUNCHES 

o DETERMINE REQUIRED TRACKING STATIONS LOCATIONS 

o INVESTIGATE COSTS AND DIFFICULTIES OF IMPLEMENTING VARIABLE 

liOLL PROGRAM ON TITAN IIIC 

o DETERMINE ACCURATELY LAUNCH WINDOWS FOR VARIOUS LAUNCH DAYS 

S 

C L. 
NRO APPROR 

RELEASE 1 J0015 

IMPACT OF RENDEZVOUS ON TEST AND OPERATIONS 

o DEVELOPMENT AND QUALIFICATION TESTS OF RENDEZVOUS EQUIPMENT 

o EXTENDED LIFE TESTS OF ON-ORBIT EQUIPMENT 

o RENDEZVOUS AND DOCKING SIMULATOR AND TRAINER 

o DUAL MISSION SIMULATORS - ACCELERATED TRAINING 

o DUAL VIB CAPABILITY, AGE AND CREWS 

o PROBABLY DUAL PAD CAPABILITY 

o ' DUAL MCC DISPLAYS, EQUIPMENT AND CREWS 

o COMPUTING CAPABILITY FOR RENDEZVOUS 

o ADDITIONAL ON-ORBIT TELEMETRY SUPPORT EQUIPMENT AND CREWS 

o ADDITIONAL RECOVERY FORCES 

o POSSIBLE USE OF MASA IMCC 

o POSSIBLE SATURATION OF NASA ENVIRONMENTAL FACILITIES 

• • 
NRO APPRO:1R 

RELEASE 1 J 2015 

AN EXPERIMENT ALLOCATION 

EXPERIMENTS 

2 3 

FLIGHT NOS. 

NOS. 4 5 6 8 R 

P - 1, 2, 3 402 402 402 402 402 402 

P - 4 660 660 

.13- 5 250 200 150 120 150 120 

P - 6 670 670 670 

P - 7 605 605 

P - 8 340 340 

P - 10 385 385 385 

P - 11 35 35 35 35 35 35 

P - 12 400 400 500 400 300 400 

P - 13 . 698 

GPE 505 505 505 505 505 505 

ACTUAL 2867 2532 2402 3205 2402 3205 

AVAILABLE 3500 3200 2400 3200 2400 3500 

AVAILABLE SECONDARY 633 660 0 0 0 295 

TOTAL SECONDARY ALLOCATION = 1596 
NRO APPRO R 

RELEASE 1J 2015 

SOME SUMMARY RENDEZVOUS CONSIDERATIONS 

• END OBJECTIVE OF MOL SHOULD BE 90 DAY RECONN. MISSIONS OUT OF PMR 

o SERIOUS PAYLOAD LOSS 

#2 MANEUVERING - 3600# TO 2100# (VERY NARROW WINDOW) 

#1 TARGET - 3600# TO 3100# 

• MANEUVERING VEHICLE (#2) PROBABLY UNDESIREABLE FOR SIGNIFICANT EXPERIMENTS 

o TWO LAUNCH PADS 

o TWO CELLS OF ITL 

o TWO DISPLAY ROOMS ETC. @ MMC (OR MCC) 

• MOL MUST BE DESIGNED TO WORK BOTH INTEGRALLY AND DOCKED 

o TESTING 92 FOOT DOCKED MOL'S IS A PROBLEM 

o 6 FLIGHTS FOR 30 DAY QUALIFIED ASTRONAUTS IS ADEQUATE 

o 60 DAYS IS PROBABLY AMBITIOUS FOR 6 LAUNCH PROGRAM - PARTICULARLY TO 

GET ALL "13" EXPERIMENTS ACCOMPLISHED 

o 60 DAY CAPABILITY IS PROBABLY BEST ACCOMPLISHED BY EXTENSIONS OF 

PRESENT MOL CAPABILITY. 

o 156" SOLIDS CAN GET 11, 500# OF SENSORS FOR 90 DAY MISSIONS 
NRO APPRO 

RELEASE 1 102C115 

UNCLASSIFIED 

MOL RENDEZVOUS INCREMENTAL COST ESTIMATE 

$ x106 

DESIGN & DEVELOPMENT 

LABORATORY: DOCKING MODULE 41 

ENVIRONMENTAL CONTROL 3 

ELECTRICAL POWER 10 

STABILIZATION CONTROL 2 

TEST SECTION REMOVAL 24 

TOTAL LABORATORY 80 

GEMINI B: RENDEZVOUS RADAR & CONTROLS 2 

TOTAL DESIGN & DEVELOPMENT 82 

HARDWARE PROCUREMENT & OPERATIONS 

LABORATORY 2 

GEMINI B 3 

LAUNCH SUPPORT 1 

TOTAL HARDWARE PROC. & OPS. 6 

UNCLASSIFIED 
TOTAL PROGRAM 

1.11NCLAsoFgED 

NRO APPRO /( 11. ) R 

RELEASE 1 J1 P94 

• 

././Naleib 

UNCLASSIFIED 

PROGRAM SUPPORT 

FLIGHT HARDWARE SPARES 1 

AGE: DUPLICATE SET T III -C 70 

DUPLICATE SET GEMINI 14 

DUPLICATE SET LABORATORY 24 

PECULIAR TO RENDEZVOUS 6 

AUTOMATION 60 

TOTAL AGE 174 

AGE SPARES 23 

TRAINERS 2 

EXTENDED RECOVERY 1 

MISSION CONTROL: IM C C 10 

NETWORK SUPPORT 20 

DOCUMENTATION 10 

TOTAL SUPPORT 241 
UNCLAz,b61FIED I 1. 

NRO APPROOR 

RELEASE 1J • 

tIMetAsnirso 

MOL RENDEZVOUS INCREMENTAL COST ESTIMATE 

EXPLANATION OF METHODOLOGY 

I. DESIGN & DEVELOPMENT 

A. LABORATORY TOTAL CHANGE TO LABORATORY ASSUMED TO BE OF 

SUFFICIENT MAGNITUDE TO BE CONSIDERED AS ENTIRE 

SPACECRAFT DEVELOPMENT TYPE EFFORT. ESTIMATE 

WAS DETERMINED ON DOLLARS PER POUND BASIS USING 

DATA ON APOLLO, GEMINI, MECURY, AND DYNA-SOAR 

PROGRAMS. BREAKDOWN INTO SUBSYSTEMS RATIOED 

ACCORDING TO WEIGHT BREAKDOWN. 

B. GEMINI B DERIVED FROM 12/18/63 ESTIMATE WHERE PROVISION WAS 

INCLUDED FOR REMOVAL OF INDICATED ITEMS. 

II. HARDWARE PROCUREMENT & OPERATIONS 

A. LABORATORY ESTIMATE WAS DETERMINED ON DOLLARS PER POUND 

BASIS USING DATA ON APOLLO AND DYNA-SOAR PROGRAMS. 

• B. GEMINI B DERIVED FROM 12118/63 ESTIMATE, ADDING BACK 

PREVIOUSLY DELETED ITEMS. 

C. LAUNCH SUPPORT - PREVIOUS ESTIMATE RATIOED UP ACCORDING TO 

INCREASE IN HARDWARE COST. 

tfe 

t 
• OW 

NRO APPRO (111/1 R 

RELEASE 1 JU-2CLI C 

MOL RENDEZVOUS IN MAW ESTIMATE 

III. PROGRAM SUPPORT 

A. FLIGHT HARDWARE SPARES - 20% FACTOR BASED ON GENERAL MISSILE 

AND SPACE SYSTEM EXPERIENCE. 

B. AGE DUPLICATE T III-C, GEMINI AND LABORATORY 

EQUIPMENT + EXTRA FOR RENDEZVOUS 

+ ADDITIONAL FOR AUTOMATION + FACILITIES. 

C. AGE SPARES - 20% FACTOR AS STATED FOR FLIGHT HARDWARE. 

D. TRAINERS BASED ON RATIO OF GEMINI MISSION SIMULATOR COST 

TO PRODUCTION VEHICLE COST. 

E. EXTENDED RECOVERY - PREVIOUS ESTIMATE RATIOED UP ACCORDING 

TO INCREASE IN NUMBER OF DAYS. 

F. MISSION CONTROL - 1/2 OF HOUSTON MCC PLUS 1 ADDITIONAL 

TRACKING STATION. 

G. DOCUMENTAION - 3% OF ALL OTHER ELEMENTS OF TOTAL PROGRAM 

INCREMENTAL COST BASED ON APOLLO EXPERIENCE. 

i. 

UNLLAQSIFIED 

• • 
NRO APPRO., 

RELEASE 1 JULY-21115 

A COST -EFFECTIVENESS COMPARISON 

OF 

RENDEZVOUS AND INTEGRAL LAUNCH 

INTEGRAL 

LAUNCH RENDEZVOUS 

MISSION LAUNCH COSTS 

(70 M$ EACH) 

RELIABILITY 

COST/PROBABLE SUCCESS 

30 DAY EXP. 60-DAY SIAMESE 

. 64 .44 

110 M$/SUCCESS 320 M$/SUCCESS 
NRO APPRO 

RELEASE 1 J 2015 • 

IMPROVING LAUNCH VEHICLE CAPABILITY 

• HOW MUCH WOULD IT BE WORTH TO IMPROVE TITAN III 

EXP. PAYLOAD (AMR) 

T-IIIC 3, 500 # 70 M$/LAUNCH 

6 SEG. 8, 500 # 71 M$/LAUNCH (ESTIMATE) 

7 SEG. 11, 000 # 72 MS/LAUNCH (ESTIMATE) 

156" 19, 000 # 75 MS/LAUNCH (ESTIMATE) 

THEREFORE, 

T-ILIC $20,000/# 

6 SEG. $ 8,300/# 

7 SEG. $ 6,600/# 

156" $ 4,000/# 

PRESENT PRIMARY EXPERIMENTS --,./ 20, 000# INCLUDING DUPLICATION 

oo T-IIIC o REQUIRES 6 LAUNCHES @ 70 = 420 M$ 

6 SEG. REQUIRES 3 LAUNCHES: @ 71 = 213 M$ 

7 SEG. REQUIRES 2 LAUNCHES @ 72 = 144 M$ 

156" REQUIRES 2 LAUNCHES @ 75 = 150 M$ 
NRO APPRO R 

RELEASE 1 J 2015 

IMPROVING LAUNCH VEHICLE CAPABILITY 

THEREFORE, FOR THE MOL PRIMARY EXPERIMENTS ONE COULD 

IN THEORY AFFORD TO PAY: 

200 M$ TO DEVELOP 6 SEGMENT TITAN III 

275 M$ TO DEVELOP 7 SEGMENT TITAN III 

270 TO 325 M$ TO DEVELOP 156 INCH TITAN III 
RELEASE 1 

NRO APPR

2015 

R • 

CONCLUSIONS ON MOL RENDEZVOUS 

• THE RELIABILITY OF THE PRESENT "COMPLETE" MOL MISSION IS PROBABLY NOT 

MUCH GREATER THAN D. 65. (THIS GIVES -•- .85 FOR 3 OR MORE SUCCESSES IN THE 

6 LAUNCH PROGRAM 

THE RELIABILITY OF A RENDEZVOUS MISSION IS PROBABLY-..0. 45. (THIS GIVES 

"-. 85 FOR ONE OR MORE SUCCESSES IN A 3 x 2. = 6 LAUNCH PROGRAM) 

• REASONABLE MODIFICATIONS APPEAR TO BE POSSIBLE TO EXTEND THE PRESENT 

MOL INTEGRAL LAUNCH TO 60 DAYS 

o THE IMPACT ON EXPERIMENT ALLOCATION AND RELIABLE EXPERIMENT 

ACCOMPLISHMENT IS VERY SERIOUS 

o THE PAYLOAD LOSS IS 500 TO 2500 POUNDS 

THE IMPACT ON THE GROUND FROM ALMOST ALL ASPECTS OF OPERATION IS 

SERIOUS 

• INTERJECTING 2 NEW CONFIGURATIONS INTO A 6-LAUNCH PROGRAM IS EXTREMELY 

AMBITIOUS 

o THE FINAL OPERATIONAL MISSION CONFIGURATION IS NOT YET FIRM ENOUGH TO 

DO EXTENSIVE MISSION PLANNING 

o NO DOLLAR ESTIMATE HAS YET BEEN MADE OF THE IMPACT OF RENDEZVOUS ON 

THE PROGRAM 

• IT IS ESSENTIALLY IMPOSSIBLE TO GET ENOUGH RENDEZVOUS LAUNCHES IN SUCH 

A FEW LAUNCHES TO BE TRULY MEANINGFUL 

MOL WOULD CONTRIBUTE QUITE SUCCESSFULLY IF 3- 4, -5 or 6 CREWS WERE FULLY 

QUALIFIED FOR 30-DAY MISSIONS 
NRO APPRO\JR 

RELEASE 1 )1 

• 

SOME OTHER NATIONAL SPACE PROGRAMS 

FAILURES SUCCESSES 

DYNASOAR X-15 

SAINT MERCURY 

RANGER TELSTAR 

MIDAS TRANSIT 

VANGUARD TIROS 

SYNCOM 

VOSTOK 

SURVEYOR ? 

GEMINI 

APOLLO ? 

LESSON: AVOID OVER-AMBITIOUS PROJECTS? ? ? 
NRO APPR 

RELEASE 1 

• 

RECOMMENDATIONS AND ACTION ITEMS 

o ELIMINATE REND. FROM PRESENT 6 FLIGHT PROGRAM 

/ SPEC. 

/ PROGRAM TEST PLAN 

/ ETC. 

o INSIST THAT INDUSTRY SHOW THEIR DESIGN APPROACH FOR FOLLOW-ON 

REND. FLIGHTS. 

/ SPEC. ADDENDUM? 

o INSIST THAT INDUSTRY SHOW THEIR DESIGN TO REACH 60 DAYS BY EITHER 

INTEGRAL OR REND. LAUNCH. 

o STUDY VIGOROUSLY THE RECONN. MISSION FOR APPLICABILITY OF 

"PRESENT" HARDWARE. LAY REQUIREMENTS ON MOL WHEN "FIRM". 

o STUDY FLY-BY MISSION FOR APPLICABILITY OF "PRESENT" MOL HARDWARE. 

o CONTINUE TO STUDY ALL FOLLOW-ON MOL MISSIONS. 

/ NASA REQUIREMENTS 

/ RECONN. REQUIREMENTS 

/ FLY-BY REQUIREMENTS 

/ OTHER REQUIREMENTS 
NRO APPROVED FO 

RELEASE 1 JULY 2015 • 

411•11110 

UNCLASSIFIED 

UNCLASSIFIED 

11111MNINha