J. 

D FOR 

ELEAJULY 2015 

NTEROFFICE CORRESPONDENCE 

cc:- Noted Below 

242412.30-67 

DATE 27 October 1964 

AEROSPACE OSPACE CORPORATION 

LIBRARY 

Document No .1) le 6-3 0q 

Copy No. / 

• w UNCLASSIFIED 

SUBJECT MOL Weight History (JO 5107-30) FROM S. E. Rice 

Bldg. A2/2043 

Ext. 85591 

References: See Table III 

Recent events, such as internal briefings, review .of the MOL system 

.specification, and various discussions have prompted the preparation of 

this memorandum. The specific objectives are to illustrate the term.ilexperiments weight" and to clearly indicate a potential "experiments weight" 

problem. 

Table I is a weight summary representing our interpretation of the 

MOL specification and included in Table III. The weight now available 

for experiments as shown in Table I is 3,613 pounds. Of this, 1,028 as 

shown in Table I is for propellants, fuel cell reactants, data handlingequipment, and structure.. This total has been charged to the experiments 

as its proportionate share of the total of these quantities. 

Recent studies show that complex space vehicles have increased 22 

percent in weight from the contract phase to final hardware development. 

The current MOL weight estimates includes for contingencies 5 percent 

(300 pounds) for the re-entry vehicle and 15 percent 12,000 pounds) for 

the laboratory excluding experiments. These low contingency weights will 

require very extensive and detailed weight control procedures to prevent 

further reductiot in weight. available for experiments. 

Figure 1 illustrates the variation in weight available for experiments on the - MOL program since'2-jannary 1964, The payloads shown in 

FROPT...-d`f (3 

LiC Qr .- .'.1+:1000Ar--'" 

PORATIObVRAc:D z; 

."-:CLASSIFIED AFTER 12 YEARS. 

RETURN TO LIBRA DOD D1R 5200.10 UNCLASSIFIED LA 

This doculwent contains information affecting the national defense of the United States within the meaning of the Espionage Laws. Title 

113, U. S. C., Section 793 and 794, the transmission or revelation of which in any manner to an unauthorized person is prohibited by law. 
viivirwoiricm 

• ' 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 41111.1111W 64-2412.30-67 

Page 2 

this Figure have been adjusted, to Coincide with the booster capability 

predicted by the current MOL specification for a circular orbit at 160 

nautical miles and an inclination of 32 degrees (22,200 pounds). The 

experiments weights have also been adjusted to a common reaction control system propellant loading of 35 pounds. 

Table I is a weight summary representing the current vehicle configuration. The weights associated with the experiment provisions is 

supplied with this Table. 

Table II summarizes the weights shown in, Figure 1 and notes the 

major reasons for the changes. 

Table III references the documents which form the basis for this 

memorandum and summarizes the. more important design constraints assoelated with.our estimates'. 

APPROVED: 62.4Z9-4-‘64-,--/ 

C. R. Pullen, Manager 

Weight Prediction Section 

APPROVED: 

Steinman, Head 

icle Systems Department 

SER:mn 

cc: J. E. Bennett J. E. Roberts 

H. Bernstein E. R. Ryder 

J. M. Brown T. Silva 

J. W. Duroux C. Stewart 

K. G. Graff W. P. Targoff 

J. R. Henry D. E. Wilkins 

C. J. Holden D. Willens 

J. G. Krisilas W. C. Williams.-'- 

E. L. La Porte M. G. Wolfe 

B. P. Leonard 

C. A. Lindley 

A. Mager 

N. W. Nordyke 

C. L. Olson UNCLASCAFEED C. R. Precious 

• 

This document contains information affecting of t e United States within the meaning of the Espionage Laws, Title 

le it 701 70a the. frontmisaion r revelation of which in any manner to an unauthorized carton is prohibited by law. 
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ED 
imudimED, 

64-2412.30-67 

. Page 4 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

TABLE I 

ORBITING VEHICLE WEIGHT SUMMARY 

' Based on Retro Rocket Abort ConfigUration, and 

Basic Structural Provisions only for Rendezvous and 

GEMINI B SEGMENT 

Docking 

Weight-Pounds 

6,325 

4,545 

1,480 

300 

12,985 

Re7entry Vehicle (Includes Crew) 

Adapter Section - 15°, 6 Rockets 

Contingency 

LABORATORY VEHICLE SEGMENT 

Structure (Docking provisions in basic structure) 2,960 (1) 

Orientation Control System (Less Propellant) .690 

Electrical Power (Less Reactants) 2,230 

Instrumentation 130 

Communications 735 (2) 

Environmental Control System (Less Expendables) 890 

Personnel Accommodations 630 

Displays and Controls 315 

Spare Parts 140 

Expendables (2,265) 

Food 120 

Oxygen - Supercritical 285 

Oxygen - High Pressure 10 

Nitrogen - Supercritical 100 

Water - Reserve 15 

Lithium Hydroxide 215 

Disposable Clothing, Tissues, Chemicals 35 

Reactants for Electrical Power - 1800 Watts Average 1,350 (3) 

Propellants 135 (4) 

Contingency 2,000 

EXPERIMENT SEGMENT - WEIGHT AVAILABLE 2,585 (5) 

TRANSTAGE MODIFICATIONS 

30 Day MOL - A Weight 

Redundant Auto Pilot System 

GROSS WEIGHT AT LAUNCH 

Notes 

305 

6o (6) 

245 

22,200 (7) 

(1) Includes Provisions for Experiments (240 lbs.) 

(2) Includes Data Handling System for Experiments (500 lbs.) 1,028 lbs. 

(3) Includes Reactants for Experiments (250 yatts) (188 lbs.) 

(4) Includes Propellant Allowance for Expetrent Maneuvers (100 lbs.) 

(5) Weight Available for Experiments is in addition to Items (1)to(4), 

(6) A Weight is the difference between the predicted weight of the transtage 

for the 30-day MOL and the weight used in the performance analysis. 

(7) Specification performance for an inclination of 32°, and a circular 

160 nautical mile orbit*, UNCLASSIFIED 

This document contains information offec one e ense of the nited States wi n meaning of the Espionage Lows, Title 

18, U.S.C., Section 793 and 794, the transmission or revelation of which in any manner to on unauthorized person is prohibited by law. 
. • 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

64-2412.30-67 

Page 5 

TABLE II 

MOL PAYLOAD WEIGHT HISTORY 

ence 

Date 

1964 

Primary Reason for 

Weight Change 

A Weight 

Change 

Normalized 

Payload 

(1) 

(2) 

2 January 

30 March 

Change from two 500 cu. ft. compartments to 

a 750 cu. ft. compartment. 

Minimum change MOL concept. Gemini fuel 

cells in lieu of fully oriented solar array. 

-34o 

+1,488 

5,845 

6,185 

(3) 30 April 4,697 

Replace fuel cells with roll controlled 

solar array. 

-82o 

(4) 19 May 5,517 

Increase pressurized volume.ftom 750 cu.ft. 

to 1300 cu. ft. 

+592 

(5) 20 May 4,925 

Reduce pressurized volume to-1200 - Cu. ft. 

Replace solar..array with fuel cells. -32 

Reduce length of mission from 40 to 35 days 

(6) 17 June 4,957 

Reduce length of mission from 35 to 33 days 

Increase power level from 1,500 watts to 

1,600 watts. - +357 

Increase reactant rate from 1.0 to 1.16 

pounds/KW hour and increase number of fuel 

cells from 4 to 12. 

(7) 11 August 4,60o 

Structural revisions +125 

(8) 17 September 4,475 

Reduce reactant rate from 1.16 pounds/KW 

hour to 0.95 pounds/KW hour. 

Increase average power requirement from 

1.6 KW to 1.8 KW. 

- 4'398 

Provide for 2 gas system at 7 psi in place 

of 1 gas system at 5 psi. 

Increase reaction control system weights. 

Increase reactant tank weights. 

(9) 13 October 4,077 

Use retro rocket abort configuration in 

place of tower abort system. 

+464 

(10) 27 October '3, 613 

Payload weights have been "normalized" to a booster capability of 22,200 pounds 

and to the same RCS prope UNCLA6'SIFIED 

This document contains information affecting the national defense of the United State w ithin the meaning of the Espionage Laws, Title 

18, U.S.C., Section 793 and 794, the transmission or revelation of which in ony manner to an unauthorized person is prohibited by law. 
NRO APPROVED FOR 

RELEASE I JULY 2015 70 , 

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