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MEMORANDUM FOR RECORD 

SUBJECT: Program Review, MOL Systems Office, April 2, 1966 

The meeting was officially called to order when General Schriever 

arrived at 1000. The Executive Session had been held from 0830-1000 

with the Generals and key Aerospace personnel in attendance. Some of 

the key personnel present were: Generals Schriever, Evans, Berg, Funk, 

Martin, and Cooper, Dr. Getting, Dr. Donovan, Dr. Leonard, Dr. Williams, 

and others including Frank Ross of Dr. Flax's office. The following 

are simmAries of the agenda items in the order they were presented at 

the Program Review. 

A. Weights Review. This item was presented by Mr. Weeks, 

W. Moss and W. Strong of Aerospace. The design objective for MOL was 

stated to be 32,600 pounds, 80/155 nautical mile ephemeris, 80° inclination. The 32,600 pounds is made up of a weight budget of 28,561 pounds 

plus 4,010 contingency to make a grand total of 32,571 (32,600) pounds. 

The design weight goals have been apportioned as follows: 

Contingency 

Weight 

Crew Equipment 413 lbs. + 80 lbs. = 493 lbs. 

Gemini plus Crew 6,160 lbs. + 290 lbs. = 6,450 lbs. 

Mission Module 8,433 lbs. +1,700 lbs. = 10,133 lbs. 

Laboratory Module 1,555 lbs. +1,940 lbs. = 15,495 lbs. 

TOTAL 28,561 lbs. +4,010 lbs. = 32,571 lbs. 

At the present time the program people associated with 

the laboratory module are driving hard to reduce their weight by 1,000 

lbs. They were weighing 15,456; they presently weigh 14,502 and their 

objective is 13,555 pounds. (The weight of the mission module structure 

is included in the weight budget charged to the La.boratory Module.) 

The history of the weight problem in the mission module 

is as follows: 

Scptember 1965 • 6,160 lbs. 

December 1965 • 6,675 lbs. 

January 1966 • 8,910 lbs. 

February 1966 • 9,360 lbs. 

April 2, 1966 • 9,178 lbs. 

Aerospace Target - 8,433 lbs. 

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B. Program Planning. Dr. Leonard and Dr. Williams discussed in great detail the need for design and development of a "fat" 

TITAN-an improved, Large Diameter Core (LDC). The strength of their 

arguments were predicated on the eventual need for long duration MDL 

systems, capable of becoming cost effective through rendezvous 

techniques. The whole basis of their argument rested on the need 

to bring cost of manned reconnaissance operation down from an 

estimated high of $3.1 million per day (80 N.M. perigee) and $4.5 

million per day (70 N.M. perigee) to a figure close to the estimated 

cost of $2.0 million per day (70 N.M. perigee), unmanned. 

The cost of this LDC development was estimated by Dr. 

Williams to be $50.0 million from go-ahead.. He stated that Phase lB 

should be initiated as soon as possible to achieve for a test launch 

of the first LDC in 1970. 

General Schriever stated that the requirement for 

extended duration of man in orbit for the period of time to make 

initiation of this development attractive required some detailed study. 

He stated he would meet with Aerospace on April 5 to attempt to 

understand more completely the proposal being made by Aerospace, and 

deferred any action on this item until that time. 

C. Data Retrieval. Mr. Stan Strong of Aerospace introduced this subject and Bob Brandel gave the presentation. The same 

presentation had been given to Dr. Flax on the 28th of March. W. 

Strong stated he believed. Dr. Flax generally supported the positions 

taken on this effort. 

(1) Readout. A secure link was believed essential 

for any data readout. The two ways to achieve this security were: 

a. A 3' diameter directional antenna on the ))L 

vehicle. 

b. SLandard 20mb (SGLS) transmitter plus 

encrypting. 

The latter method was favored due to the desire 

to delete any requirement for an extra antenna on the MOL vehicle. 

This system includes the CBS scanner, modified, the 

which is presently under contract, and the 20mb (SGLS) 

transmitter, The three reasons given for requiring security were: 

a. Protect the sensitivity of man's role in 

reconnaissance from space. 

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b. Protect the knowledge of the HRO capability. 

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c. Protect the knowledge of the users interest 

in specific tests. 

(2) Film Return. For data retrieval in the manned 

MOL, Dr. Flax has asked that provisions be made for a single 33 inch 

re-entry vehicle to dump some film after a week's operation. Provisions mast also be made to include a possible second re-entry 

vehicle. The GEMINI is being designed to bring back three separate 

cans containing rolls of film weighing 60 pounds each. Also to be 

included is a small container for 30e50 pounds of secondary data, such 

as /R, color, film packs and processed film, previously readout over 

the data readout link. 

(3) Cameras. The present Eastman Kodak work statement 

calls for two cameras, Because of space limitations in the laboratory, 

it is intended to design the system with only one camera with a platen 

capable of accepting alternate films and filters. The objective would 

be to permit the astronaut to change film in the same way that film 

packs are changed on the backs of Speed Graphics. The MOL Program 

Office is also considering the use of 5-inch instead of 9-inch film for 

the data readout photography. This is possible in the manned system 

due to the fact that man will be able to center the target and all that 

win. be lost is the inferior data at the edges of the 9-inch diameter 

lens. 

(4) Unmanned System. The design has been selected for 

;his system. It will include six re-entry vehicles and will be 

designed for an operational life of 40 days. 

D. Roles and Responsibilities,Colonel Ktolle gave a 

short presentation on this subject. He stated there was now firm 

agreement on the factory-to-pad issue. Douglas would fabricate and 

ship the mission mod le shell to GE. GE, with the aid of an EEC 

semelator, would install its 3,000 pounds of equipment and put the 

doors on the shell. GE would then remove the EK simulator and ship the 

mission module to E. There, Eastman would install and test the 1010 

and ship to Douglas, 20 weeks after receipt of the shell from GE. 

Douglas would then mate the Lab Vehicle and Mission Module, perform 

system tests and ship to the UM pad for launch. 

E. Eastman Kodak Presentation. Mr. John Sewell. of EEC 

covered the following areas: 

(1) Roles and Responsibilities. These were as 

originftny planned with the exception, that the mission payload assembly 

and optical test would be accomplished at EMC and shipped directly to 

Douglas. A flow plan showing a 20-week assembly and functional checkout was presented. 

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SYSTEM ORLY 

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(2) Facilities. It was shown that the total of new 

facility construction required had been reduced from 160,150 square 

feet to 141,200 square feet since submittal of their facility proposal 

in December. 

(3) Review of frsonnell Cost Estimates, Schedules and 

Program Status: 

a. Personnel. Difficulty was being encountered 

in obtaining fast clearance of personnel and they requested assistance 

of the Program Office. 

b. Cost, EX estimates that there will be an 

8 per cent cost reduction in their January 1966 estimate* 

• c. Schedule* EK stated that there had been a 

two-month slip in the delivery of the .1(1 optical system from July 15, 

1969 to September 15, 1969 because of Air Force delay in authorization 

of facilities and long lead time items and an ES:underestimate for time 

to debug the optical test chambers. A representative list of the pacing 

schedule items and the delay attributable to each was shown. EK 

showed a composite milestone schedule showing the delivery dates of 

FM-1 through FW7. 

F. General Electric Presentation. Mr. George Miller of 

GE made the presentations of Impact of Hardware, Roles and Responsibilities, Impact of Factory to Pad Flow Dcisions, Status and Plans 

and Overall Appraisal. No significant problem areas were raised and 

it was indicated that GE could handle their responsibility satisfactorily. 

G. Insertion Ship. The insertion ship status was presented 

by Colonel Creighton (NRD). The presentation included the following 

recommended positions: 

FIRST CHOICE 

o Modify two T-2's $1.0,4 

o Both programs accept schedule constraints 

SECOND CHOICE 

o MdiAly two T-2's as above 

Plan. T-2 support for first four tests 

o Minimdm mods to existing ship for later tests 

$3.024 

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THIRD CHOICE 

o Xbdify one T-2 $0.5M 

o Modify AGM-6 $11.5K 

After some discussion General Schriever decided that 

the second choice was his selection and that NB1) should work Out the 

necessary arrangements with AASA. 

ROBE 3. WAILING 

Colonel, IMF 

Chief, Program Control Division 

Col wqiiing/SAFSL/13Apr66/rad 

Cys to: 

SCG Read (Cy 1) 

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