Page of 4ipOges 

Copy of- ...ff copies 

SUM Control 46Y6-410%2" 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1124k- Y4a BYEMAN kl 74A7 

Control System 

111111111111111111twomm 

5 APR 1956 

MIZIORANDUM FOR COLONEL WALLING 

SUBJECT: Program Review, MOL Systems Office, OLApril 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. William' 

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

The first item on the agenda was a Weights Review conducted by 

Mr. Weeks, Mr. Mass and Mr. Strong of Aerospace. The design objective 

for MOL was stated to be: 

32,600 pounds, 80/155 Nautical Nile 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 ibs. + 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 13.555 lbs. +1.940 lbst= 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 Laboratory 

Module.) 

The history of the weight problem in the mission module is as 

follows: 

6,160 lbs 

6,675 lbs 

- 8,910 lbs 

- 9,360 lbs 

.. 9,178 lbs 

- 8,413 lbs 

September 1965 

December 1965 

January 1966 

February 1966 

April 2 1966 

Aercispace Target 

Handle via BYENAN l id e t, Ni 

Control System 

• 1 
NRO APPROVED FOR 

RELT4JULY 2015 

nail 9 via BYEMN[Do R '4 A / 

bantral System 

DATA RETRIEVAL - Mr. Stan Strong of Aerospace introduced 

this subject and Bob Brenda gave the presentation. The same 

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

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

positions taken on this effort. 

The points that were made on Readout were as follows: 

1. Security - 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 

HOL vehicle. 

b. Standard 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 20 mb (SGLS) transuittor. 

The three reasons given for requiring security were: 

1. Protect the sensitivity of man's role in reconnaissance 

from space. 

2. Protect the knowledge of the ERO capability. 

3. Protect the knowledge of the users interest in specific 

tests. 

SYSTEM RESPONSIBILITY - Another major issue associated with 

the data readout problemwas the need for early assignment for system 

responsibility to a specific contractor. 

FILM RETURN - For data retrieval in the maimed MOL, Dr. Flax 

has asked that provisions be made for a single 33 inch re-entryvehicle 

to dump some film after a week's operation. Provisions must also be 

made to include a- possible second re-entry vehicle. The GEMINI is 

being:designed to bring back three separate cane containing rolls of 

film weighing 60 pounds each. Also to be included is a small container 

for 30-50 pounds of secondary data, such as IR, color, film peeks and 

processed film, previously readout over the data readout link. 

2 

Handle via HYMN /6o ei Ar 

Control System 

Page .2 of pages 

Copy -5-of copieS 

MEM Co atrol C- 6 

•Pr 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Handle via BYEMAN le ti 

Control System 

CAMERAS - The present Eastman Kodak work statement calls 

for two camera. 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 HOL 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 will be lost is the inferior data 

at the edges of the 9-inch diameter lens. 

UNMANN/1) SYSTEM - The design has been selected for this 

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

for an operational life of 40 days. 

PROGRAM PLANNING - Dr. Leonard and Dr. Williams discussed in 

great detail the need for design and development of a "fat" TITANan improved, Large Diameter Core (LDC). The strength of their 

arguments were predicated on the eventual need for long duration 

MOL 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 minion per day (SO N.M. perigee) and $4.5 

millionpr 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. W1111.a 

to be $50.0 million from go-ahead. Re stated that Phase TB 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. Be 

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

understand more completely the proposal being made by Aerospace. 

EigalleaSpalgUit - Colonel Knolle gave a short 

presentation on this subject. Be stated there was now firm agreement 

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

mission module shell to GE. GE, with the aid of an EKC simulator, 

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

shell. GE would then remove the EX simulator and ship the mission 

Handle via BYIMAN)Qi/9-A/ 

Control System 

page of ..-`t pagto 

Copy. of 4:Aopies 

SIAM Doiatrol 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Hanel via BYEMAN 7De, 12//cr- I 

Control System 

module to EKC. There, Eastman would install and teat the ERO 

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

GE. Douglas would then mate the Lab Vehicle and Mission Nodule, 

perform system tests and ship to the WTR pad for launch. 

SIGNED 

S. NORMAN, JR. 

Colonel, USAF 

Mission Planning Division 

Copies to: SAF-SLM - Cy 2 

SAF-SL - Cy 3 

SCG-Read - Cy 4 

Lt Col Floyd/5 Apr 66/SAFSLM/55674/ams 

Handle via BANAW-Ab?),9A/ 

Control System 

Page -.3. of _ pages 

Copy of copies 

SIAFS :Control -Ct