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ECRET-- 

AUG 1 1969 

.'Zi..- .11111111111.0110 1,011.1. 11111. 

MEMORANDUM FOR DR. SEAMANS 

This is in reply to your memorandum dated June 30, 1969, pertaining to the establishment of an Ad Hoc Group to review MCI, hardware, 

technology and experience to insure that pilor4mum national benefit 

is derived therefrom. 

The Ad Hoc Group was established under the chairmanship of 

Dr. M. I. Yerymovych, end their report is transmitted herewith. The 

report is divided into two volumes. Volume I contains the summery 

and the conclusions, the maL system development status at time of 

termination, the residuals and technology selected for special 

consideration and related planning considerations. Volume II contains 

the Appendixes which include supporting documentation and material 

reviewed by the Group. 

I have reviewed the Ad Hoc Group's report and concur with their 

findings and recommendations, and I commend it to you for your approval 

of the recommended actions. 

2 Attachments 

1. Review of MOL Residuals, 

Vol I, (C) 

2. Review of MOL Residuals, 

Vol II, (s) 

Stned: - 

GRP1,1. L. HANSEN 

Aszistant Secretor/ ' 

Research and rievelopmeg 

r;WORICING PAPER 

'SECRET— UNCLASSIFIED WHEN 

INCLOSURES ARE REMOVED 
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REVIEW OF MOL RESIDUALS 

AUGUST 1, 1969 
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REVIEW OF MOD RESIDUALS 

Prepared by an Ad Hoc Group 

for the Secretary of the U.S. Air Force 

Volume I 

Approved 

Washington, D.C. 

August 1, 1969 

WORKING PAPER 
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REVIEW OF MOL RESIDUALS 

CONTENTS 

VOLUME I 

Section Page No. 

I. Summary and Conclusions 3 

II. Introduction 9 

MOL System Development Status at Time of Termination 12 

A. Major System Segments 12 

B. Completion Status 13 

IV. Residuals and Technology Selected for Special Consideration 16 

A. MOL Hardware 18 

B. MOL Facilities 41 

C. Related Technology 47 

V. Planning Considerations 55 

A. Aerospace Biotechnology 55 

B. Military Space Planning 61 

VOLUME II 

Appendixes 

A. Enabling Document 

B. Committee Members 

C. Committee Actions 

D. Facilities List 

E. MOL Systems Office Briefings 

F. USAF Technology Review 

G. Contractors' Briefings 

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I. SUMMARY AND CONCLUSIONS 

As directed by the Secretary of the Air Force, an Ad Hoc Group on 

MOL Residuals was organized to insure that maximum national benefit is 

realized from the MOL Program hardware, technology, and experience. In 

fulfilling its charter, the Group made a comprehensive review of the 

significant hardware, facilities, and technology available. The review 

included detailed presentations by the MOL Systems Office, the Space and 

Missiles Systems Organization, and the Aerospace Medical Division and 

stimulated a number of investigations of various areas by potential users. 

Additionally, McDonnell Douglas Astronautics Corporation and General 

Electric Company presented to the Ad Hoc Group suggestions on possible uses of 

their developed hardware, technology, and experience. 

Review and deliberations by the Group verified that the originally 

approved conceptual approach--that flight demonstrated hardware and proven 

technology be used to the maximum extent possible to achieve a highly reliable 

and operational system at the outset--was closely followed. The approach 

included the use of a modified Gemini reentry vehicle and space suit and 

proven space vehicle structural design and fabrication techniques. Modified 

or adapted Apollo subsystems and components and a modified Titan III booster 

for improved performance and man-rated safety were also used. Particularly 

close coordination and standardization between NASA and the Air Force was 

evident in the crew-related and fire-resistant materials areas. 

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In spite of the extensive utilization or adaptation of available hardware and technology, the MOL Program was a massive engineering undertaking 

to develop an efficient system useful for low-altitude, long-duration 

operations. A sizable portion of the engineering test hardware had been 

completed, and fabrication of flight articles had commenced. 

All the significant MOL hardware, test and checkout equipment, facilities 

and technology were identified and the potential use to DoD and/or NASA 

was assessed. The disposition actions and plans of the MOIL Program/Systems 

Office are generally concurred in by the Group. Furthermore, the plans 

insure that all possible beneficiaries of Government and industry are 

afforded an opportunity to review the residual inventories and assess their 

needs in accordance with the established priority although the beneficiary 

may not have been represented by membership on the Group. 

Specifically, the following actions were underway and the Group concurs 

with their implementations: 

1. The crew-related equipment which includes feeding systems, 

MOL suit development, and environmental control components have direct 

application to NASA manned programs. The feeding system contract is being 

transferred to NASA, andthe waste management components and technologies are 

made available to NASA through the mutual contractor. The oxygen sensor 

components and the MOL development and training pressure suits will be 

transferred to NASA. 

2. The Gemini Aerospace Ground Equipment was originally obtained 

from NASA and it will be returned to NASA as specified in the original agreement. 

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-CONFMENTIAL-- 

3. Space Launch Complex No. 6 will be "mothballed!' and maintained 

in a "down-mode" for possible use on future programs. The MOL Support 

Facilities at Vandenberg will be reallocated to other users. 

4. Air Force Satellite Control Facility's Advanced Data System 

and MOL-associated tasks were cancelled and a study to determine the use 

of the Advanced Satellite Test Center has been initiated. 

5. The requirement for the Recovery Staging Base at Easter 

Island was cancelled. 

6. The essential MOL development work that must be continued in 

other Air Force projects was associated with Titan IIIM. This involves 

design improvements and qualification tests that were slated for integration 

in other Titan III programs to improve payload capability and to preclude 

re-procuring of earlier obsolete configurations. The essential development 

effort has been transferred to the Titan III R&D program. Studies are 

presently underway to consider the most effective application of residual 

Titan IIIM test equipment. 

A number of items were identified by the Group as requiring special 

consideration by the DoD and/or NASA. It is recommended that the following 

specific actions be taken: 

1. The Air Force Systems Command (AFSC) and the Air Staff should 

evaluate the SAMSO study on use of the Titan III automatic checkout equipment 

(CAGE) and make recommendations to the Assistant Secretary of the Air Force 

for R&D (SAFRD) by September 1, 1969. 

-CONFIDENTIAL 

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2. NASA should submit their recommendation on their use of 

simulators and checkout systems to SAFRD by September 1, 1969. Any conflict 

between the Air Force and NASA needs will be resolved by SAFRD. 

3. All general purpose computers should be listed for inventory 

and disposition in accordance with Armed Services Procurement Regulations 

as planned; however, disposition of those computers associated with the 

simulators and checkout systems mentioned above should be held in abeyance 

until completion of the above studies. 

4. The MOL fuel cell hardware should be transferred to the 

AF Aero Propulsion Laboratory. 

5. The AF Rocket Propulsion Laboratory should have first priority 

on the Attitude Control Engines. The remaining engines and associated 

tankage and valving should be transferred to NASA, Langley Research Center. 

6. AFSC and the Air Staff should investigate Air Force space 

and aeronautical systems need for the MOL 4 Pi Extended Performance flight• 

computers and advise the appropriate Termination Contracting Officer. If 

not needed by the Air Force, the hardware may then be transferred to NASA. 

7. The hardware for the Expandable Airlock Experiment for the 

Apollo Applications Program (D021) should beheld in storage pending 

resolution of NASA's plans for the dry workshop. Inasmuch as the flight 

hardware is completed and NASA has expended most of the integration effort, 

it may be appropriate to continue this experiment. The Director of 

Laboratories should review this matter with the Air Staff and NASA. The 

Expandable Reentry Structure experiment (D022) should be cancelled. 

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8. In its charge to identify desirable MOL technology which 

might be continued, the Ad Hoc Group carefully reviewed the Biotechnology 

area. The Group concluded that in the future the difference between flight 

in manned spacecraft and high performance aircraft will become indistinguishable. Also, NASA relies heavily upon the Air Force Aerospace Medical 

Division (AMD),and it would be wasteful of national resources to establish 

a similar capability at NASA. Therefore, the Group recommends that 

continuation of a balanced activity in biotechnology is appropriate and 

desirable. In this context, for example, the Whole Body Exercise effort 

to improve crew conditioning techniques, which has been under development 

in-house by the AMD for MOL, should be continued because of its significant 

contribution to NASA and future Air Force programs. Also, the AFSC and 

NASA should jointly study the possibility of developing a value of man 

experiment in AAP to replace the data which would have been gained from MOL. 

9. The Air Force Experiments for the NASA Apollo Applications 

Program, Human Mass Measuring Device (M-172 and M-074), should be continued 

as joint NASA/DoD efforts as presently negotiated and procured. The MOL 

Suit Donning and Sleep Station Evaluation (D019), and Alternate Restraints 

Evaluation (D020) experiments should be transferred to NASA by Manned Space 

Flight Experiment Board action. 

10. NASA should be encouraged by SAFRD to continue development 

of the MOL suit. If NASA elects to continue the development effort, a 

limited number of Air Force personnel associated with the suit development 

should be detailed to support the NASA effort. 

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11. The desirable technology items related to MOL which might 

be continued as follow-on Exploratory or Advanced Development projects were 

identified. Important adaptations and technological developments evolved 

during the development phase of the MOL program and, it is considered 

highly desirable to have special papers or reports written in each area 

and provided to the scientific and engineering communities. Wide 

distribution would help insure that maximum national benefit is derived 

from MOL technologies. Because of the potential benefit and the small 

costs involved to provide the papers, the Group believes that the MOL 

Program Office should invite the respective contractors to prepare the 

reports and make publication possible after screening by the appropriate 

Air Force Laboratory. 

Although the Group has attempted to assess all known needs, undoubtedly 

additional requirements exist, and the various Air Force elements should be 

encouraged to establish them with the appropriate Termination Contracting 

Officers at the contractors' plants. 

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II. INTRODUCTION 

Cancellation of the Manned Orbiting Laboratory (MOL) Program was 

publicly announced by the Secretary of Defense on June 10, 1969. 

Simultaneously, in accord with the Secretary's direction for an orderly 

closeout of MOL activities, the Air Force issued termination, partialtermination, or stop-work notices, as appropriate, to MOL contractors. 

Review of various contractual efforts for possible application in other 

projects were initiated immediately by National Aeronautics and Space 

Administration (NASA) and Space and Missile Systems Organization (SAMSO) 

in conjunction with the MOL Systems Office. 

On June 30, the Secretary of the Air Force (SECAF) directed the 

Assistant Secretary of the Air Force for Research and Development to 

establish an Ad Hoc Group of appropriate individuals to conduct a formal, 

comprehensive review of MOL residuals to insure that maximum national 

benefit was realized from MOL hardware, technology and experience. The 

objectives of the Group included the identification of all significant MOL 

Program residuals that might be useful to DOD and/or NASA and review of the 

disposition actions and plans and recommendations thereof. Also the objective 

included the identification and recommended courses of action for essential 

MOL work which must be carried on in other Air Force projects as well as 

desirable MOL technology which might be continued. The Group consisted not 

only of representatives from various Air Force organizations, but also had 

member representatives from - the Office of the. Secretary of Defense and the 

National Aeronautics and Space Administration. The Ad Hoc Group reviewed 

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the status of all systems and major subsystems of the MOL Program. They 

also heard views of the major associate contractors regarding their 

suggestions on utilization of MOL Program residuals. Appendixes to this 

report include the directive from SECAF establishing the Ad Hoc Group, 

the composition of the Group and a summary of its activities. 

From the outset of the MOL Program, it was fundamental that flightdemonstrated hardware and proven technology would be used to the maximum 

extent possible. The reason for that approach was to achieve a highly 

reliable and operational space test bed, so that primary emphasis could 

be focused on the basic MOL objectives, i.e.,the determination of the 

extent of man's utility in space for military purposes, and the development 

of experimental hardware for both manned and unmanned defense space 

applications. 

At the beginning of the review by the Ad Hoc Group, it became obvious 

to all concerned that the tangible residual benefits of the MOL Program, in 

terms of advanced technology and hardware directly applicable to other 

military and civilian undertakings, would be relatively modest when measured 

against the sizeable investment since engineering development was initiated. 

The review by the Ad Hoc Group revealed that a sizeable percentage of 

the engineering test hardware had been completed, and fabrication of flight 

articles had commenced. In this regard, an unmeasurable but real benefit 

of the program is the expansion of manned spaceflight hnow-how across a 

broad segment of industry and Government. 

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The report is divided into three major sections. First, (Section III) 

is a summary of the ?4)L systems status at the time of termination. Secondly, 

subsystems and facilities reviewed for possible use other than routine 

disposition are documented in Section IV. This section also contains 

discussions on essential work that must be continued and ongoing or 

projected technology developments outside the MOL Program which might have 

had an application to future MOL growth versions. 

The MOL Systems Office is in the process of carrying out termination 

procedures per applicable regulations. The Group did not consider it 

within its responsibility to modify or redirect the normal termination 

and disposition activities. It only attempted to review the total activity 

to assure that all elements were considered and to make recommendations to 

the MOL Systems Office as well as to potential users of MOL hardware and 

technology regarding disposition alternatives. 

In considering future planning, the Group became concerned that 

cancellation of MOL might precipitate an extended withdrawal by the DO 

from space-related activities. This subject is discussed in Section V of 

the report. 

The Group did not review personnel reassignments or manpower positions 

because another Ad Hoc Group has addressed the subject. 

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III. MOL SYSTEM DEVELOPMENT STATUS SUMMARY AT TIME OF TERMINATION 

A. MAJOR SYSTEM SEGMENTS 

At termination on June 10, 1969, the MOL Development Program was well 

into the engineering development which had begun in late 1966. Every 

1 

component and subsystem of the total MOL vehicle had been defined and 

designed in detail. All of the hardware components were in some stage of 

fabrication, and the initial development testing of many of them had been 

completed. In some instances long-lead hardware items, particularly in 

the ground support equipment category, had advanced into manufacturing and 

were scheduled for early delivery during CY 1969 and CY 1970. Construction 

of major facilities was scheduled for completion in mid-1969. 

The estimated status of completion of all the significant hardware 

being developed within the MOL Program at the time of program termination 

is presented in summary regardless of current disposition or other utilization. 

A more detailed compilation of the significant hardware developments is 

contained in Volume II, Appendix E which consists of a number of briefings 

presented by the responsible MOL Systems Office development managers to the 

Ad Hoc Committee on July 10, 1969. Although portions of Appendix E differ 

in context and format, they contain, in summary, a complete and detailed 

presentation of the significant developments as evaluated at the time of 

program termination. 

It should be noted that the stages of hardware development varied 

among MOL contractors depending on the maturity of hardware. For example, 

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because the Gemini B was largely a direct adaptation of the NASA Gemini, 

its development status, except for one or two significant modifications, 

was largely complete; and the next step was initiation of .all manufacturing. 

The MOL System development was characterized by the division of the 

MOL vehicle into major segments managed by associate contractors. 

Segment Associate Contractor 

Laboratory Module (LM) McDonnell Douglas, Western Division 

Huntington Beach, Calif. (MDAC-WD) 

Mission Module (MM) General Electric Company (GE) 

King of Prussia, Pa. 

Gemini B (GB) McDonnell Douglas, Eastern Division 

St. Louis, Mo. (MDAC-ED) 

Titan IIIM Booster (T-IIIM) 

(Vehicle System) Martin Marietta Corporation (01C) 

Denver, Colo. 

(Liquid Engines) Aerojet General Corporation (AGC) 

Azuza, Calif. 

(Guidance) AC Electronics Division (ACED) 

Milwaukee, Wisconsin 

(Solid Rocket Motors) United Technology Corporation (UTC) 

Sacramento, Calif. 

Pressure Suit Assembly (PSA) Hamilton Standard (HS) 

Hartford, Conn. 

MOL Feeding System Whirlpool (0) 

St. Joseph, Michigan 

B. COMPLETION STATUS 

The following tables summarize the status of completion of the major 

MOL hardware developments at the time of termination. All estimates reflect 

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normal percentage of the complete effort associated with the particular 

development. For a particular subsystem the percent completion is based 

on the amount expended up to termination and the total cost to carry that 

particular effort through the complete MOL Program cycle including flight. 

MOL Segment 

LABORATORY VEHICLE 

Subsystems 

Contractor 

MDAC-WD 

Completion 

Status (Percent) 

Mission Module Structure 

Laboratory Module Structure 

Attitude Control and Translation 

Environmental Control 

Data Management 

Instrumentation Displays and Consoles 

Communications 

Electrical Power 

Crew Status Monitoring 

Crew Station and Accommodations 

Subcontracts/Subcontractor 

ACTS-SCE 

Low and High Thrustor Assembly 

Propellant Tank Assembly 

Primary Power 

Environmental Control 

Waste Management 

Atmosphere Reactants Supply 

Communications 

Command Subsystem Group 

Pulse Code Mod Assembly 

Data Computation Subsystem 

Monitor and Alarm 

TITAN IIIM 

Honeywell 

Marquardt 

Rocketdyne 

Allis-Chalmers 

Hamilton Standard 

Fairchild Hiller 

AiResearch 

Collins 

Radiation 

Radiation 

IBM 

Radiation 

40 

38 

54 

40 

64 

21 

83 

50 

21 

21 

55 

61 

4o 

15 

57 

53 

40 

7o 

46 

66 

78 

63 

Subsystem 

Booster ICC 46 

Liquid Engines AGC 58 

Guidance ACE 37 

Solid Rocket Motors UTC 35 

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MOL Segment 

Completion 

Contractor Status (Percent) 

GEMINI B MDAC -ED 

Subsystem 

Guidance and Control 

Environmental Control 

Instrumentation 

Voice and Tracking 

Ejection Seat 

Electrical 

Propulsion 

Pyrotechnic 

Landing and Recovery 

Crew Station 

Reentry Module Structure 

Adapter Structute 

MISSION PAYLOAD GE 

35 

55 

45 

45 

75 

6o 

5o 

55 

50 

60 

55 

50 

SubcontractjSubcontractor 

Low "G" Accelerometer Bell , 23 

Visual Display Projector Lear Seigler 42 

Star Tracker Kollsman 52 

Computer Integrated Test 

Equipment (CITE) GE 52 

PRESSURE SUIT ASSEMBLY Hamilton Standard 29 

FEEDING SYSTEM Whirlpool 68 

SPACE LAUNCH COMPLEX 46 Corps of Engineers 92 

MOL SUPPORT FACILITIES Corps of Engineers 80 

The MOL development program was supported by a mixture of governmentowned and contractor-owned facilities. The government facilities were located 

at the AF Western Test Range and the AF Satellite Test Center at Sunnyvale, 

California. All of the facilities at the contractor locations were contractor owned. A detailed identification of all these facilities is provided 

in Appendix D. 

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IV. RESIDUALS AND TECHNOLOGY SELECTED FOR SPECIAL CONSIDERATION 

During the review and evaluation of the complete MOL system development status, the group identified specific items of hardware and technology 

for which special consideration and requirements for exploitation are 

desired. Whereas it is recognized that all possible users were not 

represented, the members did, however, represent all of the likely 

beneficiaries of MOL residuals. The established MOL hardware-disposition 

plan and priorities insure distribution and listing of residual inventories 

to other possible beneficiaries as soon as the inventories become available. 

Forecast dates for individual contractor inventory disposition are contained 

in Appendix E. 

There were a total of 21 individual items selected for special consideration. They are divided into hardware, facilities, and related technology. 

Each item is treated as a separate subject in a standard format covering the 

situation, rationale for proposed actions and proposed action. Below is a 

list of the items discussed. 

1. Food and Feeding System 

2. MOL Suit Development 

3. Waste Management Subsystem 

4. Two Gas Controller 

5. Laboratory Module Simulator 

6. Computer Integrated Test Equipment 

7. Data Processing Equipment 
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8. Gemini Aerospace Ground Equipment 

9. Fuel Cells 

10. Attitude Control Engine 

11. MOL Flight Computer 

12. Mass Measuring Device 

13. MOL Related Experiments Assigned to AAP 

14. Titan IIIM Hardware and Development Effort 

15. MOL Support Facilities 

16. Space Launch Complex No. 6 

17. Air Force Satellite Control Facility 

18. Recovery Staging Base 

19. Technological Achievements. Suitable for Publication 

20. MOL Crew Whole Body Exerciser 

21. Expandable Structures 

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A. MOL HARDWARE 

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1. Food and Feeding System 

Situation: The U.S. Air Force and NASA have been engaged in a 

joint program, directed toward development of in-flight food and food 

preparation and eating techniques for approximately six years. The MOL 

Program termination requires that NASA review the activity in in-flight 

food development which was sponsored at this time by the U.S. Air Force. 

NASA has expressed willingness to assume contractual and technical 

management responsibilities of the MOL contract with Whirlpool Corporation, 

for one year, beginning July 31, 1969, (Option A). Any time during this 

year NASA may extend the contract beyond July 31, 1970, (Option B); and, 

at any further time, NASA may elect to contract for production (Option C). 

Agreements were reached for the implementation of contractual transfe; 

to NASA/MSC by July 31, 1969. 

Rationale for Proposed Action: The Food and Feeding System is 

a joint effort with NASA, end the system is presently being used on Apollo. 

Proposed Action: The Group concurs with the action to transfer 

the Whirlpool contract to NASA by July 31, 1969. 

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2. MOL Suit Development 

Situation: Immediately following the announcement of cancellation 

of the MOL program, NASA requested that the Air Force continue the HamiltonStandard contract on suit development through July 31, 1969, on a minimum 

expenditure basis. This action was taken to permit the contractor to 

incorporate a number of mandatory changes into suits nearing completion. 

Although the Air Force contract will not, by July 31, 1969, result in 

delivery of flight-qualified suits, approximately 13 training suits and 

a number of development suits and components will have been delivered. 

Rationale for Proposed Action: NASA, because of unique requirements imposed by lunar-surface extra-vehicular activity, and other Apollo 

and Apollo Applications considerations, has a vigorous suit-development 

program underway at MSC. The MOL suit had unique mobility and self-donning 

features, however, which may be very useful for AAP. The Air Force depended 

heavily upon the MOL suit development for the advancement of suit technology;and 

in-house R&D had been reduced under pressure of a squeeze on resources. 

Cancellation of the MOL undercut the in-Air Force program. Although the 

Air Force closely cooperates with NASA in the area of suit development, it 

still will require the re-establishment of a vigorous in-house suit development program in order that it can support its high-altitude aircraft programs 

as well as maintaining a competence in space-suit technology. At least, as 

an interim measure, the Air Force should transfer MOL suits and suit 

personnel to NASA in order that the technology and experience levels will 

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be maintained while the Air Force is re-establishing its in-laboratory 

program. 

Proposed Action: The Air Force should re-establish its exploratory 

development program for space-suit technology. Initially, MOL training 

and development suits should be transferred to NASA, and NASA should continue 

development of the MOL suit. Air Force personnel to support this work 

should be detailed to NASA until an in-house program can be re-established 

to maintain capabilities for the future in this area. 

A 

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3. Waste Management Subsystem 

Situation: The Fairchild-Hiller Corporation has been under 

contract for major elements of the MOL Waste Management System. In midFebruary, 1969, NASA, through the McDonnell Douglas Corporation, contracted 

with the same corporation for the adaptation of certain MOL system components 

and technology to satisfy the requirements of the Apollo Applications 

Program. The waste management subsystem is part of the Environmental Life 

Support System and the contract was terminated. 

Rationale for Proposed Action: This system development is uniquely 

applicable to the NASA waste management system because of the inter-relationship of the Air Force and NASA efforts. 

Proposed Action: The group concurs that all of the tooling and 

development and test components produced under the MOL contract should be 

transferred to NASA. 

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4. Two-Gas Controller 

Situation: The basic method of controlling the atmospheric gas 

in NASA's Apollo Application Program (AAP) is very similar to that planned 

for MOL. Both systems sense total pressure and partial pressure of oxygen. 

The two systems vary in the hardware implementation of the control valving; 

MOL uses an electronic controller whereas AAP uses the flight proven Apollo 

cabin pressure regulator in conjunction with a solenoid valve. The contract 

for the two-gas controller was terminated. 

Rationale for Proposed Action: Because of the similarity and 

the proven flight experience of most of the AAP components,there does not 

appear to be an advantage to consider the MOL two-gas controller hardware 

as a system for AAP. However, the MOL partial pressure sensors will aid 

in the testing and verification of the AAP system. 

Proposed Action: The MOL partial pressure sensors should be 

transferred to NASA. The remaining components should be. placed on inventory 

for disposition. 

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5. Laboratory Module Simulator 

Situation: As a portion of their overall responsibility, 

McDonnell Douglas WesternDivision has been under contract to develop a 

laboratory module simulator. Major elements of the simulator include a 

functioning representation of the laboratory module itself, extensive 

stimulus generating and recording peripheral equipment, and operating 

consoles. Although the system was directly applicable to the MOL program, 

much of the logic behind its development, and many of its subsystems and 

components, are applicable to a range of manned space systems. At the 

time of cancellation the simulator basic hardware was checked out and 

operational. Real-time support-system software was coded and checked out. 

Rationale for Proposed Action: The most effective utilization 

of the government investment in the simulator will be realized if it can 

be adapted to another manned space-flight program. If it is not economically 

feasible to employ it in this application, disposition of individual components can be made separately, but the net return from the investment 

to date will be significantly reduced. 

Proposed Action: The contractor should be•requested to consider, 

with appropriate personnel within NASA, the possible use of the simulator 

in the NASA Manned Space Flight Program. This should be determined prior 

to September 1, 1969, to allow timely disposition of the associated computers 

if a requirement is not established. 

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Rationale for Proposed Action: CITE and ACE-S/C equipment was 

designed and produced by General Electric. The ACE design preceded the 

CITE design by a number of years; therefore, CITE represents a second 

generation of automatic check-out equipment and may have a direct 

undating application to the ACE equipment now in use and/or other NASA 

programs. Also, CITE, with its computers, may be desirable for use 

with Air Force programs within SAMS°. 

Proposed Action: The group recommends that the NASA work with 

the Air Force termination officer to identify those specific items of 

hardware which can be used in the NASA program; and when the equipment 

is adequately dentified, these items should be:transferred to the NASA if 

there are no Air Force requirements. Also, the geoup.mcommends that a 

study be conducted by SANSO to determine possible uses of CITE. as a 

system. The computers associated with CITE should not be dispositioned 

until the SANS° study is completed by September 1, 1969. 

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6. Computer Integrated Test Equipment (OITE). 

Situation: CITE basically consists of the following categories 

of items: 

a. Computer System - SDS 9300 Computers, Associated 

Peripheral Equipment and Input/Output Devices 

b. Commend Link 

c. Downlink Automatic Ground Equipment 

d. PCM Acquisition System 

e. Timing System 

f. Display System 

g. MOL/Ground Interface Equipment 

A preliminary review by NASA has indicated that there are considerable 

benefits to be gained if certain technology, documentation,and hardware 

associated with CITE could be made available. The CITE Ground Test and 

Checkout Equipment could be of benefit in furthering the Manned Spacecraft 

Center (MSC) ground checkout and test goals of automating and reducing the 

number of test consoles and test personnel required for checkout operations. 

It is possible that CITE modules and/or components have direct commonality 

features with the NASA Automatic Checkout Equipment-Spacecraft (ACE-S/C) 

systems, so that existing Components could be utilized to support 

operational ACE Station. As soon as the Air Force can provide termination 

inventories and permit direct contact with the manufacturer, the value of 

the existing inventory to the NASA program can be more clearly defined. 

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7. Data Processing Equipment 

Situation: The MOL surplus data processing equipment consists 

of a total of 17 computers as follows: 

4 - SDS 9300 located at MDAC at Huntington Beach for use in 

the All Systems Test Equipment Group (ASTEG). 

2 - SDS 9300 located at General Electric, Valley Forge, for 

use with Computerized Integrated Test Equipment 

(CITE). 

1 - SDS 9300 located at General Electric, Daytona Beach, for 

use with CITE. 

1 - SW 930/2200 located at General Electric, Valley Forge, 

for use with the Mission Simulator. 

1 - IBM 360/44 located at General Electric, Valley Forge, 

for use with the Mission Simulator. 

1 - IBM 360/65 located at MDAC, Huntington Beach, for use 

with the Laboratory Module Simulator. 

2 - Honeywell 24 located at MDAC, St. Louis, for use with the 

1 -Honeywell 324 

Gemini B simulator. 

4 - SDS Sigma 7 located at Martin Company, Denver, used with 

Computerized Aerospace Ground Equipment. 

This equipment has not been listed7on-theiniientorY schedule. 

Meanwhile, a review is being conducted throughout SAM and the 'Air Force 

Laboratories to determine where it can best be used. Preliminary review 

indicates possible uses as follows: 

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a. IBM 360/30: 

(1) By 949 SPO for Command and Control support. 

b. IBM 360/65: 

1 By 949 SPO for software development. 

2 By Air Training Command for 949 training. 

3 By Aerospace as Government Furnished Equipment 

in lieu of presently leased IBM 360/65. 

c. SDS 9300: 

By 949 SPO as driver for user display. 

2 By Aerospace as Government Furnished Equipment in 

lieu of presently leased SDS 930. 

d. SDS Sigma 7: 

1 By Titan. III SPO for continued support of Titan program. 

2 By 949 SPO to drive user displays. 

3 At MIT in support of advanced technology contracts. 

e. IBM 360/44: 

(1) By the 949 SAD in the switching center. 

f. IBM 360 Model: 

(1) By Air Force Avionics Laboratory in the Reconnaissance 

Central Facility in lieu of presently leased equipment. 

Rationale for Proposed Action: The critical need for computers 

throughout the Air Force dictates that assignments of a computer must be 

based on usability, need,and capability criteria. The computers are associated 

with the automated checkout systems and simulators being considered as total 

systems elsewhere in this report. Total Air Force requirements, however, 

must be considered and the computers, as indicated in the discussion on 

. disposition priorities, will be reported in accordance with Armed Services 

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Procurement Regulations (ASPR). Because the computers were procured on 

Air Force contract, the Air Force retains priority over other agencies for 

disposition purposes. 

Proposed Action: The Group concurs that the computers should be 

listed on inventory schedule and dispositioned in accordance with ASPR; 

however, disposition should be held in abeyance pending completion of SAMBO 

review and review of needs for CAGE, CITE, and the simulators reported upon 

elsewhere in this report. Disposition of the computers should be initiated 

after September 1, 1969, if no use for the systems are determined. 

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8. Gemini Aerospace Ground Equipment (AGE) 

Situation: With the inception of the Gemini B-MOL Program, an 

official agreement between NASA and the DoD on the "Procedure for Transfer 

of NPSA Gemini equipment to the USAF for utilization on the Manned Orbiting 

Laboratory Program," was consummated July 15, 1966. The NASA, with its 

more limited need, was to obtain articles of AGE hardware on a loan basis 

and then return them to the Air Force for their ultimate use. The agreement 

also provided for return of the AGE to NASA when the MOL requirement had 

been satisfied. The development of the Airlock module for the NASA Apollo 

Applications Program used Gemini experience and hardware to the greatest 

extent practicable. Aerospace Ground Equipment (AGE) required for the 

Airlock was drawn from existing Gemini AGE inventory and represents about 

80% of the hardware required for the Airlock module. Late in 1968, it 

became evident that sufficient quantities of certain items were not 

available to support manufacturing and fbrecast launch schedules of both 

programs. Subsequently, NASA and the Air Force had been working together 

to reduce tice quantity of additional AGE articles needed to support both 

programs. 

Rationale for Proposed Action: The NASA Airlock program has a 

continuing direct application fbr this equipment. Furthermore, the Air Force/ 

NASA agreement provides for the return of the equipment to NASA. 

Proposed Action: The group concurs that the Gemini AGE 

equipment should be returned to NAA. 

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9. Fuel Cells 

Situation: Allis Chalmers was developing a 2 kilowatt radiatively 

cooled fuel cell for the MOL and possibly for the Apollo Applications 

Program (AAP). The MOL Program was funding the engineering development 

of the fuel cell and NASA was funding the qualification testing. One fuel 

cell has been completed and most of the components exist for two more fuel 

cells. NASA requirement for fuel cells on AAP has been recently cancelled. 

Rationale for Proposed Action: A proposed FY 70 Advanced Development Program for fuel-cell development was disapproved by AFSC because of 

budgetary considerations. Air Force Aero Propulsion Laboratory (AFAPL) 

FY 70 efforts in Exploratory Development are still programmed to proceed as 

planned because there are applications for fuel cells for unmanned satellites, 

hard-rock silos and remote-standby power. These. efforts consist of component 

developments for high performance, high power density,and regenerative 

fuels. AFAPL is also working with other Air Force agencies on the possible 

deployment of a liolo watt fuel cell in another program. 

Proposed Action: The Group concurs in the AFAPL request that 

the completed units and components be shipped to them for further study,.test, 

and evaluation. 

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19. Attitude Control Engine 

Situation: MOL attitude control engines of 22 and 1001b. 

thrust were being adapted from NASA engines. Some thrusters are available 

as a result of the MOL termination. One 22-1b. thruster has already been 

shipped to the Air Force Rocket Propulsion Laboratory (AFRPL) as part of 

their request for four engines (2-22 lb. thrust and 2-100 lb. thrust). 

The NASA Lewis Research Center will design, build, and test two 

complete flightweight space propulsion (research) modules. One module 

will use Hydrogen-Florine as primary propellants; the other, flox-methane. 

They hope to delineate all real spacecraft problems including interactions 

such as mutual freezing between primary and secondary propellants, or 

the effects of plume heating from the secondary propulsion. For secondary 

propulsion, current analyses indicate earth storable by propellant engines 

to be the most likely choice. 

Rationale for Proposed Action: The engines and components are 

no longer required by the MOL Program, but can be used. by the AFRPL to 

refine an in-house pulse-performance computer-simulation model of attitude 

control engines and to complete an in-house project to determine the effects 

of attitude-control engine-exhaust products on optical and radar windows. 

This latter program is 80% complete. The results of both these programs 

will be made available to NASA. 

For direct use in the NASA program, they estimate the need for 8 to 12 

each of the 22-1b. and 100.1b. thrust engines complete with tankage and 

feed systems if possible. However, four engines each would be of great 

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assistance because additional thrusters could be purchased if these engines 

are selected after preliminary system interaction testing. Excess propellant 

valves could be used for some of the Viking simulation effort at JPL. 

Proposed Action: The Group concurs with the transfer of required 

22 and 100-1b. thruster and attitude control engines to MEL. The 

remaining engines and associated tankage and fuel systems should be 

transferred to NASA. 

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11. MOL Flight Computer 

Situation: The IBM 4 Pi Extended Performance (EP) computer and 

its peripheral equipment (printers, keyboard, display unit, auxiliary' 

memory unit and laboratory data adaptor unit) provided the integrated 

on-board data computation capability. The contract for the computer was 

terminated and inventory lists should be available in approximately 90 days. 

Rationale for Proposed Action: Proposed uses for the MOL 4 Pi 

EP computer include the Integrated Medical and Behavioral Laboratory 

Measurement System (IMBLMS) and the On-board Checkout System (OCS). These 

systems are being developed by NASA for potential use in future space 

programs including the NASA dry.workshop, space station, space base, lunar 

base, and space shuttle. The technology is also adaptable to other 

aerospace and aircraft programs. 

The IBM 4 Pi EP computer is a vital part of the IMBLMS functional 

breadboard and will probably be part of the later versions. Prior to the 

MOL cancellation, the NASA Manned Spacecraft. Center (MSC) had planned to 

borrow a 4 Pi computer for six months and then purchase one. 

OCS is being developed to provide on-board checkout of long duration 

spacecraft subsystems and experiments. It will be capable of operation in 

automatic, semi-automatic and manual modes. The 4 Pi EP computer is utilized 

in the Martin Company flight packaged OCS development unit to be delivered 

to MSC for test and evaluation. One 4 Pi EP computer has already been 

purchased for this unit and another is desired to test multi-processing 

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Another potential use of the 4 Pi EP computer is to provide experience 

for the forthcoming Apollo Telescope Mount 4 Pi Tactical Computer (TC) 

used for attitude control in the Apollo Applications Program (AAP) dry 

workshop. Both computers are members of the same family and experience 

with one will be beneficial to use of the other. 

In addition to the basic IBM 4 Pi computers and the associated software 

and documentation, available peripheral equipment such as the laboratory 

data adapter unit, keyboard, printer, display, system control panel, 

maintenance equipment, auxiliary memory unit, computer subsystem control 

are required. 

The MOL 4 Pi computer. is an extended performance model which may be 

useful and needed by Air Force space or aeronautical programs. 

Proposed Action: The Group recommends that the Air Force 

Aeronautical Systems Division be made aware of the availability of the 4 Pi 

computer equipment, and the total Air Force requirement should be investigated 

by the Air Staff (AFRDC). The peripheral equipment should be transferred 

to NASA along with a 4 Pi computer if available after Air Force investigation. 

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12 Mass Measuring Device --A 

Situation: The Aerospace Medical Division (AMD) of the Air 

Force Systems Command (AFSC) has designed and built a device for use by 

the MOL that will measure mass and mass changes within 1% accuracy. The 

device was designed to provide this capability over two ranges of masses, 

those from 1 gram to 1 kilogram and those from 1 kilogram to 100 kilograms. 

These devices represent a new invention by in-house scientists. Patent 

applications have been submitted. 

Flight prototypes of both the small and human mass devices have been 

completed; laboratory tests, including zero gravity Keplerian flight tests, 

have been completed and have validated the design and anticipated accuracies. 

Flight demonstration of the mass measuring devices has been proposed 

by AMD as an experiment for the NASA AAP. The experiments have been approved 

by NASA as M-172 Human Mass Measuring Device and M-074 Small Mass Measuring 

Device. 

Subsequently, NASA proposed to use the AF experiment units for 

operational measurements over both ranges of mass during the AAP missions. 

As a result NASA and AMD re-negotiated the experimental protocol and plans 

for funding. Air Force participation in this experiment is being carried 

by the Air Force Exploratory Development Program in Aerospace Biotechnology. 

Flight hardware for these experiments is under procurement. 

Rationale for Proposed Action: The availability of an accurate 

mass measurement system for measuring small masses and large masses permits 

the biologist to undertake an accurate in-flight energy and fluid balance 

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program for the first time. Accurate tally of the amount that has been 

eaten and drunk by the crewmen can be established. Comparison of this 

data with accurate measured data of the diet makeup permits daily inflight 

assessment of energy intake. Measurement of the mass of urinary and 

solid waste output permits the establishment of the other side of fluid 

and energy balance only as long as fluid loss through sweating is controlled. 

The periodic measurement of total body mass will provide a cross-check of 

the accuracy of the daily intake-output assessment. Measurement of total 

body mass becomes essential in the flight assessment of any biomedical 

changes that might occur through severe sweating (i.e. suited operations, 

temporary loss of thermal control of the vehicle, etc.) or gastrointestinal 

upset (i.e. vomiting, diarrhea, etc.). It also provides essential check 

data for evaluating the effectiveness of any efforts at replacement of 

the fluids lost by the events above. 

Proposed Action: The successful development and flight qualification of the mass measuring devices will provide important tools for 

the daily assessment of crew status during prolonged missions. The devices 

should be continued to completion of the experiments on AAP. The Air Force 

should continue the experimental and operational plans for flight of these 

mass measuring units as planned before MOL termination. 

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13. MOL-Related Experiments Assigned to AAP 

Situation: Two MOL-related experiments have been under Air Force 

development to be flown in NASA AAP missions. The first, entitled Suit 

Donning and Sleep Station Evaluation (designated as D019 by NASA) was 

to permit evaluation of the techniques and time required for pressuresuit donning and for the evaluation of sleep restraints. The second, Alternate 

Restraints Evaluation, D020, was to evaluate various crew restraint devices 

designed for use in both operating and maintaining equipment. Testing was 

to include foot, leg, waist, pelvic and head restraints, MOL tools, task 

board and pressure suits. McDonnell Douglas Western Division has been 

under contract for the development hardware has been produced. Manufacture 

of flight hardware has not been authorized. 

Rationale for Proposed Action: Although the experiments were 

planned for direct support of MOL, the problems to be studied are common 

to all zero-g manned spacecraft. NASA has a number of complementary 

experimental activities underway for flight in AAP. It is appropriate, 

therefore, for DoD to withdraw the experiments from the NASA flight program, 

and to transfer the designs and development hardware produced under Air 

Force contract to NASA for possible incorporation into NASA experiments 

or flight systems. 

Proposed Action: It is recommended that the DoD members of the NASA 

Manned Space Flight Experiment Board be instructed to withdraw the request 

for NASA to fly D019 and D020, and to transfer the experiment design and 

development hardware to NASA for their possible experimental or operational use. 

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14. Titan IIIM Hardware and Development Effort 

Situation: The termination of the MOL Program and issuance of 

cancellation instructions to the Titan IIIM associate contractors seriously 

impacted the Titan III B, C, and D programs. Several developments under the 

Titan IIIM contracts were planned for and scheduled for integration into 

the Titan III B, C, and D production. 

Contract Change Notices and RFP's have been issued to Titan III 

contractors to continue the essential development efforts under the 

appropriate Titan III B, C, and D contracts. Examples of this effort are: 

completion of design and fabrication of test equipment, test fixtures, and 

simulators for re-designed and improved subsystems, completion of 

Electromagnetic Interference (EMI) and qualification tests on common avionics 

components, completion of development of improved Stage II engine, Stage I 

battleship tests, continuing Titan IIIM initiated production of common items 

of hardware required for current and follow-on booster buys. The qualification tests of the Thrust Vector Control system will continue through 

three additional static firings of the Titan IIIM 7-segment SRM's. The 

termination of the Titan HIM reduced the production base on the common 

guidance computer to the point that further purchases have become uneconomical. 

A competition will take place to develop and qualify a new guidance computer 

that will have a larger production base than just Titan III; e.g., computer 

used by Agena, NASA/Centaur and aircraft programs. Also, studies are underway 

to determine the most effective use of the residual technology and equipment 

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such as Computerized Aerospace Ground Equipment (CAGE) for use on other 

Titan III programs. 

Rationale for Proposed Action: Failure to complete the essential 

developments would result in even greater expense in terminating portions 

of current B, C, D program efforts, re-engineering and re-procuring to 

earlier configurations, and associated payload program schedule slippages. 

Also, payload design and weight constraints have, in many cases, been 

relaxed to take full advantage of expected improved launch vehicle capabilities. Additionally, the CAGE system, which incorporates Sigma 7 

computers, represents an advancement in vehicle check out methods and employs 

a unique machine launguage and data compression technique which could be 

useful to the other Titan III programs. FY 70 and 71 funds are presently 

programmed for the updating/modernization of the Aerospace Ground Equipment 

(AGE) for Titan III at the Eastern Test Range. Residual Titan IIIM CAGE 

use is proposed. 

Proposed Action: SAMSO has received authority to transfer the 

essential development efforts to the appropriate TitanIII contracts for 

completion and the group supports the action. Also, the group concurs in 

the study efforts that are under way to consider possible application of 

the CAGE and residual hardware for use on other Titan III programs. However, 

a determination on the use of CAGE should be made by September 1, 1969, to 

allow timely disposition review of the computers in accordance with Armed 

Services Procurement Regulations should CAGE not be used as a system. 

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B. IDOL FACILITIES 

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1. MOL Support Facilities 

Situation: As a result of the MOL cancellation, three buildings 

designed as MOL support facilities at Vandenberg Air Force Base have become 

available for other use. The buildings are the Engineering and Operations 

Building (E0B), Operational Readiness Unit (ORU), and the Operational 

Training and Evaluation Facility (Oak). These facilities are currently 

80% complete and are usable structures which can be occupied with some 

outfitting of the interiors. SAMSO, based upon agreement between the 

6595th ATW commander, the AFWTR commander, and the 1st Strategic Aerospace 

Division (SAC) commander has proposed to AFSC and Air Force that these 

facilities be taken over by resident organizations at Vandenberg. 

Rationale for Proposed Action: This course of action has the 

following advantages: 

a. Vandenberg AFB Headquarters is now scattered and poorly 

housed. The proposed move would allow the. Headquarters activities to be 

properly consolidated under one roof in the area most appropriate to its 

function. 

b. At the present time, AFWTR occupies a part of the 6595th 

ATW Headquarters building and, as a matter of fact, a large addition to this 

building is under construction for their use. Future plans call for 

construction of an additional technical building in this area for the AFWTR. 

Thus, the proposed move of AFWTR to the 6595th ATW Headquarters building 

does permit them to consolidate all of their activities in the area most 

appropriate to their needB. 

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c. Although the 6595th ATW is adequately accommodated in 

its present building, the new facilities will be suitable for their needs 

and should be done to accommodate a and b, above. Their relocation into 

the MOL facilities should also provide for a better interface with contractors 

and AFCMD. 

Proposed Action: The Group concurs with the proposed re-allocation 

of these buildings as planned to the resident organizations at Vandenberg AFB. 

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2. Space Launch Complex No. 6 (SLC-6) Facilities 

Situation: The SLC-6 includes the launch pad with Mobile Service 

and Umbilical towers; fuel and oxidizer facilities; AGE, Complex Support 

and Ready buildings; Launch Control Center; Solid Rocket Motor Inspection 

and Storage buildings; and small support buildings and utilities. 

On the date of the MOL Program cancellation, the SLC-6 was approximately 

92% complete. The remaining of effort included primarily the requirement 

for the construction contractor to conduct acceptance and demonstration 

tests prior to Air Force acceptance at the beneficial occupancy data. The 

decision was made to complete the construction, demonstration testing and 

Air Force acceptance. The following phases such as AGE installation were 

cancelled. The facility will be maintained in a "down mode" caretaker 

status. The down mode status involves the minimum operation and maintenance 

of critical items that cannot be feasibly removed and stored. The detailed 

down mode maintenance plan is being prepared by the 6595th Aerospace Test 

Wing. The implementation of the plan is to be accomplished by a caretaker 

crew consisting of approximately four people from the .6595thATif and supported 

by the 4392nd Civil Engineering Squadron (SAC). 

Rationale for Proposed Action: It is the opinion of the group that 

the above plans will provide maximum protection of the Air Force investment 

and allow potential future use at a minimum cost and effort. 

Proposed Actions: The Group concurs with the assignment of SLC-6 

to SAMSO for possible use with current and/or future Titan III programs. 

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3. Air Force Satellite Control Facility 

Situation: The termination of the MOL Program eliminated the 

requirement for the Advanced Data System and the MOL portion of the 

Advanced Satellite Test Center (ASTC). The ASTC is complete and the 

integral power plant is to be completed in September 1969. The current 

status is as follows: 

a. Advanced Data System was terminated except for the 

Remote Tracking Site Tasks and delivery of Control and Display equipment 

which was 9094 complete (Lockheed). 

b. MAL software integration and computer program development was terminated (SDC). 

c. MOL software development for Remote Tracking Sites 

was terminated (Mellonics). 

d. Software modeling contract was terminated; the 360-67 

Triplex computer and 360-67 Duplex computer leases were cancelled (IBM). 

e. The CDC 6600 computer lease was cancelled and the associated 

operating system development was terminated (CDC). 

Rationale for Proposed Action: The move of the existing satellite 

programmfrom the STC to the'ASTC will allow cancellation of the approved 

support facility addition to STC. Consolidation of the software development 

test facilities now at Santa Monica and Santa Clara in the ASTC will provide 

for efficient and economical software support and facilitate the move of 

the satellite programs to the ASTC. 

Proposed Action: The Group concurs with the actions that have 

been taken and the proposed move into the ASTC. 

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4. Recovery Staging Base 

Situation: The MOL Program has negotiated for the use of the 

6200 foot airfield at Easter Island as an recovery aircraft staging base 

in the event of a launch abort. The potential use of this airfield by the 

Air Force Western Test Range and/or NASA was considered. The airfield 

construction is completed. 

Rationale for Proposed Action: NASA has indicated no requirement 

for recovery forces in this location and the airfield is not adequate for 

the Range instrumented C-135 aircraft use. 

Proposed Action: No future action required. 

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C. RELATED TECHNOLOGY 

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1. Technological Achievements Suitable for Publication 

Situation: Although no new technology was developed, important 

adaptations or unique techniques to existing technology evolved in several 

areas during the course of the MOL development program. Because of the 

particular technology or capability, the following list of items are presented 

for consideration as subjects for special papers to be published in order to 

provide wide distribution to the scientific and engineering communities. 

The production of these papers may require costs for preparation and, in 

some cases, only the compilation of test data. Each item should be reviewed 

and treated separately on its own merit and on its related application. 

a. Cylindrical Structures 

The MOL decision to use a waffle rather than a smooth 

cylindrical structure on a space vehicle should be of interest to the 

engineering/scientific community. It is believed that a 25% weight savings 

was realized when considering the strength-to-weight relationship. The 

Technique to achieve optimum design is unique, particularly in areas of 

combined multi-dimensional skin (MDAC-WD) 

b. Bearing Technology 

Unique application of bearing technology allowed 

reduction in ripple (noise) in slow moving ball bearings. (GE) 

c. Torquer Technology 

Reduction in noise (ripple, cogging, brush noise) in 

slow: moving torquers. (GE) 

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d. Majority Vote Redundancy 

A new method for continuous failure mode monitoring 

of three redundant electromechanical channels with automatic and instaneous 

selection of the most probable channel. The theory and hardware being tested 

have potential use on high reliability (man-rated) systems, either aircraft 

or space vehicles. (MSC) 

e. Computerized Aerospace Ground Equipement(CAGE) 

CAGE is automated control and checkout system which 

monitors, analyzes, displays, controls, and records data from any test article 

in real time. The CAGE system utilizes unique machine language and data 

compression techniques. The fully developed CAGE hardware has potential use 

in the pre-launch and in-flight portions of space programs, flight line 

verification of aircraft systems, and large environmental test programs. (M4C) 

f. MOL Pressure Suit Assembly (PSA) 

This pressure suit is unique in providing the best 

performance mobility available in US Aerospace technology today. (AND) 

g. Crew Conditioning Unit (CCU) 

The CCU is a unique exercise device which the space 

crewman uses to quantitatively exercise selected body/muscle systems and to 

stablize cardiovascular deconditioning resulting from prolonged exposure to 

weightlessness. (AMD) 

h. Manned Space Radiation Dosimetry 

The Charged Particle Spectrometer (CPS) and the Active 

Biological Dosimeter (ARD) are a pair of unique instruments which provide 

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a means of measuring space radation and relating it to the dose received by 

the crewman in the spacecraft. The CPS can also provide data useful in the 

prediction of the solar events as they relate to mission programming. (AMID) 

i. Mass Measurement Unit (MMU) 

The MMU is a unique device developed to accurately 

measure the weight/mass of a man in the weightless state in order to evaluate 

his water balance relative to the effects of the flight environment and the 

qmoity of life support. A report on the MMU prototype has been published 

by AMD School of Aerospace Medicine. CAM')) 

j. Monitor and Alarm Subsystem (MAS) 

The MAS monitors those functions which have been determined 

critical either to the safety of the crew or to the completion of the mission. 

It provides an oral and visual alarm (warning or caution) output in event 

of an out of tolerance condition. The MAS accepts data inputs, and provides 

output which activates visual and oral alarm, caution and warning pronunciators, 

and automatic master circuits. (MDAC-WD) 

Rationale for Proposed Action: The techniques involved in each 

of the preceeding areas should be carefully screened by the applicable 

Air Force laboratory to insure its usefulness and desirability to the 

scientific and engineering community. 

Proposed Action: The Group recommends that the MOL Program Office 

in conjunction with the Director of Laboratories should take appropriate 

action to have the papers published. 

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2. MOL Crew Whole-Body Exerciser 

Situation: The Aerospace Medical Division (AND) of AFSC has 

designed in-house a crew exercising apparatus to be used by the MOL crew 

during flight. Proper use of the apparatus was expected to counter the. 

physiological deconditioning of the men due to weightlessness during the 

mission. The design of the apparatus permits the flexible scheduling of 

sufficient daily physical exercise during flight in a manner that the men 

are maintained within acceptable medical and physiological bounds. This 

apparatus represents a new invention by in-house scientists. 

The design of the MOL vehicle flight prototype of the apparatus was 

nearing completion at the contractor at termination of the program. 

Laboratory prototypes of the flight model were complete. Similar units 

used for collecting ground data during bed rest (weightless analogue) 

studies have been constructed and are under test at AMD. These units were 

to be used in the training of the crewmen. 

The MOL Program and AMD proposed an experiment for testing the exerciser 

on the NASA AAP. The objectives of the experiment would test the adequacy 

of the engineering design, verify the crew interfaces with the apparatus, 

and provide a cross-check of the flight results with that seen during the 

ground studies. The NASA, Aeromedical Scientific Advisory Group requested 

the MOL and AMD to undertake a more comprehensive study than the initial 

experimental prototype because the use of the exerciser, if shown to be 

adequate, offered great promise for the maintenance of crew conditioning 

during prolonged weightless flight. If the concept of whole-body exercise 

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is demonstrated, NASA then could consider the approach for long termed 

conditioning of crewmen. They recommended, as a first step, the undertaking 

of scientific ground study to verify the Whole-Body Exercise concept as well 

as the demonstration that the exercise unit is capable of providing the 

exercise levels desired. The NASA. committee's recommendations were accepted 

by MOL and AND and the ground studies were underway in the USAF School of 

Aerospace Medicine at MOL termination. 

Rationale for Proposed Action: Analysis of the physiological changes 

observed in space crews to date indicate that an adequate exercise program 

may provide the best single and the most versatile approach for maintaining 

crew conditioning to within adequate limits during prolonged weightless 

flight. Demonstration of the validity of this approach through both ground 

studies and flight offers to future programs an alternate to the provision 

of artificial gravity now expected to be needed for crews during long 

missions. 

Proposed Action: This approach to crew conditioning and the 

associated hardware development are of such potential importance to future 

long termed manned space-flight that the following actionwahould be required: 

a. Because this approach is an "in-house Air Force invention" 

and the NASA operations has expressed a degree of reservation on its use 

until proven, the Air Force should continue the laboratory studies to a 

point of confirming the adequacy of both the concept and the equipment. 

b. After demonstration of the concept, the Air Force should 

undertake negotiations with NASA to either confirm the concept and equipment 

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as an experiment or, as in the case of the mass measuring units, develop 

a joint program for flight testing and operational use of the concept and 

equipment. 

c. To achieve a and b above, the program for "whole-body 

exercise" be incorporated into the Air Force Exploratory Development Program 

as soon as possible. 

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3. Expandable Structures 

Situation: Expandable Airlock (D021) and Expandable Reentry 

Structure (D022) Experiments were approved in 1967 for testing on the NASA 

Saturn IVB Orbital Workshop under the assumption that expandable structures 

might find application on manned spacecraft which were follow-on to MOL. An 

Advanced Development Program on Expandable Structures was programmed for 

$1.5M in FY 70. Major emphasis was to be given to manned spacecraft 

applications. 

FY 70 Exploratory Development Funds for the experiment are withheld. 

No FY 70 funds are apportioned for the Advanced Development Program. 

Rationale for Proposed Action: With the termination of the MOL 

Program and the re-orientation of the NASA Orbital Workshop, no FY 70 

Exploratory Development Funds should be expended until NASA's programs 

become firmer. The proposed Advanced Development Program was also tied 

in part to manned spaceflight applications. AFSO recommended, that no FY 70 

funds be apportioned because of budget restrictions and relative priorities. 

The termination of MOL served only to reinforce this position. 

Proposed Action: The Group concurs with the plan to withhold 

funds for D021 experiment until NASA's plans are firmer. Since the hardware 

is complete, the Director of Laboratories should explore with NASA the 

future of this experiment. The D022 experiment should be cancelled. 

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V. PLANNING CONSIDERATIONS 

A. AEROSPACE BIOTECHNOLOGY 

1. Background 

The cancellation of the MOL Program eliminated the only DoD 

manned spaceflight program. The question arises as a result of this action 

as to whether the Air Force should continue or discontinue the development 

of space-related biotechnology for man and man-support systems. 

Appendix F summarizes the AMD analysis of the impact of MOL cancellation 

on the program element "Aerospace Biotechnology." The major part of the 

RDT&E program carried out under this program element is done in the 

laboratories of the Aerospace Medical Division (AMD) of the Air Force 

Systems Command. The space-related efforts are an integral part of a 

program to develop the requirements for man to live and work in the wide 

spectrum of aerospace environments and to develop the necessary equipments 

and procedures to provide these requirements. This R&D program recognizes 

that man may need to operate a variety of vehicles in several types of 

hostile environments. In this regard, manned space operations is considered 

as a natural extension beyond conventional aeronautical Operations. It is 

recognized that specific tailoring of the data and systems selection is 

necessary for each program to insure that the best solution for that 

military system is achieved. 

Only a small number of specific MOL tasks were underway within the 

AMD laboratories. Most of the other space-related work was being carried 

within this program element and was of a more general nature. In most cases 

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it is considered the next logical step in an evolving technology base. Thus 

the data were equally applicable to MOL or NASA programs. 

Specific actions taken on this program element since MOL cancellation 

include: Deferral of 8.0 million out of a total of 21.0 million requested 

for this program element for FY 70; reduction of the total funds for this 

program element from 21.0 million to 19.0 million, the 2.0 million reduction 

was taken from the deferral area and results in only a 6.0 million deferral 

remaining; AFSC is carrying on discussions with NASA to redefine their 

areas of data need in light of the MOL cancellation, the identification 

of the areas of unique Air Force resources to provide these needs, and the 

re-evaluation of NASA's fiscal participation in these efforts. 

That portion of the proposed FY 70 budget related to the development 

of technology applicable only to spaceflight was 1.47 million. The remainder 

of the requested 21.0 million for this program element was proposed for 

work to support man in all operational Air Force environments, included 

such areas as aircraft, missile launch control centers, spaceflight as well 

as research and development in military medicine. 

The cancellation of the MOL Program, as announced, was based upon the 

current fiscal considerations and the fact that most of the current military 

space needs can be achieved by unmanned satellites. The discussion surrounding 

the cancellation noted that the DoD maintained an interest in manned spaceflight and would continue to assess each new program on its own merit as 

to whether man had a role. It was recognized that in the interim the DoD 

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must rely heavily upon NASA to collect data on the flight aspects of 

manned spaceflight. 

2. NASA Cooperation on MOL 

During the early phases of the MOL, the NASA and Air Force bioastronautics teams made every effort to gain maximum benefit from the NASA 

experience. However, the direct translation of NASA experience to the 

specifics of MOIL operations proved quite difficult. In the basic sciences 

and life systems criteria areas, it was found that NASA data, although 

fully provided by NASA, did not permit direct program interpretation. The 

most valuable source of data for the military application was gained from 

the Air Force Laboratory scientists who had performed related studies in 

areas of mutual Air Force/NASA interests. These scientists were able to 

provide the detailed laboratory data and interpret their significance to the 

military circumstances proposed for MOL. Fortunately, most of the critical 

crew-related design areas had been under active study within the laboratories 

either for aircraft or combinations of aircraft and spacecraft applications. 

In many of the most critical areas, joint NASA/Air Force programs were underway. 

This arrangement had also been of benefit to NASA because the Air Force 

Laboratories contained unique facilities for making the complex environmental 

studies, and of more importance, had the multiple scientific and engineering 

disciplines needed to carry out the long-term studies for currently operating 

programs. Such a combination of facilities and associated staff to operate 

them is unavailable elsewhere. Key scientists from these laboratories were 

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appointed as consultants and advisors to the MOL Program. The resulting 

familiarity with the MOL Program problems permitted them to evaluate and 

redesign their own laboratory efforts, thus both MOL and laboratories 

benefited from this working relationship. 

A similar situation was found when the translation of medical 

operational aspects of NASA experience to the MOL Program were addressed. 

As a result a request was made by MOL, and accepted by NASA, to permit MOL 

bioastronautics personnel to work directly with the NASA operations during 

Gemini and Apollo flights. This proved to be highly satisfactory to both 

programs and the most adequate way of insuring meaningful exchange and 

training. Experience gained during NASA flights by the MOL personnel could 

then be interpreted and applied to the MOL specific problems. 

3. Future Needs 

The AMD Laboratories operate primarily as in-house laboratories. 

Thus, the major part of the funds represented in the "Aerospace Biotechnology" 

program element are used in direct support of this capability. A large 

portion of the remaining so-called contractual funds also are used to either 

augment the technical base of the in-house laboratory or to upgrade the 

capacity of the facilities. Marked reduction of funding or the establishment 

of a policy prohibiting these facilities to continue efforts covering the 

total scope of biotechnology, supporting the entire range of Air Force 

missions will stunt the capability of this set of facilities and its staff 

to maintain their pre-eminence in the field of biotechnology. 

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Since military pilots are urged to fly higher and faster, and modern 

military aircraft operate at the threshold of exo-atmospheric flight, it 

is prudent that the Air Force maintain its competence across the entire 

spectrum of biotechnology. If the Space Transportation System proceeds 

in the next few years, the special categorization of spaceflight versus 

airflight will cease to exist. 

In accepting this point, the space-related biotechnology areas being 

carried under the "Aerospace Biotechnology" program element should be 

continued as active and vital efforts, and the Air Force should continue 

assigning selected bioastronautics personnel for tours with the NASA Manned 

Spaceflight in order that actual operational experience will be gained. 

4. Experiment on Value of Man in Space 

The plans to assess the value of man in the performance of military 

tasks, as planned for in the MOL 30-day missions, was terminated with the 

cancellation of the program. MOL's experimental activities and operations 

plan provided a unique opportunity to perform a controlled, statistically 

significant evaluation of man's role and contribution to a demanding series 

of mission-like tasks. 

Analysis of the MOL experimental tasks developed the following unique 

factors: the crew would be tested to near maximum rates of performance in 

both the sensory and motor functions of man; the daily workload demanded 

sustaining this high.level integrated performance for sufficiently long 

periods to permit assessment of man's daily capacity to operate; the weekly 

repetitive orbital tracks and repetitiveness of the experimental tasks 

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offered sequential weekly assessment of man's continued capacity to perform 

over the four-week mission. 

The MOL crew assessment also had the major advantage in that it tested 

man as he performed realistic military operational type tasks rather than 

while he was performing synthetic laboratory tests. Thus, crew motivation 

and the desire to do a good job could be expected to be under control 

throughout the 30-day mission. 

NASA has no equivalent experiment as planned for MOL. NASA, to do 

an experiment equivalent to the MOL effort, would have to create a similar 

dedicated approach containing a daily and repetitive weekly task load that 

would demand activities up to the near maximum capacity of man, and propose 

to fly the experiment over similar flight durations. 

The arguments related to what the role of man in spaceflight should 

be have continued since before the first manned space program, Project 

Mercury. The data needed to scientifically and technically answer these 

reasonable questions have not been gained during the first decade of manned 

flight. Thus, each decision in spaceflight planning has used subjective 

or, at least, qualitative judgments to keep man in the system or exclude him. 

Performance of a man-value experiment would permit these judgments to be 

based finally upon scientific data and provide a base upon which man's role 

and capacities in future programs can be planned. 

Therefore, the DoD and NASA should undertake the formal development 

of an experimental program to develop the data needed for addressing man's 

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role and value in spaceflight. The experimental design must consider not 

only direct measurement of man's capabilities to perform tasks, but also 

provide a comparison of results of man alone, the machine alone and 

combinations of man-machine. The experimental design and plan for management must be made in a manner that will be suitable for submission to the 

NASA Manned Space Flight Experiments Board. 

B. MILITARY SPACE PLANNING 

The primary Air Force project.level planning activity for space and 

space related systems has been the Director of Development Plans (SMA), 

Space and Missile Systems Organization (SAMSO), AFSC. Within SAMSO the 

planning functions have been oriented toward unmanned high-altitude 

operations planning. For example the MOL Program Office accomplished all 

planning for the basic MOL, all growth applications for the MOL system and 

advanced missions in near earth orbit. In support of MOL a portion of the 

SAMSO advanced planning effort has been concentrated on synchronous-altitude 

space-station studies and space rescue/escape systems. 

With the cancellation of MOL, a void in technical system oriented 

planning for manned and rnmenned low-altitude space flight has been created. 

With the phase-out of the MOL Program Office, SAMSO should be given 

the responsibility to examine on a continuing basis military space systems 

in near earth orbit and compare the utility of manned and unmanned systems 

for similar functions. 

The Group supports the plan to expand the SAMSO function to include 

near earth-manned and unmanned mission planning as well as the current 

high-altitude mmanned efforts. 

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Associated with the augmentation of AFSC/SAMSO planning efforts 

toward manned military space flight, all echelons will continue emphasizing 

the establishment of long-range objectives, formulation of policies, 

guidance and procedures to exploit promising technology and to orient 

advanced development toward desired operational capabilities. 

The Space Studies line item should be closely monitored and expanded 

if necessary to conduct analytical investigations, studies, and analyses 

leading to the derivation of operational requirements, development plans, 

and documentation to provide a sound basis for Air Force space technology 

and development activities. 

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PROPOSED DISTRIBUTION 

DR. SEAMANS - 1 Copy 

SAFRD (Mr. Hansen/Dr. Yarymovych) - 1 Copy 

SAFSL (Colonel Ford) - 1 Copy plus Master 

SAFUS (Dr. McLucas/Gen. Allen) - 1 Copy 

DDR&E (Mr. Barfield) - 1 Copy 

NASA (Mr. Schneider) - 1 Copy 

DCS/RD (Gen. McNickle/Gen. Hedrick) - 1 Copy 

AFSC (Gen. Ferguson/Gen. Gilbert) - 1 Copy 

SAMSO (Gen. Wilson) - 1 Copy 

MOL SYSTEMS OFFICE (Gen. Bleymaier/Lt. Col Skantze) 1 Copy 
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REVIEW OF CLASSIFIED MOL RESIDUALS 

CONTENTS 

REPORT 

APPENDIXES 

A 

B 

C 

D 

E 

F 

G 

H 

I 

Page No. 

Enabling Document 12 

Committee Members and Classified Minutes 15 

Tracking Mirror Control System 20 

Image Velocity Sensor (IVS) 23 

Bimat On-Board Film Processor 26 

Visual Display Projector 35 

Acquisition Tracking Scope 38 

Simulation Program 41 

Contractors' Briefings 45 

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CLASSIFIED MOL RESIDUALS 

A. INTRODUCTION 

Certain of the MOL residuals, which tend to be highly classified because 

of their direct interface with the primary mission, have potential application 

in other programs. Some such programs are in the reconnaissance/intelligence 

community while others are unclassified. 

The purpose of this annex of the Review of MOL Residuals is to identify 

those items of equipment, discuss their possible applications and make 

recommendations where appropriate. 

In the majority of instances, information relating to a specific 

application of this equipment is not adequate to support a meaningful 

recommendation as to disposition. In such cases, a delay in determining 

disposition,sufficient to permit a thorough analysis of the application, 

has been suggested. There are, however, within the activities concerned, 

sufficient technical management personnel with suitable clearance status 

to make the determinations recommended by the Ad Hoc Group. To this end, 

members of the Group have tasked their respective organizations to undertake 

the necessary studies. Responses with specific recommendations for 

disposition of the equipment have been requested by September 1, 1969. 

Implicit in this effort is the necessity that the funds required to utilize 

the equipment be understood and identified as part of the application 

recommendation. 

The primary optics assembly of the MOL was excluded from consideration 

by the Ad Hoc Group on MOL Residuals. 

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Classified subsystems that have been considered for possible 

disposition are treated on an individual basis. Part of this consideration, 

of necessity, recognized that maximum utility of a piece of classified 

equipment might be realized only if the equipment could be used on an 

unclassified basis. While agreeing in principle, the Group recommends 

that the post MOL utility of a classified subsystem be determined within 

the appropriate security system. Then, if the application so warrants, a 

downgrading of the classification may be considered on a case by case basis. 

Characteristic of each suggested application of the classified 

equipment has been that it envisioned the equipment essentially intact. 

Also, the need for time to conduct a fairly detailed study of the suggested 

application was common. In any event, it would appear reasonable to 

maintain this equipment in bonded storage until each proposed application 

could be thoroughly examined. Final disposition could then be made by 

the Secretary of the Air Force. The security classification of the equipment 

would be addressed at that time. 

B. MIRROR POINTING AND TRACKING TECHNOLOGY 

Technology developed in connection with the DORIAN pointing and 

tracking system, as described in Appendix C, while not fundamentally new, 

represents a significant engineering refinement which may be of value to 

other programs. Specifically, engineering data and development test 

hardware where available on the following should be made available for 

further study: 

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1. Torquers 

2. Bearings 

3. Shaft encoders 

4. Computer derived drive signals 

5. Mission data adapter unit 

This technology has potential applicability to any highly precise, low 

noise pointing and tracking system. 

C. IMAGE VELOCITY SENSOR 

The Image Velocity Sensors in the DORIAN optical assembly as discussed 

in Appendix D were developed to provide an automatic rate killing input to 

the tracking system. At termination, developments by two manufacturers 

were judged equally capable of meeting the specified rate limit. This 

development, while representing a relatively modest portion of the program 

cost, proved to be one of the most trying technical undertakings in the 

entire effort. The technology developed has extensive application in 

bombing/navigation systems, missile homing system, aircraft reconnaissance 

systems and numerous other activities requiring precise identification/ 

recognition characteristics. 

Tracking systems for ground based optical or high powered laser tracking 

systems are particularly in need of such a device. Coupled with active 

vibration isolation systems, image velocity sensor systems could improve 

long-range, aircraft-based, oblique photography resolution by a factor 

of two to four. 

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Even if all other technical problems can be solved, practical laser 

weapons systems will require these velocity sensing, and pointing and 

tracking technologies. Appropriate steps should be taken to apprise a 

few selected individuals at the Air Force Weapons Laboratory of these 

technologies. 

The image velocity sensors and test equipment technology should be 

considered by the Air Force Avionics Laboratory (AFAL) for possible manned 

aircraft applications. In particular the AFAL Dynamic Analysis Facility has 

an urgent need for test equipment to evaluate existing image velocity 

sensors which are now used in special access intelligence collection systems. 

It is recommended that these Air Force Laboratories study the equipment 

technology. The hardware is not available for transfer. 

D. BIMAT ON-BOARD FILM PROCESSOR 

One of the current national reconnaissance and surveillance problems 

concerns near real time access, display and reaction. The Bimat on-board 

film processor as described in Appendix E might be an extremely useful 

piece of equipment on certain large aircraft. The processor might be 

transferred to AFAL for test and evaluation. AFAL investigation and 

recommendations in this regard are solicited. 

E. VISUAL DISPLAY PROJECTOR 

The Visual Display Projector system as described in Appendix F might be 

modified to augment current reconnaissance and intelligence data management 

devices for both airborne and ground based systems and could complement the 

Automatic Data Handling System. It also has potential application in NASA 

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manned spaceflight programs for crew information storage and retrieval, 

flight plan display, maintenance procedure display and recreation. Proposals 

for its application should be solicited. 

F. OPTICAL INSTRUMENTATION AND MOL EQUIPMENT 

In many instances, equipment in this category developed for MOL has 

direct application to other optical reconnaissance systems and should be 

so employed. However, much of this instrumentation and equipment can also 

be used on the AFAL Dynamic Analysis Facility or in the AFAL Optical 

Science Laboratory in conjunction with their 100 inch collimator. 

G. ACQUISITION AND TRACKING SCOPE AND MISSION SIMULATOR 

A number of suggestions for useful application of the Acquisition and 

Tracking Scope (ATS) described in Appendix G, the Mission Development Simulator described in Appendix H. and related equipment, software and 

documentation have resulted from the Group's review. The deliberations 

have included NASA use of the ATS as an experiment designed to measure the 

manned contribution to a pointing and tracking capability. Such an experiment, 

which could be part of the Earth Resources Program, would also anticipate 

use of the simulator for training and experiment development. There have 

also been suggestions that this equipment be considered for its applicability 

to aircraft reconnaissance photography and related training. 

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The simulator consists of a control console similar to the flight 

unit located in the 14)L experiment module, a tracking telescope with the 

associated slide projector to simulate scenes as seen from space, a cue 

display on the console, together with the associated monitoring equipments, 

computers and software. One simulator was essentially completed at the GE 

Valley Forge facility. 

The Air Force is vitally interested in the study of the man-machine 

interface but, at present, specific programs which can effectively and 

economically use the ATS or simulator have not been identified. Neither 

has NASA any missions where this unique man-machine interface has a direct 

application. 

The astronomy missions in Apollo Applications Program (AAP) have a 

somewhat similar man-machine interface, with similar precision required for alignment, focusing, pointing, and operating, but without the continuing rapid 

sequences and judgment requirements that are associated with multiple moving 

targets passing under the spacecraft. The Earth Resources observation 

experiments envisaged for AAP, and later manned missions, may require 

equipments similar to the ATS, but the precision required is thought to 

be far less rigorous. 

Although there appears to be no obvious direct application of the ATS 

in the NASA AAP, a good conceptual understanding of the ATS and the simulator 

would provide insight in identifying and articulating the role man can or 

should play in spaceflight. 

There are several subsystems or elements of the ATS and the simulator 

that merit more detailed review by NASA and AFAL personnel. 

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1. The slide projector that simulated the ground scene as viewed 

through the ATS optics may have application in NASA simulators or in 

intelligence system training devices. 

2. The cue display and the associated 16 mm film strip system 

may have application in AAP for simulations, conducting experiments, flight 

operations, or in-flight recreation. It may also have application in 

intelligence system data management. 

3. The technology acquired in defining and developing the 

interface between man and optical system (ATS) would appear to be of value 

to any APP project or experiment involving man and optical devices. 

A visit by suitably cleared NASA and AFAL personnel to the GE facility 

to obtain thorough briefings on the ATS, and the ATS simulator, will 

establish what interest there is in continuing any of the ATS related 

developments in technology, hardware, software or facilities. 

Possible Air Force (AFAL) interest in some components of these items 

has been indicated earlier in this annex. 

H. ARMS CONTROL OPTION 

The up-coming arms control negotiations with the USSR may produce 

a situation wherein the U.S. would want to elect whether or not to exercise 

an inspection option. Such an inspection option might be comprised of the 

ATS with suitable recording equipment flown in an available manned space 

vehicle. Exercise of the option would entail over-flying the USSR to 

observe, perhaps openly, arms control or disarmament violations. 

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Should an open skies, above, say 50 miles, agreement result as part 

of a treaty with the USSR, the ATS might prove to be the quickest and 

least expensive way to exercise the right. 

If the suggestions cited above prove to be of no value in bargaining 

with the Soviet Union, the only cost is bonded storage of the equipment 

until that determination is in hand. Routine disposition could then follow. 

Retaining the equipment in storage for the present appears reasonable 

as there is as yet no firm requirement for the ATS or the Mission Simulator 

in other programs. 

I. ASTRONOMY APPLICATION OF MOL/DORIAN OPTICS ASSEMBLY 

In connection with the disposition of MOL hardware and technology, 

the Administrator of NASA posed a question regarding the applicability of 

the main optics assembly to astronomy missions. A cursory briefing on the 

subject was prepared and is summarized here. 

To apply the DORIAN main optics as a stellar or solar telescope would 

require some fairly extensive modifications. These, however, would consist 

mainly of removing the tracking mirror assembly, the Ross Barrel and folding 

mirror and some of the forward section of the mission module. To then adapt 

the remaining mirror and optical barrel to a vehicle such as the NASA 

workshop or some other vehicle would require rather significant structural, 

pointing controls and environmental control development. A wide band-multispectral recording system would also need to be developed. 

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The performance of such an adaptation in relatively low earth orbit 

is estimated in the attached figures. Depending upon the capability of 

the recording device selected, resolution improvements of between 3 and 4 

times over the best earth-based observatory appear possible. 

Since the main optics system in MOL was not to be considered by the 

Ad Hoc Group for disposition, this discussion is included only for record. 

J. CONCLUSIONS 

Most of the classified NAL equipment that was considered for disposition 

requires further analysis prior to a decision. This is borne out by the 

absence of concrete, detailed proposals for direct application of the 

equipment. Consequently, further study by those interested agencies prior 

to making a firm proposal has been recommended. Such studies should be 

possible within the appropriate security system and initiating action has 

been taken. Responses from agencies indicated should be delivered to 

the Secretary of the Air Force by September 1, 1969. As a matter of 

record, the contractors' briefings are included in Appendix I. 

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OFFICE OF THE SECRETARY 

DEPARTMENT OF THE AIR FORCE 

WASHINGTON 20330 

June 30, 1969 

MEMORANDUM FOR MR. HANSEN, SAFRD 

Although I am aware of various efforts underway in 

the MOL Program and Systems Offices, the Air Staff, and 

NASA aimed at exploiting MOL residuals and/or carrying-on 

essential work, I nevertheless feel that a more formal, 

comprehensive review should also be undertaken to insure 

that maximum national benefit is realized from MOL hardware, technology, and experience. 

What I have in mind is an Ad Hoc Group of appropriate 

individuals to accomplish the following: 

o Identify all significant MOL hardware, test 

and checkout equipment, technology, etc., which might be 

useful to DOD and/or NASA. Review MOL Program/System Office 

disposition actions and plans in this regard and provide any 

necessary additional guidance. 

o Identify any essential MOL work which must be 

continued in other AF projects. Review actions already 

taken, underway, or planned and provide any necessary 

guidance or direction to the appropriate AF agency. 

o- Identify desirable MOL technology which might 

be continued as follow-on Exploratory or Advanced. Development 

projects, and provide any necessary guidance or direction to 

the appropriate AF agency. 

o Prepare a report on all of the above as of 

August 1. 

For composition of the Ad Hoc Group, I suggest. 

Dr. Yarymovych as Chairman, with General Hedrick, %,,aneral 

Gilbert, and appropriate representatives from MOL and SAMSO 

as members. Additionally, consideration should be given to 

DORIAN 

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the inclusion of NASA and DDR&E representatives as members of 

the group; as a minimum, an early and continuing liaison should 

be established with those agencies. 

Although those elements of the DORIAN camera system that 

are applicable to an unmanned system and in the process of 

transfer to the National Reconnaissance Program are excluded 

from this review, the Ad Hoc Group should consider all man-unique 

aspects of the MOL camera system regardless of classification. 

To facilitate its use, the report of the Ad Hoc Group 

should be a non-BYEMAN document and make no inference of any 

such material. BYEMAN-classified aspects of the MOL Program 

dealt with by the Group should be covered in a supplementary 

annex to the basic document. 

Attached for your use, as appropriate, is an unclassified 

version of this memorandum. 

ROBERT C. SEAMANS Jr. 

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APPENDIX B 

COMMITTEE MEMBERS 

AND 

CLASSIFIED MINUTES 

DORIAI 

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MEMBERS AD HOC GROUP TO REVIEW MOL RESIDUALS 

Dr. Michael I. Yarymovych - SAFRD - Chairman 

Brig. Gen. Raymond A. Gilbert - AFSC/SCT 

Brig. Gen. Walter R. Hedrick, Jr. - AFRDS/Col. Raymond Nelsen 

Brig. Gen. Louis L. Wilson - SAMSO 

Mr. Howeard P. Barfield - DDR&E 

Mr. Samuel H. Hubbard - SAFSL 

Col. Stanley C. White - SAFSL 

Lt. Col. Clements B. Merritt - SAFSL 

Lt. Col. Larry Skantze - SAFSL-6 

Lt. Col. Donald L. Steelman - SAFSL 

Mr. William C. Schneider - NASA 

Mr. Philip E. Culbertson - NASA 

Mr. Myron W. Krueger - NASA 

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CLASSIFIED ADDENDUM 

TO JULY 1, 1969, MEETING OF 

THE AD HOC GROUP TO REVIEW MOL RESIDUALS 

Reference is made to the unclassified minutes of the first meeting. 

Following are classified areas discussed in the meeting. 

1. There will be two reports - one will be a Byeman/DORIAN 

classified discussing those areas requiring this classification. The 

other report will be in the white - classified no higher than SECRET 

and it will not refer to the black documents in any way. 

2. The DORIAN classified equipment can be reviewed and if the 

use was justifiable, the possibility of downgrading it would be considered. 

3. The optical system and the Eastman Kodak facilities will 

not be discussed. 

4. Attendees at the meeting were: 

Dr. Michael I. Yarymovych - SAFRD - Chairman 

Maj. Gen. James T. Stewart - SAFSL 

Brig. Gen. Raymond A. Gilbert - AFSC/SCT 

Brig. Gen. Louis L. Wilson - SAMSO 

Col. Raymond Z. Nelsen - Alternate for Gen Hedrick - AFRDS 

Col. Stanley C. White - SAFSL 

Capt. Robert Geiger - SAFSS 

Mr. Samuel H. Hubbard - SAFSL 

Lt. Col. Larry Skantze - SAFSL-6 

Lt. Col. Donald L. Steelman - SAFSL 

Mr. William C. Schneider - NASA 

Mr. Howard P. Barfield - DDR&E 

Mr. Philip E. Culbertson - NASA 

Mr. Myron W. Krueger - NASA 
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ADDENDUM TO 10-11 JULY MEETING OF 

AD HOC GROUP TO REVIEW MOL RESIDUALS 

Reference is made to the minutes of subject meeting. Following are 

specific areas discussed which must be separated because of security 

classification. 

a. Bi Matt Processor 

The technology of bi-matt processing is available in Air Force 

Laboratory in unclassified versions. If required, it can be obtained. 

Also, the Air Force laboratories are continuing to work on the bi-matt 

processing technology. The processor should not be mentioned in the 

non-Byeman report thereby disassociating it with MOL. 

NASA indicated that they may consider on-board processing in 

follow-on (second generation) AAP for stellar application. An engineering 

unit is available at Eastman Kodak (EK) if they desire to review its 

operation. 

It was suggested that the unit remain in storage at EK for a 

period of time and processor technology be followed through the Air Force 

Labs. 

General Gilbert will write a short paragraph on the processor 

for the black supplement. 

b. Acquisition & Tracking Scope (ATS) 

NASA expressed an interest in the possibility of using it, or 

a version thereof, for earth resources and possibly lunar activity. Other 

uses are being investigated. Aerospace Corp. made studies and reports on 

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use and capability of the ATS and these can be obtained if required. 

A short paragraph on ATS will be provided by Mr. Schneider for 

space applications and General Gilbert will review for possible SR-71 

use. 

c. Image Velocity Sensor (IVS) 

The Chairman stated that the IVS was not in perview of group 

and the fallout of IVS is applicable and being considered for other 

programs. 

d. Startracker 

Accuracy requirement is all that is new. 

e. Low G Accelerator 

Off-the-shelf type item. 

f. Drive Subsystem (bearings) 

Advanced technology provided low-speed smooth operation. Present 

bearing techniques were used and "honed" or improved to obtain smooth 

operation. 

Other areas associated with the camera system, i.e., optics and special 

contractor facilities, were excluded from the scope of the review group 

per direction of Dr. Seamans. 

_ . 

DONALD L. STEELiAN 

Lt. Colonel, USAF 

SAFSLS 

-77■ 14.1 

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APPENDIX C 

TRACKING MIRROR CONTROL SYSTEM 
+42Arad/sec within .64-4. N where N is 4 under IVS control and 5 under 

6 

crew rate nulling. In addition at N equal to 3 sec the line of sight 

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TRACKING MIRROR CONTROL SYSTEM 

FUNCTION 

To drive and control the Tracking Mirror (i.e., LOS) at prescribed 

rates and null accuracies. 

TECHNICAL DESCRIPTION 

Point and maintain during operation the optical line'of sight within 

a cone of half angle .1 degree. 

Slew and settle to the above pointing accuracy and a rate accuracy of 

rate accuracy must be less than +5110Aradisec for open loop performance. 

Components included are: 

Pitch and Roll Torquers 

Pitch and Roll Gyro's 

Drive Electronics 

Super Smooth Bearings (Pitch & Roll) 

Shaft Position Encoder 

Bearing Lubricant (F-50) 

STATUS 

Analysis and brass and bread board test results have shown the drive 

system, assuming an operable IVS, to meet or exceed specification. Studies 

have shown the open loop performance to be on the order of 100,4rad/sec. 

The drive loop responded properly to IVS feed-back signals. The IVS 

component is covered separately. One minor problem area was the pointing 

accuracy, worst case IVS operation allowed the pointing accuracy to drift out 

of specification. 

% COMPLETE 40%- TOTAL PROGRAM COST TO COMPLETE $9M 1st Unit 

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APPENDIX D 

IMAGE VELOCITY SENSOR (IVS) 

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IMAGE VELOCITY SENSOR (IVS) 

FUNCTION 

The IVS optically senses the velocity of image in two axes and provides 

the information to the Tracking Mirror control loop to null the image rate. 

TECHNICAL DESCRIPTION 

The IVS input is the center 2.8 inches of the overall 9-inch scene. 

The IVS senses primarily in the visual (.4 - .9 millimicrons) range. 

The IVS outputs: 

(1) an x and y signal in analog form indicative of x and y velocity 

in the range of + 0-600 radians/sec or + 0-.3 inches/sec at the image 

plane. 

(2) a digital signal for each velocity channel indicating a 

lock-on status. 

(3) 'a digital signal indicating operational readiness of unit 

to meet spec. 

••• 

(4) a digital signal indicative of the status of the input energy. 

STATUS 

This component was subcontracted to two vendors. At termination these 

two units were undergoing competitive testing to determine which vendor 

would supply the flight models. Both vendors,had problems under adverse 

input scene conditions; however, the Systems-Office is confident that with 

further development either vendor could supply working units that would 

meet the specification. 

% COMPLETE TO% - TOTAL PROGRAM COST TO COMPLETE $2.1M 1st Flt Unit 

80% Complete- 41J4 * of Llazcpages 

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IMAGE VELOCITY SENSOR (IVS) TESTER 

FUNCTION 

To provide the tester for the IVS test program. 

TECHNICAL DESCRIPTION 

Simulates the orbital conditions with known pictures to simulate 

scene. 

STATUS 

Complete except for modifications to haze control to better control 

the input light levels. 

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MOL Segment 

PHOTOGRAPHIC SEGMENT EK 

Subcontract/Subcontractor 

Processor (negotiated) EK 70% 

MISSION PAYLOAD (negotiated) GE 

Subcontract/Subcontractor 

Acquisition Track Scope/ITEK 60% 

Image Velocity Sensor Goodyear* 95% 

Hycon* 95% 

*Goodyear and Hycon were developing in separate prototypes. Figures are 

based on those prototypes only. 

Completion 

Prime Contractor Status (Percent) 
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APPENDIX F 

VISUAL DISPLAY PROJECTOR 

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VISUAL DISPLAY PROJECTOR 

FUNCTION 

The visual display projector presents to the crewmen high resolution 

pictues of the scene prior to the target pass which aids in locating targets 

in the acquisition tracking scope field-of-view. A secondary function 

is to provide maintenance or instructional material to the crew. 

TECHNICAL DESCRIPTION 

The visual display projector has the capability of displaying any cue 

frame in a cue frame library of 32,752 frames. The frames are stored in 

eight film modules, each containing 4,094 frames. Each frame is identified 

by a binary code which is printed on the film. 

During target pass operations, cues are called up by airborne digital 

computer commands. Each cue frame called up is held for a fixed duration 

and then released to permit the visual display projector to retrieve the next 

cue. The operation is planned so that a cue is being retrieved during the 

periods when the crewman is viewing a scene in the acquisition tracking 

scope. The cue is displayed during the slew period (perhaps with some overlap` 

into the track period). The cue is released automatically if the crew votes 

on the target while it is still being displayed. The crew can retain a cue 

frame beyond the planned release time by rotating the magnification control 

stick in a clockwise direction. 

During prepass briefing periods, the airborne digital computer 

automatically commands each frame retrieval as in the target pass operation. 

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However, cues can also be called up and released manuplly by operating 

the manual controls located on the visual display control panel. Cue 

frames are called up manually by dialing the desired frame number, in 

octal form, on the manual selector control. 

A six-character alpha-numeric display is included on the visual 

display projector to project cue words relating to each target. This 

information is stored in the airborne digital computer. 

STATUS 

The design is 85% complete and the first unit is 40%. 

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APPENDIX G 

ACQUISITION TRACKING SCOPE 

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ACQUISITION TRACKING SCOPE 

The acquisition telescopes function was to permit the crewman to view' 

ground targets. 

TECHNICAL DESCRIPTION: 

The resolving power of the acquisition optics shall be high enough to 

enable an observer with vision of AFM 160-1 Flying Class I to resolve a 

3-bar target of alternating 1.65 feet wide white and black bars. The 

real FOV shall be at least 4.0° at minimum magnification and at least 1° 

at one-half maximum magnification. The minimum magnification shall be 

16x+2x; the maximum magnification shall be 127x+5x-3x. The slew capability 

of the ATS scanner shall be : T LSO. „ where AO is the line-of-sight 0 3

angle (in degrees) between the current target and the subsequent target 

at the start of slew. 

STATUS OF HARDWARE/TECHNOLOGY: 

1. ATS Drive Electronics: Detailed drawings for the modules comprising 

the drive electronics were 80% released. Engineering units of many of the ` 

modules had been fabricated and tested, but not as a complete subsystem. 

2. ATS Scanner: The scanner mechanical design was 80-90% complete. 

The engineering model was in fabrication and near completion. 

3. Telescope: Optical design was complete in 1967. Optical bench 

tests completed in May 1969 had confirmed the design (at least on-axis 

performance). Internal mechanism designs, power changer, zoom, were quite 

crude and would have required extensive redesign. 

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While much detailed design has been completed on the ATS, many aspects 

of the design had not satisfactorily completed PDR. These items are 

specifically: 

A. Thermal Design 

B. Sun Shutter 

C. Installation Alignment 

D. Internal Telescope Mechanisms. 

ESTIMATE TO COMPLETE 

Cost to complete design, development, qualification, acceptance 

testing of one Acquisition Tracking Scope would be approximately 0.50 

Million (just for the telescope). This task is ,f.--t:IBCO complete. The 

complete subsystem; i.e., gyros; shaft position encoders, etc; would be 

4.0 Million. This task is 1....r.60% complete. -

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APPENDIX H 

SIMULATION PRuGRAM 

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simurATroN 

Technical description and status of MOL Mission Module Simulation 

Activities: 

The purpose of the Mission Module Simulation Program was to develop and 

validate MOL payload operating concepts, timelines, and procedures; to 

develop and validate flight computer programs; and to train the flight 

crew and flight controllers. Three simulators were planned to meet these 

objectives, as follows: 

a. Elemental Development Simulator (EDS). This simulator was operated 

during 1968, primarily for validation of cockpit configuration. The optical displays were driven by 70 mm motion picture projectors. Optical 

quality was of marginal quality to perform advanced flight crew simulations. 

The EDS completed operation and was dismantled in September 1968. 

b. Mission Development Simulator (MDS). 

(1) This simulator is a modified and improved version of-the EDS. 

Located at the GE plant in Valley Forge, it was to continue the engineering 

development and mission validation tasks. The optical displays of the ATS 

and visual optics are provided by a series of slide viewing subsystems 

(SVS) which projected images from 9-inch square glass slides. The images 

are modified by zoom lenses, anamorphic lenses, and derotation prisms to 

provide to the flight crewman scenes of the earth as seen through his displays from the spacecraft. All operating controls and displays are 

simulated to allow realistic target acquisition, weather avoidance, 

intelligence activity detection, rate nulling, and tracking, as well as 

contingency mode operation. The MDS contained a computer complex consisting of an IBM 360-44 digital computer, a SAS/Beckman 930/2200 hybrid 

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Addendum 1 to the NASA. Report for Simulation 

STATUS OF SIMULATION PROGRAM 

1. Elemental Development Simulator (IDS). The EDS completed operation in 

September 1968 and has been torn down. 

2. Mission Development Simulator (MEG). The Phase Zero configuration MDS 

(single cockpit) was scheduled for operation July 1969 and was, therefore, 

virtually complete. The final Phase 3 configuration MDS, complete with 

five slide viewing subsystems, Airborne Digital Computer and both crew stations, 

was scheduled for initial operation during early 1970. Hardware fabrication 

was essentially complete, but approximately 50% of the computer software 

remains to be developed. 

3. Mission Module Simulation Equipment (MMSE). The MMSE design was to be 

patterned- after the Phase 3 MDS. The MMSE was in the early design stage, 

and virtually no fabrication had been accomplished. 

ESTIMATED COST TO COMPLETE PHASE 0 

AS DESCRIBED IN PARAGRAPH 2 ABOVE 

It is estimated that approximately $250,000 and 6 to 10 weeks of time 

would be required to bring the Phase 0 MDS to full operational status. 

It could then be operated for a coat of about $1.5 Million per year. 

Phase 0 was approximately 95% complete. 

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computer, and an actual IBM 4 pi flight computer) containing airborne 

software. An instructor/operator station, which includes television 

monitors of flight crew visual displays, is also included, as well as 

all necessary power conditioning and signal conditioning and switching 

equipment. 

(2) The initial single cockpit phase of the MDS was due to be 

completed in July 1969. The final two-crewman configuration was 

scheduled for completion during early 1970. 

c. Mission' Module Simulation Equipment (MMSE). This simulator was 

to be used at Vandenberg AFB for training. It was similar in configuration to the MDS, except it was designed to interface with the MDAC 

furnished Laboratory Module Simulation Equipment for integrated orbiting 

vehicle training. The MMSE was in the early design stage. 

2 

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APPENDIX I 

CONTRACTORS • BRIEFINGS 

DOMAN 

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On 24 July 1969 the General Electric Company recommended several 

actions to the MOL Disposition Board to assist that Board in applying 

MOL hardware experience and technology to other Government programs. 

This paper summarizes the classified portion of this presentation 

and the major recommendations. 

3 

1. The Acquisition Telescope System is a high 

performance system combining high quality optics 

with precise pointing capability. The system 

includes the telescope pointing, zoom, and derotation servos and the computer subsystem necessary 

to drive the servos. 

The potential applications of the Acquisition 

Subsystem have been identified for Apollo and the 

Apollo Applications Program as an experiment in: 

lunar site determinations, surface observations or 

record from lunar orbit, earth resources observation and record, adjunct to stellar, solar and 

planetary astronomy, ocean 

surveillance. 

General Electric recommends clearances for a 

limited number of NASA people and a funded study, 

supported by NASA and DoD, for the definition of 

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an unclassified experimental flight program using 

the Acquisition Telescope Subsystem. 

2. The MOL Mission Development Simulator has been 

completed to the extent of providing an operating 

capability for a single crewman with high quality 

flexible optics and controls which permit quantitative 

determinations of performance by man and equipment in 

electro-optical and command/control systems. In 

addition to direct eye piece observation, the 

Simulator has a video pick-up which is used as an 

input to a Video Console Simulator. The Video 

Console Simulator is currently being used to study 

command/control and read-out aspects of an unmanned 

direct read-out reconnaissance satellite system. 

Potential applications, manned or read-out, 

include Apollo Telescope Mount simulation; landmark positioning and associated studies of 

autonomous navigation; earth resources perform.ance 

evaluation; reconnaissance, surveillance, target 

location control and bandwidth studies; ocean 

surveillance studies and ASW studies; 

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General Electric recommends continued USAF space 

and aircraft investigations in the simulator. General 

Electric also recommends clearance for appropriate NASA 

people on the earth resources and ATM programs with 

funded operation of the simulator during an experimental 

investigation to determine the applicability of the 

simulator to these programs and the NASA interests. 

1' NpAr 

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14a MN 

3. The MOL Program developed an integrated software capability at General Electric with unique 

capabilities to produce and integrate both space 

borne and ground control and telemetry reducing 

software. .The control philosophy of MOL was 

different from that of other manned space programs 

in that the system was organized to interface man 

with the on-board computer in such a manner as to 

relieve man of routine tasks and optimize his 

capability to exercise judgment and discrimination 

in mission performance. The future NASA missions 

in Apollo applications and space station are in 

this direction and, in this instance, approximate 

those of MOL. The application of the control 

philosophy developed in MOL can be a significant 

economy to NASA. 

/-- 

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. General Electric recommends that a limited 

number of NASA personnel be cleared in order that 

the applicability and value of this software 

experience and philosophy missions can be determined and transferred to NASA. 

4. General Electric recommended potential 

applications of the Image Velocity Sensor in 

automatic, precise, optical tracking of targets - 

terrestrial, lunar, planetary, satellite or booster 

during powered flight. It recommended potential 

applications of the attitude reference system .for 

autonomous navigation in space flight when ground 

tracking is not available or not sufficiently 

accurate, and in any other application where precise, automatic pointing of optical sensors, lasers, 

communication antennas or radar antennas is required. 

It recommended applications of the gimbal drive 

system, or the technology, wherever ultra precise 

control along with rapid and smooth target tracking 

is required for optical sensors, radar and communication antennas or lasers. In this last category, 

General Electric specifically recommends that USAF 

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study funding be expended to transfer this technology to aircraft or weapons applications. 

5. General Electric recommended the following 

administrative actions be approved at the earliest 

opportunity: 

a) Relief from provisions of message 

2117 to permit free discussion and application activity on all MOL technology, 

experience, and hardware except that 

protected by Dorian classification. 

b) Approval to contact Dorian cleared 

government officials to discuss applications without specific prior approval. 

c) Approval to use the simulator, IVS tester 

and other equipment to demonstrate MOL 

technology and hardware. 

d) Approval to propose use of MOL hardware 

and equipment as GFE. 

e) Retention of MOL simulator, IVS tester 

and computers with peripheral equipment by 

excluding from mandatory screening and 

inventory procedures under termination 

pending definition of applications. 

GYEMAN 

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0 Agreement to grant limited number of Dorian 

clearances to individuals as identified by 

NASA members of the Board and as necessary 

to develop the applications. 

In our judgment, the program we have recommended will realize the 

most immediate utilization of paid-for hardware and technology in other 

programs. It can quantify and upgrade, or accelerate, man's role in the 

NASA manned spacecraft programs. It can serve as a continuing and effective research tool in the investigation of advanced manned military space 

systems which may be undertaken in apace by ourselves or others. 

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