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2 7 OCT 1989 411111111- 

NOFORN 

-FOR-REAH3f-OtittrPRELIMINARY 

TECHNICAL DEVELOPMENT PLAN 

FOR THE 

MANNED ORBITING LABORATORY 

1111111111111111" 

MICROFILMED BY TIM 

APRIL 1964 

Status 

as of 

30 JUNE 1964 

r;i:,":',,j1 C.] 3‘..-ae-A-994 

• 

SPECIAL HANDLING REQUIRED 

NOT RELEASABLE TO FOREIGN NATIONALS 

The information contained In this document will 

not be disclosed to foreign nations or their regret 

'tentative' 

C."-• 

HEADQUARTERS 111111.111111111 0 tr,•\ 

SPACE SYSTEMS DIVISION 

AIR FORCE SYSTEMS COMMAND t11 c).1 

UNITED STATES AIR FORCE 

al. CONFIDENTIAL SSM-50A ***'■ 

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NOT AUTOMATICALLY DECLASSIFIED 

DOD DIR 5200.10 1:10 I 

••k 
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2 7 OCT 1989 

This edition has been prepared to correct and to update 

the April 1964 MOL Program PTDP to reflect program 

activities and planning as of 30 June 1964. 

NOFORN 

vaimF. CONFIDENTIAL SSM-50A 

(This page is Unclassified) 

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FOREWORD 

This Preliminary Technical Development Plan (PTDP) is addressed 

primarily to the in-house and contractual activity planned for the PrePhase I time period. The Pre-Phase I period will be devoted to two 

areas of activity. 

First, the experiments to be conducted during the initial MOL flight 

program will be defined with sufficient precision and detail to reveal 

how a technically successful MOL Program will determine the usefulness of man as an element of possible future military space systems. 

This definition will precede 'selection of a Laboratory Vehicle contractor and initiation of Phase I. 

Second, vehicle systems, subsystems, and interface alternatives 

will be studied to reduce to a practical minimum the technical questions 

remaining to be resolved during the Phase I period when the Laboratory 

Vehicle contractor and all other associate contractors will be engaged 

in detailed definition of the MOL Phase II program. 

A revised version of the MOL PTDP will be submitted at the 

conclusion of the Pre-Phase I effort. This revised PTDP will describe 

the Phase I program in a more explicit and detailed fashion and will 

include a plan for the Project Definition Phase (PDP). The Phase I 

Project Definition Phase is presumed to begin after approval to proceed with Phase I is received, and proposals are requested from 

industry for definition and development of the Laboratory Vehicle, 

the only new vehicular element of the Manned Orbiting Laboratory 

System. 

WILLIAM D. BRArH•Y ------. 

Colonel, USAF 

System Program Director, MOL 

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Brig Gen, USA 

Deputy Commander for 

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SSM- 50A 

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TABLE OF CONTENTS 

Section Page 

* 1 PROGRAM SUMMARY 1-1 

* 2 SCHEDULES 2-1 

* 3 PROGRAM MANAGEMENT 3-1 

4 INTELLIGENCE ESTIMATE 4-1 

5 OPERATIONS 5-1 

* 6 ACQUISITION 6-1 

7 CIVIL ENGINEERING 7-1 

8 LOGISTICS 8-1 

9 MANPOWER AND ORGANIZATION 9-1 

10 PERSONNEL TRAINING 10-1 

* 11 FINANCIAL 11-1 

12 REQUIREMENTS 12-1 

13 AUTHORIZATIONS 13-1 

14 GENERAL INFORMATION 14-1 

15 SECURITY 15-1 

16 BIOMEDICAL 16-1 

* 17 PRELIMINARY DEFINITION PLAN 17-1 

* 18 US NAVY EXPERIMENTS 18-1 

19 NASA EXPERIMENTS 19-1 

20 SECONDARY EXPERIMENTS 20-1 

* Indicates the sections included within this PTDP. The other sections are 

merely added in tabular form for continuity to conform to the PSPP outline 

which will be formulated during Phase I. 

-SECRET- SSM-50A 

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-SEMINDEX 

SECTION 1 

PROGRAM SUMMARY 

Page 

1.0 INTRODUCTION 1-1 

1.1 PROGRAM OBJECTIVES 1-2 

1.2 BRIEF SYSTEM DESCRIPTION 1-2 

1.3 EXPERIMENTS 1-3 

1.4 PROGRAM DEVELOPMENT SUMMARY 1-5 

1.4.1 General 1-5 

1.4.2 Pre-Phase I 1-5 

1.4.3 Phase I 1-5 

1.4.4 Phase II 1-6 

Ij 

1.4.5 Graphic Presentation of Action Schedules and Networks . . . • 1-7 

•

1.4.6 Preliminary Cost Estimates 1-7 

I 

1.5 MAJOR MILESTONE SUMMARY 1-7 

--SECRET- SSM-50A 

1-1/11 

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SECTION 1 

PROGRAM SUMMARY 

1.0 INTRODUCTION, 

The Director of Defense Research and Engineering Memorandum to 

the Assistant Secretary of the Air Force (R&D), subject "Manned Orbital 

Program," dated 11 Dec 1963 announced that a Military Manned Orbital Program had been approved by the Secretary of Defense and that the program 

has been assigned to the Air Force. During 3-7 January 1964 the Space 

Systems Division of AFSC presented to Hq USAF, the Assistant Secretary of 

the Air Force, and the Deputy Director of Defense Research and Engineering/ 

Space a preliminary Air Force approach for implementing the MOL program. 

This presentation outlined in general terms the objectives of the program, 

an approach toward selecting equipments and defining the configurations of 

the Orbital vehicle, and a concept for the management of the MOL program. 

This Preliminary Technical Development Plan (PTDP) responds to 

instructions from Hq AFSC contained in Secret Msg, MSF 9-3-13. It has 

been prepared to present a specific plan for initiating the Manned Orbiting 

Laboratory program. It consists of detailed information on the Pre-Project 

Definition Phase (Pre-Phase I), planning information for a Project Definition 

Phase (Phase I), and a System Acquisition Phase (Phase II). Primarily, 

this plan has been prepared to indicate the management and contractor 

structure for the program, the roles and responsibilities of the participating 

organizations, and the schedule and decision networks and funding required 

for the early phases of the program. Particular emphasis has been placed 

on the process of completing the selection of experiments to meet the primary objective of the MOL program. Detailed schedules and costing for the 

total program will be generated during the Phase I. In preparing this PTDP 

an earnest effort has been made to conform to the provisions of AFSCM 

375-4. 

-8EGREfSSM-50A 

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1. 1 PROGRAM OBJECTIVES. 

The primary objective of the MOL program is to provide an in-space 

testing capability which will qualitatively and quantitatively assess the military usefulness of man in space. 

Accomplishment of this objective necessitates defining basic military 

tasks and design experiments that will determine and evaluate man's value in 

the accomplishment of these tasks. The selected experiments will be performed in an orbiting laboratory designed to be launched by the Titan IIIC 

Standard Launch Vehicle using a Gemini B Spacecraft for personnel transport. The objective of the MOL program is not to develop an operational 

manned military system, but to determine if there is sufficient justification 

to develop manned military space systems in the future, and, in the process, 

determine what the role of man should be and how his unique capabilities 

should be integrated into space systems to increase their military 

effectiveness. 

The second objective is to accomplish the primary objective at 

minimum cost in dollars and time and with a maximum of safety. To achieve 

maximum economy, a "bare bones" approach will characterize program definition and conduct. Minimum changes to developed and proven vehicle and 

ground hardware, procedures, and facilities will be the rule in order to take 

full advantage of the accomplishments of prior DOD and NASA programs in 

the interest of safety and reliability as well as minimizing cost and time for 

development and test. 

1.2 BRIEF SYSTEM DESCRIPTION. 

The MOL Vehicle System consists of three principle elem'ents: a 

Titan IIIC launch vehicle, a Laboratory Vehicle, and a Gemini B spacecraft. 

The system concept centers around an Orbiting Vehicle which consists of a 

Laboratory Vehicle, and a Gemini B spacecraft. The Titan III transtage 

may or may not be retained as an element of the Orbiting Vehicle. The 

Orbiting Vehicle is designed to provide a space base for military manned 

orbiting laboratory operation. The Orbiting Vehicle is to be integrally 

SSM- 50A 

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launched by the Titan IIIC. Although resupply and crew rotation by means of 

in-space rendezvous and docking do not figure in the initial flight program, 

the system is to be designed for later incorporation of these capabilities. 

The Laboratory Vehicle will be designed to provide life support for a crew of 

two without resupply for thirty days in order to perform military space 

experiments. Once the mission is complete, or in case of an emergency, 

the crew will return to earth via the Gemini B spacecraft. The Laboratory 

Vehicle may be left in orbit for future use, or it may be destroyed by 

command re-entry if the performance penalties prove tolerable. The 

general characteristics of the MOL System are listed in the following 

paragraphs. 

a. System Characteristics: 

(1) 30 day orbit duration 

(2) 2 man crew 

(3) Integral launch 

(4) Shirt sleeve environment 

(5) Large test and experimental capacity 

(6) Rendezvous, docking, and transfer provisions 

b. Operating Characteristics: 

(1) Atlantic Missile Range Launch 

(2) Low earth orbit 125-250 NM 

(3) Inclination less than 36 . 

1.3 EXPERIMENTS. 

Since the major purpose for developing the MOL is to provide a 

laboratory for evaluating man's potential as an element of a military space 

system through experiments in the true space environment, the accent will 

be on man's performance rather than equipment performance. Therefore, 

maximum ingenuity is being applied to conceive experiments which use 

existing, light, and inexpensive equipment as far as possible to obtain a 

valid measure of what man will do in an operational system. An evaluation 

SECRET SSM-50A 

1-3 

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of aircraft and ground tests will be made for the insight it provides into 

non-space system elements. 

Experiments have been divided into two catagories; primary experiments, which provide measurement of man's utility; and, secondary experiments, which are of technical and scientific importance. 

Efforts are now underway to evaluate the impact of man's performance 

on the design of experimental equipments for use in the MOL. The present 

in-house military studies and the industry Orbital Space Station Study (OSSS) 

results, together with certain supplemental contract studies, will be used 

to identify and define the experiment data to be included in the RFP for the 

Project Definition - Phase I Laboratory Vehicle program. 

The foregoing discussion applies equally to the U. S. Navy Package, 

which is summarized in Section 18* and presented in detail in reference 

(14.1). Owing to the demanding schedule, raw experiment proposals by the 

Navy for MOL were submitted directly to the Air Force Space Systems 

Division as they were generated by the various Navy laboratories. However, 

the Navy, in addition, formed a MOL Technical Panel to review the laboratories' output, to develop a specific program responsive to Navy requirements related to ocean surveillance, and to identify particular experiment 

proposals which were of key interest to the Navy in areas other than that of 

ocean surveillance (e.g. general science). It will be necessary in forthcoming Pre-Phase I studies to establish common hardware performance 

requirements, to refine experiment concepts and missions proposed by the 

Navy, and to correlate current cost estimates and eliminate overlaps. The 

Navy is arranging to participate actively in these studies. 

*The references cited in Section 18 correspond to the list of references 

appearing in reference (14.1) 

SSM-50A 

1-4 

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1.4 PROGRAM PROGRAM DEVELOPMENT SUMMARY. 

1.4.1 General. 

Although many space station configurations have been studied and 

preliminarily designed by industry with government and/or industry funding, 

insufficient information exists today to state specific costs, schedules, and 

specifications for the development of the MOL system. Once the specific 

MOL experiments have been selected, additional analysis and evaluation 

will be required to determine their influence on the MOL system design. 

Therefore, it becomes necessary to conduct a series of Pre-Phase I studies 

in addition to a Phase I and a Phase II program. 

1.4.2 Pre-Phase I. 

During the Pre-Phase I period the OSSS and selected additional 

experiment study contracts will complement in-house efforts in identifying 

MOL experiments and providing sufficient basic technical information on 

experiment packages for the Laboratory Vehicle Phase I Request for Proposal (RFP). Constructive use will be made of this Pre-Phase I interval to 

conduct several other studies which will further solidify MOL planning by 

narrowing the field of vehicle interface questions, permitting more solid 

guidance to be given the Laboratory Vehicle contractor aspirants in the 

Phase I RFP. These include studies to determine the degree to which the 

Apollo, with minimum changes to the NASA configuration, and the one-man 

Gemini on the Titan II Gemini Launch Vehicle can satisfy MOL objectives; 

studies by McDonnell on the Gemini B and by the Martin Company on the 

Titan mc configuration for MOL; and finally, selected contract studies of 

major subsystems of the Laboratory Vehicle to supplement an Aerospace 

in-house concentration on the total systems aspect of the Laboratory Vehicle. 

1.4.3 Phase I. 

This phase of the program will be subdivided into three parts. 

Phase IA begins with approval to release RFPs for the industry Phase IB 

-SEM- SSM-50A 

1-5 

This document contains information olfecting the notionoi defense of the United Stores within the meaning of the Espionage tows 

Title 18. 11. Si C . Section 793 and 794, the trons.won of which to any manner to on unauthorized person is pooh.bded by low 
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Project Definition efforts. Proposal evaluation, contractor selection, and 

award of Phase IB contracts will be completed by the end of Phase IA. 

The Systems Program Office (SPO) organization will be brought up 

to full strength for Phase I. Phase IB will be accomplished by industry 

contractors using an associate contractor structure and firm fixed-price 

contracts. During Phase IB the contractor under SSD/Aerospace guidance 

will provide completely defined proposals and performance specifications 

with detailed schedule estimates of sufficient quality to support maximum 

use of incentive contracts during the Phase II System Acquisition program. 

Phase IB will be a period of concurrent definition of the system, of the 

program for acquiring the system, and preparation of incentive contract 

formulas. Phase IB will not be limited to preliminary design and other 

"paper" effort. Sufficient structures, wind tunnel space environmental, 

and other specialized testing will be accomplished to provide adequate 

confidence in the reliability of the Phase IB product as a foundation for 

Phase II. 

During Phase IC, the final part of Phase I, Phase II cost proposals 

will be obtained and evaluated based on the program defined in Phase IB. 

Negotiation of incentive fee contracts for Phase II will be continued and the 

Phase II Program Plan submitted for approval. Meanwhile, contractors for 

Phase II will be permitted to continue work at a level of effort which will 

assure a running start on Phase II. 

1.4.4 Phase II. 

During Phase II the contractors will provide all engineering, fabrication, testing, and services required to accomplish the MOL program. 

Associate contractor procedures will be used with the Aerospace Corporation performing General Systems Engineering/Technical Direction 

(GSE/TD) for the SPO at the Space Systems Division. Testing during the 

program phase includes all development ground and flight testing, as well 

as MOL Flight Operations for the conduct of the experiments to meet MOL 

program objectives. The detailed management procedures for this phase, 

SSM-50A 

1-6 

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developed during the Phase I program, will employ PERT/Cost and PERT/ 

Time procedures to ensure effective control of the total contractor and 

government efforts on the program. 

1.4.5 Graphic Presentation of Action Schedules and Networks. 

The time-phasing of the events described in the program summary is 

graphically displayed in the Master Program Summary Schedule, The Action 

Schedule, and the individual phase summary charts in Section 2. An action 

network is found in Section 17. 

1.4.6 Preliminary Cost Estimates. 

Preliminary cost estimates are outlined in Section 11. 

1.5 MAJOR MILESTONE SUMMARY. 

A summary of the major milestones in Pre-Phase I, Phase I, and 

Phase II is made in the Action Schedule (Section 2) and the Action Network 

(Section 17). 

-SEGRET- SSM-50A 

1-7/8 

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-SEM 

INDEX 

SECTION 2 

SCHEDULES 

Page 

2.0 INTRODUCTION 2 - 1 

2.1 PRE-PHASE I 2 - 1 

2.2 PHASE I 2 - 1 

2.3 MASTER PROGRAM SUMMARY 

SCHEDULE 2 - 1 

2.4 RELATED FLIGHT TEST SCHEDULE 2 - 1 

2.5 ACTION SCHEDULE 2 - 1 

2.6 SUPPORT AGENCIES 2 - 1 

SSM-50A 

2-i/ii 

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SECTION 2 

SCHEDULES 

2.0 INTRODUCTION. 

This section contains the scheduled milestones, actions, and efforts 

for the Pre-Phase I and the Phase I periods. 

2.1 PRE-PHASE I. 

Figure 2-1 presents the schedule of activities for the Pre-Project 

Definition Phase. It reflects the tasks required to develop the foundation 

for follow-on contractor efforts to define the experiments and vehicle 

program during Phase I. 

2.2 PHASE I. 

Figure 2-2 is self-explanatory. 

2.3 MASTER PROGRAM SUMMARY SCHEDULE. 

Figure 2-3 presents the present schedule for the complete MOL 

program. 

2.4 RELATED FLIGHT TEST SCHEDULE. 

Figure 2-4 depicts the major related NASA and DOD flight programs. 

2.5 ACTION SCHEDULE. 

Figure 2-5 shows the time-phased actions which the various headquarters organizations must take to achieve the schedule displayed on 

earlier schedule charts in this section. 

2.6 SUPPORT AGENCIES. 

Figure 2-6 indicates the laboratory technical and test support which 

will be provided to the MOL program by various agencies. In addition, some 

of these agencies will serve as sponsors of MOL experiments. 

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INDEX 

SECTION 3 

PROGRAM MANAGEMENT 

3.0 INTRODUCTION 

3.1 MANAGEMENT PHILOSOPHY 

3.2 ROLES AND RESPONSIBILITIES 

Page 

3-1 

3-1 

3-4 

3.2. 1 Manned Systems Organization 3-4 

3.2.2 Support Agencies 3-10 

3.2.3 Aerospace Corporation 3-11 

3.2.4 Participating Contractors 3-11 

3.3 PRE-PHASE I, PHASE I & PHASE II 3-14 

3.3.1 Pre-Phase I 3-14 

3.3.2 Project Definition Phase I 3-28 

3.3.3 System Acquisition Phase II 3-33 

3.4 DOD-NASA RELATIONSHIP 3-33 

FIGURES 

Number Title Page 

3-1 Deputy Commander for Manned Systems 3-8 

3-2 MOL Systems Program 'Office 3-9 

3-3 Associate Contractor Structure for Phases I & II 3-34 

SECRET SSM-50A 

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SECTION 3 

PROGRAM MANAGEMENT 

3.0 INTRODUCTION. 

The MOL has been defined in a gross but important sense by the 

decision already made regarding vehicle elements to be used, the employment of state-of-the-art design, and the integral launch mode for initial 

operations. The major problems that lie ahead in the definition and execution of the MOL program are in the area of management to achieve present 

MOL objectives and to provide the potential for continued utility of the MOL 

at minimum cost. 

This section describes the management techniques, the procedures, and the planned management structure for accomplishing the MOL 

program; in addition program responsibilities and specific tasks to be performed by various industrial and government organizations are presented. 

The time-phasing, inter-relationships, and the major decision points concerning these responsibilities and tasks are presented in the schedule networks in Section 17 - Preliminary Definition Plan, and summarized in 

Section 2 (Figure 2-5). 

3.1 MANAGEMENT PHILOSOPHY. 

DOD has assigned the responsibility for conducting the MOL 

program to the Air Force, and the responsibility for developing the operating system has been delegated to the Space Systems Division, where it will 

be directed by a Deputy Commander for Manned Systems (SSH). SSD will 

utilize the GSE/TD capabilities of the Aerospace Corporation and will work 

directly with the appropriate AFSC agencies that will be responsible for 

direct technical and support inputs. In addition, SSD will work closely with 

other agencies within DOD, and with NASA and industry to ensure that technical and management data essential to the MOL program is obtained and 

disseminated. 

SSM- 50A 

3-1 

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The major management problem facing the program is integration. A Laboratory Vehicle contractor will be responsible for the design, 

construction and integration of the Laboratory Vehicle, its sub-systems, the 

mission equipment payloads, and its interfaces with the Gemini B and the 

Titan ILIC launch system. An Orbiting Vehicle contractor (presently planned 

to be the same contractor as the Laboratory Vehicle contractor) will be responsible for the integration, assembly, and checkout of the Orbiting Vehicle 

(the composite of the Laboratory Vehicle, the Gemini B, and the Titan III 

transtage of it is retained in orbit) prior to launch, and for monitoring and 

back-up support during orbital operations. A launch service contractor will 

have primary responsibility for all common support (common to both the 

launch system and the Orbiting Vehicle system), launch integration, countdown, and launch of the integrated system; further, he will be responsible 

for telemetry to the point of injection into orbit. 

The Air Force procurement philosophy of breaking out for direct 

Air Force prime procurement those identifiable components/sub-assemblies 

which are now being subcontracted is the main method of introducing substantial price competition into SSD/R&D type procurement. This philosophy 

will be applied to the extent practicable. The MOL System will be procured 

under the "Associate Contractor" concept using associate contractors for 

the major elements of the system. These participating AF prime contractors will represent the SPO's effort .to adhere to the Policy set forth in AFR 

70-9, "System Procurement". Backing up these AF prime contractors will 

be an array of major component subcontractors and major elements of the 

AF Systems Command. This structure will be responsive to a single management voice, the System Program Director. 

The decision to purchase subsystems or components through 

subcontract versus direct procurement by the Air Force will represent 

deliberate consideration of trade-offs between time, quality, economy and 

the SPO's own internal capability to manage the program. Reviews and 

decisions will be made on an item-by-item basis. Timelineds, quality, and 

economy can be attained by breaking out certain of these items for direct 

purchase whenever possible. 

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The industry contracts during the Pre-Phase I program will be 

sole source only where required, with the major portion being awarded as a 

result of wide technical competition. Source selection procedures will be 

used. During Phase I, the industry contracts will be awarded on a fixedprice basis. For Phase II, the method of contracting selected must satisfy 

the basic requirements for program integrity and unity. Careful consideration is being given to performance as an incentive factor. The objective of 

both the government and contractor should be to give the best possible product. In this vital man-rated program, this objective is paramount, but will 

not be sought at the expense of paying a cost beyond that considered appropriate. In general, the use of incentives effectively exerts pressure on the 

contractor to control cost, adhere to schedules, insure quality design and 

quality control, and generally establish a tightly disciplined operation. 

Therefore, to the maximum extent practical, Phase U will be negotiated on 

a cost plus incentive fee contract (CPIF-P) basis. Procurement planning 

does not envision the use of letter contracts to initiate work for any portion 

of the program. 

Sponsor organizations will be established for each experiment. 

The MOL program office will maintain overall management responsibility 

for all experiment packages. 

Other agencies of the DOD will contribute to the MOL program 

in a number of important respects, although the responsibilities of all of 

these supporting agencies have yet to be completely defined. In addition to 

SSD, other AFSC divisions and the Navy will sponsor DOD experiments. 

Sponsorship includes initiating a requirement, participation in experiment 

definition, and being awarded and accepting responsibility for development 

and acquisition of the experiment hardware according to a defined plan. The 

Phase U experiment program is to be centrally funded as a part of the MOL 

program. DOD sponsors will not be responsible for experiment funding for 

Primary Experiments; secondary experiments will be funded by sponsoring 

agencies and MOL/SPO will act as the integrating agency for them. NASA 

experiments will be funded as well as sponsored by NASA. 

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In addition to sponsoring experiments, other agencies of DOD 

will contribute ground test, training facilities, and technical consultation. 

The Navy will be asked to contribute sea recovery services during the flight 

program. NASA will be asked to contribute the use of NASA Gemini, 

operations resources, technical consultation, and documentation on the 

Gemini spacecraft. 

During the program, proven management techniques such as: 

Configuration Management, Program Evaluation Review Techniques (PERT), 

and Schedule Interface Logs will be used. 

a. Configuration management assures early configuration 

identification and control of changes to the configuration. 

As the acquisition phase of the system progresses toward 

prototype hardware, configuration management will provide 

the means for positive control of the system detailed design. 

The overall configuration management effort will be carried 

out in accordance with AFSCM 375-1 "Configuration 

Management". 

b. PERT Time/Cost applications will be prescribed as a 

management control system for all participating organizations. The PERT/Time/Cost system has proven an 

effective management tool and will be used by the SPO and 

all associate contractors. 

c.. The Schedule Interface Log is an official reference planning 

document for all participating organizations. By use of 

electronic data processing equipment, it provides systematic 

and expeditious mcz,ns for the accour,tability and information 

exchange of the thousands of items which make up the 

schedule interface requirement= or the total program. The 

log maintains and provides descriptive information of specific 

PERT activities. This tool is a primary control and will be 

applied to all participants. 

3.2 ROLES AND RESPONSIBILITIES. 

3.2.1 Manned Systems Organization. 

The Air Force Systems Command, through its Space Systems 

Division, has complete responsibility for management of the MOL program. 

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The SSD organization set up for MOL facilitates central management at the field level. 

a. A Deputy Commander for Manned Systems, SSH, has been 

appointed. (Authorized grade: Brigadier General.) This 

Deputy Commander is delegated full authority for field 

implementation of the MOL program and is authorized direct 

access to streamlined channels established for expedited 

action on Designated Systems Programs and the MOL 

Program. 

b. The Deputy Commander for Manned Systems will have 

complete control of allotted finanical resources, and will 

follow established procedures to assure support of all 

elements of the program. 

c. Field detachments at test sites and factory representatives 

at selected contractors° plants will be established as 

required, and will report directly to the Deputy Commander 

for Manned Systems. 

GI. Military and civilian personnel will be assigned as required 

to implement the approved program. The personnel requirements will be delineated in the PSPP. 

e. Procedures are being developed which stipulate the manner 

in which the MOL Program and its primary elements are to 

be handled by field activities, Headquarters AFSC, and 

higher authority. Pending approval of the special management procedures, the Deputy Commander for Manned 

Systems, is authorized direct access to the Commander, 

SSD, and Commander, AFSC. The.Deputy Commander 

Manned Systems span of command will encompass the 

Manned Orbiting Laboratory and Titan III System Program 

Offices. 

3.2.1.1 MOL SPO Cadre. 

Hq AFSC directed SSD to establish a MOL SPO Cadre on 2 

March 1964. This Cadre has been formed to initiate the Pre-Phase I effort 

and will be the nucleus around which the MOL SPO will grow as management 

requirements dictate. 

SSM-50A 

3-5 

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3.2.1.1.1 Pre-Phase I Responsibilities - The basic responsibilities of the 

SPO Cadre during the Pre-Phase I are: 

a. To prepare a SPO activation plan in accordance with AFSCR 

375-7. 

b. To prepare preliminary integration and implementation 

plans to guide the Pre-Phase I effort. 

c. To manage the Pre-Phase I effort. 

d. To generate those documents that are necessary to acquire 

Phase I approval and to initiate Phase I. 

3.2.1.1.2 SPO Cadre Tasks - The tasks that the SPO Cadre will perform 

during the Pre-PDP are: 

a. Update the Draft PTDP. (The draft PTDP is structured to 

the PSPP, one of the end items of Phase I. All sections are 

added in tabular form for continuity to conform to the PSPP 

outline. This will provide for the continuing orderly updating of the entire package as the Pre-Phase I and the 

Phase I progresses). 

b. Initiate Pre-Phase I study contracts, manage the contractors' 

efforts, and evaluate the study results. 

c. Specify System Performance Requirements and System 

Design Constraints. 

d. Definition of the experiments package. Experiments sponsors and supporting agencies will contribute to this task. 

e. Prepare initial System Performance/Design Requirements 

Specification. 

f. Prepare initial breakdown of Contractor End-Item 

Specifications through 1st Level. 

g. Prepare Phase I Plans and Schedules. 

h. Prepare Preliminary Program Breakdown Structure. 

1. Initiate formation of a Source Selection Board for the 

Laboratory Vehicle Contractor. 

j. Prepare Preliminary Program Management Network. 

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k. Prepare Test Planning Requirements. 

1. Prepare Phase IB Work Statements. 

m. Prepare Phase II Specimen Work Statements. 

n. Prepare Procurement Plan. 

o. Prepare Request for Proposals. 

P. Determine Eligible Contractors. 

Upon approval of the program and receipt of the System 

Definition Directive with funds, the RFPs will be released to industry, thus 

initiating the Phase I. 

3.2.1.2 Formal MOL SPO. 

With the issuance of the System Definition Directive (SDD), the 

SPO Cadre build-up will be completed. The structure of this organization 

is outlined on Figure 3-1. 

3.2.1.2.1 Roles and Responsibilities - Phase I. 

The System Program Director of the MOL SPO will be responsible to the DCMS for all aspects of the research, development, test and 

acquisition of the Manned Orbital Laboratory System. Specifically, this 

includes the development, fabrication, system integration, launching, injection into orbit, and functional testing of spacecraft vehicles and payload 

equipment including scheduling, integrating, and conducting orbital experiments. The functions of the various elements of the MOL SPO are shown 

on Figure 3-2. 

3.2.1.2.2 Formal MOL SPO Tasks. 

The initial major task to be performed by the SPO in Phase I is 

to complete final contract negotiations and to award Phase IB contracts. The 

subsequent major tasks to be performed are delineated in the AFSCM 375-4 

and they will have been precisely defined during Pre-Phase I. 

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3.2.2 Support Agencies. 

Because of the complexity and scope of the MOL program it is 

anticipated that support will be required from the following organizations: 

3.2.2.1 Aerospace Medical Division (AFSC) - Will provide bioastronautic 

and human factor design criteria and test requirements and possible experiment sponsorship. 

3.2.2.2 Office of.Aerospace Research (AFCRL) - Will provide Aerospace environment data and possible experiment sponsorship. 

3.2.2.3 Research & Technology Division (AFSC) - Will provide laboratory 

and technical support and experiment sponsorship. 

3.2.2.4 Electronic Systems Division (AFSC) - Will provide technical 

support on data processing, display and communications, and possible 

experiment sponsorship. 

3.2.2.5 Air Force Flight Test Center (AFSC) - Will provide support in 

the selection and training of astronauts. 

3.2.2.6 Arnold Engineering Development Center (AFSC) - Will provide 

wind tunnel and environmental testing support. 

3.2.2.7 6555th Aerospace Test Wing (AFSC) - Will provide guidance and 

planning for and participation in flight testing. 

3.2.2.8 6594th Aerospace Test Wing (AFSC) - Will provide guidance and 

planning for secure data retrieval and processing. 

3.2.2.9 National Range Division - Will supply planning and support for 

flight testing. 

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RELEASE 1 JULY 2015 

SECRET 

3.2.2.10 Navy - Will provide laboratory and technical support, experiment 

sponsorship, and.sea recovery. 

3.2.2.11 In addition to the above, specific support is being provided by the 

Air Charting and Information Center and the Air Rescue Service directly to 

the MOL SPO. Further, the Strategic Air Command and the Air Training 

Command have representatives working directly with the SPO. 

3.2.2.12 NASA - Will provide laboratory and technical support and 

experiment sponsorship. 

3.2.3 Aerospace Corporation. 

The Aerospace Corporation is a not-for-profit contractor to 

SSD performing general systems engineering as an in-house function and 

providing technical direction for the industrial contractor effort (GSE/TD) 

for MOL. The basic roles and responsibilities of the Aerospace Corporation 

during the conduct of the MOL program will be to provide the services of a 

technical group responsible for GSE/TD for the MOL program: GSEOverall integration of the MOL system, design compromises among subsystems, definition of interfaces, analysis of subsystems and supervision 

of system testing; and, TD - The process of reviewing associate contractor 

efforts, exchanging technical information, preparing work statements for 

contract actions, and, where it will better achieve Air Force objectives, 

the contractor's technical effort is modified, realigned or redirected. 

3.2.4 Participating Contractors. 

3.2.4.1 Orbiting Vehicle (Laboratory Vehicle) Contractor. 

The Orbiting Vehicle Contractor, will be selected by source 

selection procedures in accordance with AFR 70-10. The selected contractor 

will perform Phase IB, IC (sustaining), and Phase II. A program office, 

including a specially constituted group to perform mission equipment 

-SECRET- SSM-50A 

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-SECRETintegration, will be established within the selected contractor's organization. 

The basic roles and responsibilities of the selected Orbiting Vehicle 

(Laboratory Vehicle) contractor during the conduct of the program are: 

a. Design and develop the Laboratory Vehicle. 

b. Manufacture and test the Laboratory Vehicle. 

c. Integrate Laboratory Vehicle Subsystems. 

d. Design, develop, and manufacture the Laboratory Vehicle 

Associated Ground Equipment (AGE) and insure integration 

with the Orbiting Vehicle Ground Environment. 

e. Integrate and install the mission equipment. 

f. Integrate experiment procedures. 

g. Integrate the complete Orbiting Vehicle. 

h. Assure compatibility of the Orbiting Vehicle with the 

booster system. 

i. Assure compatibility of the Orbiting Vehicle AGE. 

j. Assure compatibility of the Orbiting Vehicle and the 

Tracking, Communications, and Control system. 

k. Provide for the checkout of the Orbiting Vehicle prior to 

astronaut entry. 

1. Provide the composite Vehicle simulator(s). 

in. Devise on-orbit procedures. 

n. Provide for on-orbit abort procedures. 

o. Checkout Orbiting Vehicle before mating to the launch 

vehicle. 

p. Provide on-orbit technical support for the Orbiting Vehicle. 

q. Provide on-orbit Orbiting Vehicle data management 

capability. 

r. Collect, distribute and analyze Orbiting Vehicle sustention 

data. (Exclusive of on-orbit experiment data.) 

(See Section 6.3 and 6.4 for detailed definition of Laboratory and Orbiting 

Vehicles. ) 

SSM-50A 

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3.2.4.2 Gemini B Contractor. 

A sole source contract for Gemini B is justified since it is a 

follow-on to the present NASA Gemini program. The basic roles and responsibilities of the Gemini B contractor during the conduct of this program will 

include: 

a. Design and develop a modified Gemini B capsule. 

b. Manufacture and test the Gemini B capsule. 

c. Design, develop, and/or modify Gemini B AGE. 

d. Provide for Gemini B monitoring and checkout on-orbit. 

e. Devise crew transfer procedures. 

f. Assure safe Gemini B separation. 

g. Devise crew procedures during re-entry and recovery. 

h. Provide vehicle-borne communications during launch, reentry, and recovery. 

i. Pre-launch checkout of Gemini. 

j. Analyze Gemini B telemetry. 

k. Provide Gemini B recovery procedures. 

1. Provide safe abort during launch. 

3.2.4.3 Titan III Contractor. 

A sole source contract for Titan III is justified since it is a 

follow-on to the present Titan III program. The basic roles and responsibilities of the Titan III contractor during the conduct of this program will be 

as follows: 

a. Design launch system modification. 

b. Manufacture and test the launch vehicle. 

c. Integrate MOL Vehicle elements for launch phase. 

d. Assemble the Orbiting Vehicle on the launch vehicle. 

e. Operate the launch facility. 

f. Conduct checkout and launch operations. 

g. Determine launch trajectories. 

h. Analyze flight dynamics. 

-SEAREf- SSM-50A 

3-13 

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-SEORET 

i. Determine launch vehicle adequacy. 

j. Define launch environment. 

k. Define launch abort environment. 

1. Analyze launch vehicle telemetry. 

3.2.4.4 Experiment Equipment Contractor(s). 

Whenever practical, these contractors will be selected competitively using source selection procedures in accordance with AFR 70-10. 

Some of the experiment contractors may qualify as sole sources because of 

unique capabilities and/or continuation of present efforts. The basic roles 

and responsibilities of the experiment contractors during the conduct of the 

MOL Program are outlined below:- 

a. Design and develop the experiment mission equipment. 

b. Manufacture and test the experiment equipment. 

c. Design, develop, and manufacture the associated AGE. 

d. Check-out and deliver the equipment to the Laboratory 

Vehicle Contractor. 

e. Assure compatibility with the Laboratory Vehicle. 

f. Establish experiment test procedures. 

g. Checkout the experimental equipment. 

h. Analyze the experimental data. 

3.3 PRE-PHASE I, PHASE I & PHASE II. 

3.3.1 Pre-Phase I. 

Approval to proceed with Phase I will be contingent upon the 

evolution of a group of experiments which, in the judgment of the approving 

authority, meets the criteria set for the MOL program and justifies the cost 

of proceeding. A Pre-Phase I effort consisting of Air Force, Navy, and 

Aerospace in-house plus industrial contractor studies is required to produce 

this experiment package. This effort constitutes the "critical path" in the 

overall program definition effort. This experiment study activity is also 

beneficial in that it will enable the technical and operational characteristics 

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3-14 

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'SECRETof the experiments to be specified in the Laboratory Vehicle RFP much more 

accurately. While not a mandatory requirement for contractor selection, 

this inclusion insures that the selected contractor will not have to be substantially redirected upon Phase IB go-ahead, thus saving time and avoiding 

wasted effort. Furthermore, the three months of contractor performance 

required for generation of experiment information affords time for launch 

vehicle and Gemini B studies to provide interface and design constraints 

information which will enable laboratory proposers to configure more 

intelligently the laboratory and its interfaces with adjacent vehicle elements. 

Studies by subsystems contractors will contribute specific trade-off information on Laboratory Vehicle subsystems. These contractor efforts will 

further the decrease number and complexity of inter-vehicle iterations 

required during Phase IB and reduce the time required in Phase IB to select 

Laboratory Vehicle subsystems designs. More precise RFP inputs will also 

reduce waste motion by Laboratory Vehicle aspirants during the proposal 

period (Phase IA). The timing of these Pre-Phase I studies allows the 

contractual relationship with McDonnell and Martin to be interrupted during 

the Laboratory Vehicle proposal and source selection period - a cleaner 

arrangement if these contractors complete for the laboratory contract. 

The industrial contract studies to be conducted are described 

below. 

3.3.1.1 Orbital Space Station Studies. 

Three contractors have been selected and are performing this 

study for the primary purpose of deriving MOL experiments. This study, as 

presently-planned, does not involve the selection of space station configurations or the design of space stations. The resulting experiments will be 

mission-derived, but oriented toward assessing man's ability to perform 

military missions in space. The tasks to be performed during each of 

these studies are: 

Task 1 - Technical Requirements Planning 

Task 2 - Test Operations Planning 

Task 3 - Parametric System Definition 

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3.3.1.2 Experiment Studies. 

Detailed technical, cost, and schedule information will be required for each experiment to provide the Laboratory Vehicle contractor 

sufficient data to carry out Phase IB. Detailed definition of experiments 

will be accomplished to the maximum extent possible by in-house study using 

the full capabilities of AFSC. However, supplemental contract studies will 

be necessary to define the equipment and techniques for experiments where 

the technical approach is uncertain. These studies will provide trade-off 

comparisons and data sufficient to determine feasibility, validity, and preferred approach. Contract studies identified to date include: 

3.3.1.2.1 Image Velocity Sensor Subsystem Study. 

A study will be performed to analyze and define the experimental 

equipment required for three experiments identified as: P-1 - Acquisition 

and Tracking of Ground Targets; P-2 - 

_and P-3 - Direct Viewing for Ground and Sea Targets. Request for 

proposal No. 04-695-64-24-247 - Image Velocity Sensor Subsystem Study 

was issued 20 June 1964 and responses are expected 21 July 1964. One 

contractor will be selected to perform the following tasks: 

Task 1 - Elemental Simulations 

Task 2 - Parametric and Tradeoff Analysis 

Task 3 - Functions of Man 

Task 4 - Vehicle Interface 

Task 5 - Image Quality Analysis 

Task 6 - Experimental Testing and Mockup 

Task 7 - Preliminary Design Recommendations and Configuration 

Task 8 - Experiment Procedure Planning 

Task 9 - Experiment Simulation 

Task 10 - Program Planning 

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3.3.1.2.2 Multiband Spectral Observation Study. 

Proposals in response to RFP No. 04-695-64-250 were received 

4 June 1964 and have been evaluated. A contract is being negotiated on a 

price competition basis to accomplish the following tasks: 

Task 1 - Preliminary Study 

Task 2 - Preliminary Experiment Description 

Task 3 - Parametric Analysis and Tradeoff Studies 

Task 4 - Preliminary Design Recommendations and Configuration 

Task 5 - Simulation Definition 

Task 6 - Program Planning 

3.3.1.2.3 Autonomous Navigation Definition Study. 

Proposals for this study were received 23 June 1964. A 

contract will be awarded to one contractor to accomplish the following tasks: 

Task 1 Experiment Procedures 

Task 2 Equipment Requirements 

Task 3 Mapping and Geodetic Survey of Selected Terrestrial 

Sights 

Task 4 Vehicle Interface 

Task 5 Parametric Analysis and Trade-off Study 

Task 6 Simulation Program Definition 

Task 7 Astronaut Functions 

Task 8 Preliminary Design Recommendations and 

Configuration 

Task 9 Program Planning 

3.3.1.2.4 Manned Electromagnetic Signal Detection Studies. 

One contractor is required to perform the following tasks: 

Approval and release of this work statement is required from higher headquarters. 

Task 1 - Equipment Definition and Techniques Studies 

Task 2 - Astronaut Functions 

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--SfeRETTask 3 - Preliminary Design Recommendations and 

Configuration 

Task 4 - Program Planning 

3.3.1.3 Gemini B Pre-Phase I Study. 

A contract has been negotiated with the McDonnell Aircraft 

Corporation to conduct a study under a fixed price contract for the purpose 

of: (a) defining the configuration of Gemini B as an element of the MO!, 

system to the extent practical prior to Laboratory Vehicle definition, (b) 

providing early identification and recognition of interface problems and 

recommended solutions, and (c) identifying tasks and costs required to 

complete Gemini B definition. Resolution of certain questions regarding 

MOL vehicle systems and subsystems can best be obtained with the assistance 

of the McDonnell Aircraft Corporation and Martin-Marietta Corporation 

performing specific studies in coordination. For those tasks which require 

effort by both contractors, one contractor will be designated lead and the 

other will be the supporting contractor. The technique being employed is as 

follows: 

a. Briefly review and summarize previous studies which have 

enabled selection of promising alternatives. 

b. Perform preliminary design for selected alternatives. 

c. Evaluate each alternative against criteria chosen to reveal 

reliability, safety performance, time and cost impacts. 

d. Prepare conclusions and recommendations on each task. 

The specific tasks the McDonnell Aircraft Corporation aro performing are as follows: 

Task 1 - Gemini B System Functional Analyses 

The Contractor will conduct a functional analysis of operation and 

in-space monitoring, checkout and maintenance of the Gemini B spacecraft. 

Both routine and emergency situations will be covered. The results of this 

task will be used in concert with analyses of other MOL system elements 

for the identification of initial system requirements. 

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Task 2 - Crew Transfer Techniques. 

Alternative techniques for crew transfer between Gemini B and 

the Laboratory Vehicle will be defined and evaluated. The constraints placed 

on the Laboratory Vehicle will be set forth for each method. 

Task 3 - Crew Escape Methods. 

Alternative methods of crew escape on the pad and during boost 

will be studied. This task will be based on an abort environment model 

provided by the Martin Co. 

Task 4 - Retrograde and Retrograde and Re-entry System. 

The modifications required to enable Gemini B to de-orbit and 

re-enter from the MOL flight altitude (higher than that of the NASA Gemini) 

will be identified and the system operational constraints will be defined. 

Task 5 - Subsystem Studies. 

Studies of the Gemini Subsystems will be conducted to determine 

modification and test required to insure reliable performance after 30 days 

on orbit, to provide designs for on-orbit monitoring and checkout and to 

determine how subsystems not required for the period of Laboratory operation can best be secured. 

Task 6 - Gemini B/Laboratory Vehicle Interface. 

The objective of this task is to define the interface problems 

between the Gemini B and the Laboratory Vehicle. Problem areas include 

the requirements of the Gemini B for on-orbit power and environmental 

control, the choice of design atmosphere for the Gemini B, and checkout and 

monitoring of the Gemini B from the Laboratory Vehicle. 

Task 7 - ITL/MOL Compatibility Study. 

The purpose of this task is to evaluate the use of the AMR ITL 

facility compared to on-pad assembly of the orbital vehicle. New facility and 

OGE requirements will be identified. Design changes which will have a 

major effect on the ground system requirements will be defined. 

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Task 8 - Rescue Mission Analysis 

This study task will identify the rescue system requirements and 

characteristics and Gemini equipment modifications required to provide a 

capability for rescuing a MOL crew. 

Task 9 - Piggyback/Simulation Flight Tests 

This study will define a flight test program, consisting of a 

minimum number of piggybazIt flights on Titan IIIC R&D launches, adequate 

to proof test the Gemini B and thereby reduce the number of unmanned MOL 

flights. 

Task 10 - Program Planning. 

The Contractor will formulate a program plan for Phase I and a 

preliminary plan for Phase II. These plans will identify, define, and relate 

the tasks to be performed in development of Gemini B and provide cost and 

schedule estimates, contractor, and government resources required consistent with the Master Program Schedule. 

Task 11 - Final Technical Documentary Report. 

The final report will contain all the significant technical data 

resulting from the work performed and will include the Contractor's conclusions and recommendations. It will be used as an input to the Laboratory 

Vehicle RFP. 

Titan III Pre-Phase I Study. 

A contract has been negotiated with the Martin-Marietta 

Corporation to conduct a study under a fixed price contract for the purpose 

of: (a) defining the configuration of Titan III as an element of the MOL system 

to the extent practical prior to Laboratory Vehicle definition, (b) to provide 

early identification and recognition of interface problems and recommended 

solutions, and (c) to identify tasks and costs required to complete the 

definition of the Titan III configuration for MOL, The techniques to be 

employed in conducting this study will be as described in Paragraph 3.3.1.3 

above. The specific tasks are as follows: 

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Task 1 —Titan III System Functional Analyses. 

The Contractor will review the functional analysis which was 

performed during the Titan III Program Definition Phase and determine the 

impact of MOL. New or modified functions will be analyzed to determine 

additional system requirements and constraints on the laboratory vehicle. 

Task 2 - Launch Vehicle Constraints on Payload. 

A study will be conducted to define the launch vehicle constraints 

on the Laboratory Vehicle design. 

Task 3 - Guidance Study. 

The Gemini inertial guidance system (ICS) will be evaluated for 

application as a primary guidance system and as a backup for the MOL 

launch phase. 

Task 4 - ITL/MOL Compatibility. 

The purpose of this task is to evaluate the use of the AMR ITL 

facility compared to on-pad assembly of the Orbiting Vehicle. New facility 

and AGE requirements will be identified. Design changes which will have a 

major effect on the ground system requirements will be defined. 

Task 5 - Transtage Study. 

Use of the transtage to perform on-orbit stabilization and 

propulsion will be investigated and required modifications will be identified. 

Task 6 - Payload Performance. 

An analysis will be performed on the Titan III payload capability 

for MOL application. The calculations will be conducted for both minimum 

and nominal limit launch vehicle characteristics. 

Task 7 - Crew Safety. 

The abort hazard environment will be determined in terms of 

fireball position and overpressure as a function of position in the launch 

trajectory. 

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Task 8 - Rescue. 

Launch vehicle and launch complex requirements will be determined for providina the capability to launch an unmanned Gemini with Titan 

III or the Titan U Gemini Launch Vehicle for rescuing the crew of a MOL 

spacecraft. 

Task 9 - Program Planning. 

The Contractor will formulate a program plan for Phase I and 

a preliminary plan for Phase II. These plans will define, note inputs required from and outputs to other associate contractors, schedule the tasks to be 

performed and provide cost estimates, contractor, and government 

resources required consistent with the Master Program Schedule. 

Task 10 - Final Technical Documentary Report. 

The final report will contain all the significant technical data 

resulting from the work performed and will include the Contractor's conclusions and recommendations for inclusion in the Laboratory Vehicle RFP. 

3.3.1.5 Apollo Pre-Phase I Study. 

It has been recommended that North American Aviation, Inc. 

perform a funded systems study to provide information needed to determine 

the potential of the Apollo system to perform the MOL mission. The study 

will be based on the MOL system characteristics and requirements as they 

are currently defined. The study will take advantage of the Extended Apollo 

Study performed under NASA contract and will follow the concept of minimum 

changes to the present NASA Apollo configuration. Both the Saturn IB and 

Titan LUC launch vehicles will be considered. On the basis of this study the 

capability of the Apollo to perform the MOL mission will be determined. 

Approval and release of the Apollo Study Tasks to be performed under this 

study are as follows: 

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Task 1 - Mission Analysis 

The contractor will perform mission and functional analysis to 

determine requirements imposed on the Apollo system by the MOL program 

objective. 

Task 2 - System Analysis and Design. 

This task requires the selection of the most desirable Apollo 

configuration for accomplishing the MOL mission. Trade-off analysis of 

configuration considered is required. 

Task 3 - Program Planning. 

The contractor will define an optimum program plan which shall 

include, but not be limited to, the following subtasks: development, ground 

test, aircraft test, space flight test program, program schedule, and timephases costs for recommended flight programs. 

3.3.1.6 One Man Gemini Study. 

It has been recommended that the McDonnell Aircraft 

Corporation conduct a funded study to investigate the degree to which a 

GLV-launched Gemini spacecraft modified for operation by one astronaut 

can satisfy MOL objectives. The contractor will determine the modifications 

necessary to carry and operate experiment equipment within the performance 

and volumetric capacity of the system, and to remain in orbit as long as is 

practical with this system up to thirty days. He will determine a preferred 

operational procedure, derive the time available for conduct of experiments, 

identify and describe the experiments to be conducted and develop a program 

schedule and cost. Specific tasks are: 

Task 1 - Functional Analyses 

Task 2 - Experiment Integrations 

Task 3 - Program Planning 

Task 4 - Final Technical Documentary Report 

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3.3.1.7 Laboratory Vehicle Subsystem Studies. 

Pre-Phase I studies will provide MOL- specific trade-off information on alternative designs and components in each subsystem modular 

area. Each study will cover the evaluation spectrum, furnishing technical, 

reliability, safety, schedule, and cost information. As a part of the 

Laboratory Vehicle RFP data, information generated by these studies will 

start proposing contractors' efforts closer to the final answer in each of 

these areas. Each of these studies will stress design to make the most of 

the presence of the crew to increase simplicity and reliability. It will be 

the goal. of each to identify a single preferred approach. In any case, the 

trade-off analyses will reduce the area of uncertainty and will identify further 

study and tests to be conducted in Phase IB to produce final decisions and 

subsystem specifications. 

3.3.1.7.1 Environmental Control Subsystems Study. 

This study is in the process of contract negotiations with the 

Hamilton Standard and Garrett Corporations. These contractors will conduct an evaluation of a single versus a two-gas subsystem for the Laboratory 

Vehicle. Since this system will probably supply the environmental control 

needs of the Gemini B during its 30-day period of storage on orbit, this 

study will consider the needs of the entire Orbiting Vehicle. It will be 

closely coupled to the Gemini B study in progress du-ring the Pre-Phase I 

period. 

3.3.1.72 Electrical Power Subsystem Study. 

This study is in the process of contract negotiations. The 

electrical power supply for the Orbiting Vehicle, located in the Laboratory 

Vehicle, will consist either of a solar cell-rechargeable battery system, or 

of fuel cells, or a combination of the two approaches. These approaches 

exhibit different advantages and disadvantages and the contractor studies will 

be conducted to determine the optimum system. The selection of the 

electrical power system profoundly affects the Laboratory Vehicle design and 

constrains the ability of the MOL to perform its initial and possible 

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electrical power system profoundly affects the Laboratory Vehicle design 

and constrains the ability of the MOL to perform its initial and possible 

future missions. 

3.3.1.7.3 Attitude Control Subsystem (ACS) Study. 

A contract has been negotiated with the Minneapolis-Honeywell 

Corporation. This study will provide design criteria for the MOL ACS 

system through a range of requirements which may be imposed by experiments 

and other subsystems, such as solar panel orientation and crew motion. A 

crossfeed will be maintained between this study and other subsystems 

studies so that impulse requirements can be determined and a preferred ACS 

system can be specified. 

3.3.1.7.4 Guidance Subsystem Study. 

Martin is required to analyze T-III guidance for use through 

injection plus pilot in loop at launch. McDonnell is analyzing uses of Gemini 

Inertial system for de-orbit and re-entry in view of this and anticipated data 

from Standard Space Guidance Study plus the fact that it now appears that no 

one industry source would provide a complete and objective analysis of the 

overall problem, no additional funded industry support is planned at this 

time. MOL guidance system will be collected and compared. This study 

will be closely coupled with guidance requirements studies for Titan III launch 

and Gemini B re-entry guidance during the Pre-Phase I period. 

3.3.1.7.5 Communications and Control Subsystem. 

It was originally intended that this effort would consist of a 

funded study.with industry and encompass five task areas: 

a. On-board data management and transmission. 

b. Ground support. 

c. Inter-site communications. 

d. Display, control, analysis, and simulation. 

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e. Rendezvous requirements on the ground system. Further 

review of these tasks reveal that they could more effectively 

be accomplished by utilization of DOD resources. Specifically, arrangements have been made wherein NRD supported 

by SCF will accomplish tasks B and C. Tasks A and D are 

to be accomplished in-house by Aerospace with possible 

support from ESD. Task E has been deleted in view of 

similar analysis in the 706 Phase 0 studies. It is possible 

that some future contractor effort of a small nature will be 

utilized in support of the NRD efforts. 

3.3.1.7.6 Vehicle Design Requirements of a Side-Looking Radar. 

Lesign requirements of a side-looking radar: In view of the 

capability existing in SSD/Aerospace and ASD initial phases of this task are 

being accomplished in-house. It may be desirable to have funded industry 

effort in this area in the future. 

3.3.1.8 Aerospace Corporation Pre-Phase I Effort. 

Task 1 - System Functional Analyses to derive: 

a. Preliminary performance requirements 

b. Preliminary design criteria 

c. Functional interfaces 

d. End item identification 

Task 2 - Experiments Program to derive: 

a. Experiments definition 

b. Integrated Experiment Payload Package 

c. Vehicle Interface Requirements 

d. Payload Specifications 

e. Necessary documentation for Ph I (work 

statements, RFP data, etc.) 

Task 3 - Identify Major Technical Problems and alternative 

solutions. 

Task 4 - Necessary technical support data, work statements, 

and RFP data for Phase I to include laboratory 

vehicle, vehicle subsystems, Gemini B, T-III, flight 

test plans and documentation, prerequisite data as 

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reflected in DOD Directive 3200.9, and other required 

support documentation. 

Task 5 - In-house studies and analyses leading to a sound 

approach for the MOL vehicle. 

Task 6 - Preparation of Pre-Phase I Contractor Task 

Descriptions. 

Task 7 - Evaluation of Pre-Phase I Study Results. 

Task 8 - Preparation of Phase I Contractors Task Description. 

Task 9 - Pre-Phase I Studies. 

a. Stablization 

b. Monitoring and checkout on orbit 

c. Electrical power subsystem 

d. Environmental control system 

e. On-board data handling 

f. Electromagnetic interference (EMI) Compatibility 

g. Communications 

h. Flight test plan 

I. Program integrated ground test plan 

j. Telemetry, tracking and communications 

k. Analysis of existing and programmed TT&C 

capability 

1. MOL information processing 

m. MOL support planning 

n. Communications and control interface definition 

o. Communications and Control Subsystem on-board 

data management and transmission 

p. Communications and Control Subsystem display, 

control, analysis, and simulation 

q. Configuration analysis 

r. Compartimentization 

s. Docking methods 

t. MOL diameter/length trade-off 

u. Orbital life trade-off 

v. Astronaut rescue 

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IfeRETw. Vehicle design 

x. Subsystem integration 

y. Configuration development/control 

z. Environmental criteria 

aa. Crew utilization/human factors 

bb. Redundance/maintainability 

cc. Astronaut safety criteria 

dd. Design requirements of side-locking radar 

Task 10 - Final Detailed Technical Report (one for each PrePhase I Study). 

Task 11. - MOL Experiments Studies. 

Task 12 - Prepare MOL System Performance/Design Requirements Specification. 

Task 13 - Prepare Data Package (for Phase I RFPs). 

The Aerospace studies, coupled and augmented by the industry 

studies, will significantly improve the quality of the RFPs so that the Phase 

IB efforts can be accomplished with reduced number of iterations and in the 

time allotted. 

Task 14 - Preparation of Technical Development Plan 

3.3.2 Project Definition Phase I. 

Phase I will be the formal step in the MOL'development process 

preceding full-scale development (Phase U), during which preliminary engineering and contract and management planning will be accomplished. The 

primary objectives of Phase I are: 

a. To establish firm performance specifications down to the 

vehicle element, interface and experiments level. 

b. To define contractor roles and missions. 

c. To identify high risk areas. 

d. To select technical approaches. 

e. To define work statements and establish firm and 

realistic schedules. 

f. To evolve and negotiate incentive contract formulas for 

Phase II. 

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g. To cost realistically the defined Phase II program. 

h. To prepare the documentation and technical data necessary 

to request Phase II program approval. 

This phase, consisting of three subphases (IA, IB and IC), will begin with 

approval to proceed and release of funds by the Office of the Secretary of 

Defense (OSD). It will end with OSD approval to initiate Phase II. 

3.3qt.1 Aerospace Corporation. 

During Project Definition Phase, the Aerospace Corporation will 

perform the following tasks: 

Task 1 General Systems Engineering 

a. Establish performance requirements 

b. Define design criteria 

c. Identify and define interfaces 

d. Evaluate alternative approaches to technical 

problems 

e. Identify technical solutions to systems problems 

Task 2 - Provision of technical support to source selection 

Task 3 - Evaluation of Phase I contractor's efforts 

Task 4 - Maintenance of Data Book 

Task 5 - Review and evaluation of contractors' Phase II proposals 

Task 6 - Provide technical advice to Air Force in contract 

negotiations 

3.3.2.2 Phase IA - Preparation for Contractor Definition. 

Upon approval to proceed with Phase I, the Laboratory Vehicle 

RFP will be released to industry. This RFP will solicit proposals for the 

Contractor Definition Phase IB and planning proposals for the Phase II development of the Laboratory Vehicle. 

Following proposal evaluation via source selection procedures, 

a contractor will be selected to conduct Phase IB. Concurrently, McDonnell 

and Martin and supporting contractors in vehicle subsystems areas will be 

requested to submit proposals for providing Phase IB support to the 

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definition of the complete MOL system and completing the definition of the 

Gemini B and Titan UM configurations. In addition, sole source and/or 

competitive selection procedures will be used to award contracts for selected 

MOL experimental packages. During Phase IA the SPO, together with Aerospace, will evolve a detailed plan for coordinating the iterative preliminary 

design process that is the heart of the IB effort. Other associate contractors 

may also enter the program in Phase I. Phase LA terminates with the 

initiation of the Phase IB Definition contracts. 

3.3.2.3 Phase IB - C.Jntractor Definition. 

During this period the contractors will accomplish the preliminary engineering that is required to define the MOL system along with developing the contract and management for Phase II. The SPO, with Aerospace 

technical support, will closely direct contractor effort according to the plan 

developed during IA and provide additional guidance as needed to assure that 

the resulting system definition is optimized. During definition of the 

technical, schedule, and management aspects of the development program, 

the contractors will continuously update specifications and proposals, including work statements, for the Phase U development. Also, Phase IB will see 

continuous negotiation of incentive contract formulas for Phase II. 

The tasks to be performed by the contractors during Phase IB are 

summarized below, but will be expressed in detail in the Phase IB work 

statements. The work statements (IB) will be prepared during the Pre-Phase 

I period and updated upon receipt and evaluation of the contractors' proposals. 

They will form the basis for Phase IB Contract negotiation. 

The Phase IB work statement tasks are summarized for the 

Laboratory contractor in the next paragraph. Since the work statement 

structure and the essential elements of the tasks are substantially the same 

for all Phase IB contractors, no additional summaries are shown for other 

Phase IB associates. 

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3.3.2.3.1 Laboratory Vehicle Contractor Phase IB Tasks. 

Task 1 - System Engineering 

The contractor will conduct studies and perform preliminary 

design in accordance with the system engineering definition provided in 

AFSCM 375-1 and AFSCM 375-4. The following technical studies will be 

accomplished in addition to the speciality area studies required to prepare 

the necessary functional management plans: 

a. Mission Pr-ofile Analysis 

The pre-launch, launch and injection, and orbital operation 

periods will be analyzed to determine design requirements 

for the laboratory vehicle. 

b. System Analysis 

System analyses of single or dual compartment trade-offs, 

rendezvous and docking, extended mission duration, growth 

provisions, crew transfer, abort operations, and interface 

investigations will be conducted and design approaches 

defined. 

C. Subsystem Analysis 

Subsystem analyses including crew performance, integration 

of experiments, propulsion systems, environmental control, 

stabilization and control, data recovery, and communications 

will be accomplished and technical design requirements determined as necessary to prepare the appropriate end-item 

specifications. 

d. Special Studies 

The contractor will accomplish selected special studies as 

required to define the laboratory vehicle and prepare the 

required system specifications. Typical studies are: disposal of the laboratory vehicle, test program philosophy, 

recovery requirements, and identification of high risk areas. 

Additional special studies may be generated by SSD/ 

Aerospace or the contractor as required to insure the optimized system definition. 

Task 2 - Phase II Proposal 

The contractor will prepare a firm proposal for the acquisition 

of the Laboratory Vehicle system. This Phase II - System Acquisition 

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proposal will form the basis for negotiation between the AF and the contractor and will include all work packages for the program. The contractor will 

accomplish the following sub-tasks in order to prepare the laboratory vehicle 

proposal: 

a. System and End-Item Design/Performance Requirement 

Specifications 

All specifications required from the system to the enditems will be prepared by the contractor. 

b. Functional Management Plans 

The con: actor will prepare all the functional management 

plans that are necessary to acquire the Laboratory Vehicle 

system. Specifically, a Program Plan, Program Test Plan, 

System Effectiveness Plan, Material Support Plan, Documentation and Data Requirements Plan, Configuration 

Management Plan, Financial Plan, and an Interface Control 

Plan will be prepared. The System Effectiveness Plan is 

further subdivided into the Reliability, Quality Assurance, 

Maintainability, Personnel Subsystem, Safety, and Transportability Programs. The Material Support Plan includes 

the Maintenance, Supply, and Transportation Program, and 

the Financial Plan includes Cost Estimates, Incentive-Fee 

Plan, Make-Buy Plan, Value Engineering Plan, and the 

Contractors Financial Data. 

c. PERT/Time/Cost Systein 

A plan for implementing a PERT/ Time and Cost System for 

the complete Phase II program will be prepared. 

d. Phase II Work Statement 

The contractor will prepare a detailed Work Statement for 

the Phase II program, and this work statement will be 

patterned after the Specimen Phase II Work Statement provided with the Phase I Laboratory Vehicle RFP. 

Task 3 - Contractor Phase IB Summary Report 

3.3.2.4 Phase IC - Review & Decision. 

This period will start with the receipt of the contractors' Phase 

IB reports and Phase II program proposals, all significant features of which 

were negotiated in Phase IB, and Phase U cost proposals. These reports 

SSM-50A 

3-32 -SEGRETTM document contorns •n1otrnot.on ollecbng the nohonol cletense 01 the Untied State, ...hot the meon,ng 01 the Eqttortege so«. 

Tale 18. 11 5 C Section 793 and 794 the of ■ rt nny moony, to an unnuthor.yerl person .s prnh.h,ed by Ion 

• 
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and proposals will be evaluated, necessary changes made in the work 

statements, and firm program costs be determined. Definitive contracts 

will be negotiated during this phase. Phase IC will end with OSD approval 

to initiate the Phase II. During the Phase IC evaluation and approval process, the contractors will be funded at a level adequate to insure program 

continuity and to permit preparation for prompt procurement of long-lead 

items. 

3.3.3. System Acquisition Phase II. 

Phase IT Is the full scale development period (including development and testing) which follows Phase I. It will begin with OSD approval to 

initiate Phase II and end when development activity is no longer significant. 

It should be emphasized that the Phase II data reflected within this plan is 

not firm data, and is only provided for preliminary planning purposes. The 

Phase I effort will generate the detailed information required to develop the 

system during a Phase II program. The actual tests and experiments to be 

conducted by MOL to assess man's utility in performing military missions 

are all considered part of this Phase II effort. In the development of a 

normal operational military system, a Phase III Operations period follows 

System Acquisition. However, MOL as presently conceived will remain in 

Phase II throughout its flight history. Should the MOL ever be used as an 

operational system, it would require a follow-on Phase III program. The 

tasks to be performed by the Associate Contractor during Phase II will be 

formulated during Pre-Phase I and presented via the Phase II Specimen 

Work Statement. These work statements, for the Laboratory Vehicle, 

Gemini B, Titan III, and Experiment Contractor will become a part of the 

Phase IB RFPs. 

3.4 DOD-NASA RELATIONSHIP. 

The 21 January 1963 agreement between the NASA and the DOD 

concerning the Gemini Program has established the basis as well as the 

-BRET- SSM-50A 

3-33 

This document contains Infotmohon allechng the notionot detente 01 the United States .,thin the meaning of the Espionage laws 

T∎IIe le. U.S C . Section 793 and 794. the 01 wh.ch in any mann°, to on unouthoi•ted personis ntm..b•rad by In. 
EROSPACE 

SYSTEMS DIVISION 

NRO APPROVED FOR 

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SCCRET 

SSM— 50A 

3-34 -SECRETThis document contains informonan effecting the notional omente of the Untied Stales within the meaning of the Espionage tans 

Title 113. U.S.C.. Section 793 and 794, the transmission of which in any manner to on unauthorized amen is prohibited by tow 

Figure 3-3, AssociateCo

ntractor StructUreForPhases I& II 
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--rsEeREfprecedent for development of working relations between the two agencies for 

the MOL program. The three major NASA-DOD interfaces envisioned are: 

a. Contracting for Gemini B 

b. Common use of existing facilities 

c. Inclusion of NASA experiments 

In regard to contracting for the Gemini. B, the Air Force desires 

a direct contractual relationship with McDonnell in order to employ the 

management principles and procedures of the DOD. NASA is concerned that 

such an arrangement might result in competition for McDonnell resources 

to the detriment of the NASA Gemini program. An additional agreement between the Associate Administration of NASA and the Director of Defense 

Research and Engineering on 23 January 1964 included interface problems 

growing out of the Gemini and Gemini B/MOL, in the charter of the Gemini 

Program Planning Board (GPPB). This agreement also recognized the intention of the Air Force to contract directly with McDonnell for the preliminary design of the Gemini B. The work statement for the Gemini B PrePhase I contract includes a task to develop the time-phased McDonnell 

resource requirement to conduct the Gemini B definition and development 

effort. The resource requirement for Phase II will be updated during Phase 

IB. It will be meshed with NASA requirements for the same resources so 

that a plan with adequate controls can be evolved to preclude interference 

between the two programs. Effective working relations have been established 

between the SSD and the Manned Spacecraft Center (MSC). An MSC liaison 

engineer has been named and has been working with SSD since mid-February 

1964. Experience to date indicates that problems of NASA Gemini - Gemini 

B interface will not be difficult to resolve. 

The interface problems in the area of ground facilities for 

training and flight operations must be resolved during the Pre-Phase I and 

Phase I periods. Such facilities will include the Mercury Control Center, 

tracking station, communications facilities, and the joint use of DOD 

recovery forces. Explicit DOD/NASA agreements must be arrived at for 

the use of these resources. 

SECRET SSM-50A 

3-35 

Thus document conto.ns .nlormo,on otiect.ng t■, oc•e-le o' U-•teo S.n. 0... the etecte•n9 01 the E11,0"09f 

Tole f9. U S C Sect.on 793 o^c1 794 the ter. m s. o^ of ■•••• •t, om n^c ..^o^^e• to o-u,O,,0,c-te f netio^ rvoK b•,ed by In.. 
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The concept for MOL includes the acceptance of NASA experiments on a basis analogous to that governing placement of DOD experiments 

aboard the NASA Gemini flights. A NASA representative at SSD represents 

NASA in the day-to-day work of integrating NASA-sponsored experiments in 

the MOL. 

SSM-50A 

3-36 -SEMTh., document cOnlOstvt ofiechng the not.onot nee,e or the Untied States ....thin the meaning Of the Esotonoge 

T.tre 1 8 U S C Sect.on 793 and 79.1 the of .n nny mono, ion vnnveho,,r1 Dent. b..ed he In. 
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SECTION 4 

INTELLIGENCE ESTIMATE 

NOT APPLICABLE AT THIS TIME 

DATA PERTINENT TO THIS SECTION 

MAY BE GENERATED DURING PHASE IB 

SSM- 50 A 
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SECTION 5 

OPERATIONS 

NOT APPLICABLE AT THIS TIME 

THIS SECTION IS ADDRESSED TO PHASE III OPERATIONS WHICH IS 

NOT A CONSIDERATION IN THE MOL PROGRAM AT THIS TIME 

SSM-50A 
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INDEX 

SECTION 6 

ACQUISITION 

Page 

6.0 SYSTEM SUMMARY 6- 1 

6.1 MOL EXPERIMENTS 6- 1 

6.1.1 Objective of the Experiments Program 6- 3 

6.1.2 Criteria for Selection of Experiments 6- 3 

6.1.3 Basic Manned System Considerations 6- 4 

6.1.4 Mission Analysis 6- 5 

6.1.5 Experiments Definition 6- 7 

6.1.6 Primary Experiments - Assessment 

of Man's Utility 6- 8 

6.1.7 Experiments versus Missions & 

Applied Functions 6-34 

6.1.8 Secondary Experiments 6-34 

6.1.9 Summary of Vehicle Requirements 6-37 

6.1.10 Summary of Simulation Requirements 6-38 

6.1.11 Summary of Funded Definition Studies 6-40 

'6 1.1-2 U.S. Navy. Package 6-44 

6.2 MISSION PROFILE 6-45 

6.3 VEHICLE SYSTEM 6-46 

6.3.1 Orbiting Vehicle (OV) 6-47 

6.4 LABORATORY VEHICLE 6-48 

6.4.1 Structural Arrangement 

6.4.2 Astronaut Transfer 

6.4.3 Environmental Control 

6.4.4 In-Space Maneuvering 

6-48 

6-51 

6-51 

6-53 

-SECRET- SSM-50A 

6-i 

1k., •,.. the LInoed Srnre, .ch,a the oleon.ng of the ho'o".qe la.s. 

; 8 ■ ; S f .•,. ',1 r3,1 794 • • •• vor, .h.cM1 ••• ony n nc. to nn vnoutho•./c•d . ■ woh.h.,ed by In 
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t .,1 X It (i) 

Page 

6.4.5 Crew Duty Cycle 6-55 

6.4.6 Navigation and On-Orbit Control 6-56 

6.4.7 Electrical Power 6-56 

6.4.8 Data Processing and Communications 6-57 

6.4.9 Reliability, Monitoring, and Checkout 6-57 

6.4.10 Weight Breakdown 6-58 

GEMINI B 6-58 

6.5.1 General 6-58 

6.5.2 Design and Modification Considerations 6-59 

6.5.3 Gemini Subsystems 6-59 

6.5.4 Interfaces 6-61 

6.5.5 Major Problem Areas 6-61 

6.5.6 Gemini B Preliminary Weight Breakdown 6-62 

LAUNCH VEHICLE 6-62 

6.6.1 Description 6-62 

6.6.2 Modification Considerations 6-62 

6.6.3 Interfaces 6-64 

6.6.4 Problem Areas 6-64 

6.6.5 Payload Capability 6-64 

GROUND SUPPORT 6-64 

6.7.1 Checkout and Launch 6-64 

6.7.2 Mission Control Center 6-66 

6.7.3 Remote Station Network 6-66 

6.7.4 Tracking, Communications, and 

Control (TC and C) 6-66 

6.7.5 Satellite Recovery Complex 6-67 

6.7.6 Data Processing 6-67 

SSM- 50A 

6-ii -SECRET- 

.",nt,ent.0e. ollet s,r7 'he ho„nnsyl detente .1 t he lb,,erI Stnors w ■ vh.n the menenng of the f wtanage 

6.5 

6.6 

6.7 
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Page 

6.8 MANUFACTURING AND GROUND 

TEST FACILITIES 6-68 

6.9 COMPONENT AND SUBSYSTEM 

DEVELOPMENT TESTING 6-68 

6.10 SYSTEM FLIGHT TEST AND 

OBJECTIVES 6-69 

6.10.1 Test Operations Concept 6-69 

6.10.2 Flight Test Planning 6-70 

6.11 ACQUISITION SUPPORT 6-70 

6.12 PERSONNEL TRAINING 6-71 

6.13 MOL SPECIFICATIONS 6-72 

6.14 RELATED STUDIES 6-72 

FIGURES 

Number Title Page 

6-1. MOL Flight Vehicle 6- 2 

6-2 MOL Laboratory Vehicle - Single Pressure 

Compartment 6-49 

6-3 MOL Laboratory Vehicle - Dual Pressure 

Compartment 6-50 

6-4 Astronaut Transfer Concepts 6-52 

6-5 Docking and Mooring Concepts 6-54 

6-6 Gemini B Vehicle 6-60 

6-7 Titan IIIC Vehicle 6-63 

6-8 Titan IIIC ITL Facility 6-65 

6-9 MOL System Specifications 6-74 

-EGRET- SSM-50A 

6-iii 

This document contains information aflecting the national defense of the United Slates within the meaning of the Espionage Lows, 

Title IS, U.S C . Section 793 and 794, the transmission of which in ony manner to an unouthorized person is prohibited by low 
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LIST OF TABLES 

Number Title Page 

6-1 Manned Military Mission Assessment 6- 6 

6-2 Manned Military Mission Assessment 

Mission-Peculiar Experiment Relation Summary 6-35 

6-3 Manned Military Mission Assessment 

Mission-Peculiar Experiment Relation Summary 6-36 

6-4 Representative Crew Duty Cycle (2 Man Crew) 6-55 

SSM- 50A 

6-iv -SEGREF 

This document contains information eillecting the notional defense of the United Senses within the meaning of the Espionage lows. 

lille IS. U.S C Section 793 and 794. the transmission of which in any manner to on unauthorized onion is prohibited by low 
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SECTION 6 

ACQUISITION 

6.0 SYSTEM SUMMARY. 

The MOL System consists of major elements presently in 

various stages of development. The NASA Gemini vehicle is scheduled 

to be flown with a man aboard in the latter part of 1964/ and the Titan 

IIIC is scheduled to be man-rated in 1966. The Laboratory Vehicl6 still 

remains to be defined and engineered. Therefore, a prime Laboratory 

Vehicle objective is to make maximum use of available hardware and the 

efforts of other programs, but, at the same time, design and develop a 

system that meets the established MOL program objectives to assess 

man's utility and ability to perform military space missions. 

The overall MOL System will consist of an Orbiting Vehicle, 

a Titan III Standard Launch System, a Ground Environment System and 

flight and ground personnel. The Orbiting Vehicle is composed of the 

Laboratory Vehicle with experiments installed and the Gemini B re-entry 

capsule. An overall profile of the MOL flight vehicle at time of launch is 

presented in Figure 6-1. 

6.1 MOL EXPERIMENTS. 

The selection of specific experiments is a critical item in 

achieving the MOL program objectives. The definition of the experiments 

in terms of equipments, test procedures, and evaluation procedures is an 

important input to the overall laboratory design and will be needed before 

this effort can be accomplished to any large degree. 

A preliminary experiments package is defined in the following 

paragraphs. Selection of this package is the result of across-the-boatd 

DOD participation. Requirements sulpmitted .by the Army, Navy, and 

Air Force in support of their respective missions have been analyzed by a 

SSM-50A 

6-1 

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Tete tB. U 5 C Sect•on 793 ct^O '94 •he s. o^ at u !tt c- .th.thc• ne,!a- oth^ o •ec b, the 
GEMINI B ADAPTER 

REENTRY -423.00 CAPSULE 

T IIIC 

STA 

LABORATORY 

LAB MODULE 

VEHICLE 

TEST 

MODULE 

TITANIC 

T-III C 

STA 

1359.10 

SEPARATION 

PLANE STA 

77.000 

Figure 6-1. MOL Flight Vehicle 

SSM-50A 

6-2 -SECRETNRO APPROVED FOR 

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That document conto•ns .nforrnatmn offect.no the not.onol netense 01 the Untied Stole% *al.,. the rneontog of the Esponoge tont 

Ttlie la. U S C . Seefion 793 and 791, the t ■ t:nvn■ is■ on of .h.th .n any manner to on unouthot•zed person .t ptohtbded by la. 
NRO APPROVED FOR 

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SECRET 

composite experiments working group. This package requires additional 

definition which is to be achieved in the Pre-Phase 1 and Phase I program 

activities. Particularly this PTDP emphasizes the Pre-Phase I activities 

as they represent the next step in the program. As the program develops, 

it is expected that there will be additions and deletions to the experiments 

package as a result of further definitions. 

6.1.1 Objective of the Experiments Program. 

The objective of the MOL experiments program is to establish 

a qualitative and quantitative measure of man's usefulness in space for performing military tasks. 

6.1.2 Criteria for Selection of Experiments. 

The experiments presented in the subsequent paragraphs have 

been selected on the basis of guidance and direction received from Higher 

Headquarters (Ref. Section 14) and the statement of the program objectives. 

The criteria established are: 

a. The MOL is a space laboratory, not an operational vehicle. 

b. The experiments should be focused upon the role 'of man 

rather than specific equipment. 

c. The proposed experiments should consider the entire spectrum of possible military applications. 

d. Photography of reconnaissance quality will not be used to 

record or verify experiments. 

e. Maximum use should be made of ground simulations, aircraft tests, and existing space programs for testing. 

f. Experiments selected for MOL should be those that cannot 

be achieved in any other way, or which constitute a proof 

test of experiments primarily conducted in ground simulations or aircraft tests. 

g. The cost of the experimental program should be minimum, 

making use of existing equipment, and provide a comprehensive and meaningful test effort. 

Where new or modified test equipments are required the 

equipments must be technically feasible of attainment with 

minimum technical risk and readily available within the 

MOL program schedule. 

--SEGRET- SSM-50A 

6-3 

This document content intotmation atletting the notional aetente of the United Slates *aka, ihe meaning 01 the Espionage loa 

Title 18, U 5 C Section 793 and 794, the ti■snsmission of whtch sn any 'nanny( to on unouthOr ■ yyri per,On a•ah•h•Paa be 
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-ffERETi. which contribute to the development of military technologies which are scientific experiments of 

national importance may be considered as secondary experiments, particularly if they provide an assessment of man's 

utility. 

6.1.3 Manned System Basic Considerations. 

6.1.3.1 Man's Utility. 

Man's utility for performing military space tasks results from 

five basic abilities; the ability to: see, hear, reason, manipulate, and talk. 

These abilities combine to form a unique functional capability that has not as 

yet and probably will not, in the foreseeable future, be duplicated by any 

unmanned means. These unique functions are pattern recognition, systems 

management, and providing a versatile servomechanism capability. 

Pattern recognition is a function that is important in many 

present day military applications such as flying aircraft, assessing a. situation, acquiring targets, identifying targets, identifying targets and check 

points, and making damage assessments. The systems management function 

includes such tasks as selection of sensors or weapons, overriding or switching to alternate equipments, adaptive programming of propellant, selection 

of alternate targets, and deployment of defense measures. The servomechanism function is evident in all operations where the man performs direct 

manipulations such as vehicle control, sensor pointing and adjustments, and 

calibrations of equipment. The same functions of man are expected to be 

the basis for utilization of man in military space missions. The subsequent 

mission analysis discussion (paragraph 6.1.4) is predicated on the continued 

supremacy of man in these three unique functional areas. 

6.1.3.2 Man's Limitations. 

While man will add new dimensions to future military space 

systems, his operations will be limited by natural radiation and may also be 

limited by artificial radiation. The geomagnetic field about the earth traps 

cosmic electrons and protons forming a radiation belt which, for 30-day 

SSM-50A 

6-4 -sEefitf" 

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-BRETmissions and allowable biological doses on the order of 25 to 50 rads, 

limits manned operations to 300 nautical mile orbits and below, or to orbits 

of 20,000 nautical miles or more. 

6.1.4 Mission Analysis. 

In order to define a meaningful set of experiments which will 

provide an assessment of man's ability in military space tasks, it is necessary to analyze each military space mission and determine how man could be 

used to enhance the mission capability. While man can provide trivial functhins each as throwing switches, if his inclusion is going to be justified it 

must provide significant improvement in mission capability. In Table 6-1 

the critical mission functions which employ man's utility, discussed in 

paragraph 6.1. 3.1, are listed across the top of the page. On the left are 

listed the complete spectrum of potential military space missions. For 

each mission area the analysis has been carried out to determine the critical 

manned functions and these are marked in the appropriate columns. 

In performing this analysis no consideration was given initially 

to mission overall feasibility or the detrimental aspects of incorporating 

the man. This was done because in the case of manned satellites several 

nissions might be accomplished with one satellite, making it feasible to have 

the man there; whereas if each mission were performed individually the 

additional cost of the man would not be justifiable. As an example, manned 

meteorological satellites appear economically prohibitive, whereas if this 

mission is combined with land and ocean observation it appears as an attractive possibility for manned satellite system. Nuclear detection on the other 

hand appears to be a poor candidate for a manned system because of the 

limited contribution the man can make and the unique orbital altitude 

requirements. 

While most of the entries in Table 6-1 are self-explanatory, the 

items of maintenance, satellite defense, and logistics need explanation. 

Maintenance may be the most significant single contribution man can provide, particularly where the mission requires keeping the system on orbit 

for long periods of time. Manned maintenance becomes increasingly 

SECRET SSM-50A 

6-5 

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MAN'S CRITICAL 

APPLIED 

FUNCTIONS 

POTENTIAL 

MILITARY SPACE MISSIONS 

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Manned MilitaryMission Assessment 
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attractive as the weight of the man and his support equipment are a smaller 

fraction of the mission payload. In some mission areas, such as possible 

future orbital bombardment stations, manned maintenance may be the key 

factor in ultimately achieving an economically feasible approach. In other 

areas such as nuclear detection, about the only significant manned contributions that can be cited is maintenance, but the payload weight and reliability 

are such that inclusion of a man is impractical from an economic standpoint. 

Satellite defense becomes important for those systems that must 

endure long periods of time or exist during general hot war conditions. It 

too, is like maintenance in that the bigger or more critical the system is, 

the more justifiable is the inclusion of man for operation of defense 

capabilities. 

Logistic support will be required on all long duration manned 

missions. If the missions were to be accomplished unmanned, undoubtedly 

the satellite would have to be replaced. Whereas in the manned case, the 

presence of the man makes it feasible to consider rendezvous, docking, and 

resupplying of the basic spacecraft. 

6.1.5 Experiments Definition. 

The experiments program is divided into primary and secondary 

experiments. The primary experiments are those which form an integral 

part of the MOL Program and are defined as: 

a. Experiments to directly assess quantitatively and qualitatively the role of man in military space tasks. 

b. Experiments required as a result of the presence of the man 

in spacecraft, such as biomedical monitoring. , 

The secondary experiments are defined as experiments where 

the objective is the advancement of technology which will be applicable to 

future military space missions or acquisition of scientific data of national 

importance. 

SSM-50A 

6-7 

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6.1.6 Primary Experiments - Assessment of Man's Utility. 

P-1 

P-2 

P-3 

P-4 

P-6 

P-7 

P-8 

P-9 

P-10 

P-11 

P-12 

Acquisition and Tracking of Ground Targets 

Direct Viewing for Ground and Sea Targets 

Electromagnetic Signal Detection 

In-Space Maintenance 

Extravehicular Activity 

Autonomous Navigation 

Deleted by Direction 

Multi-band Spectral Observations 

General Performance in Military Space 

Biomedical and Physiological Evaluation 

6.1.6.1 Acquisition and Tracking of Ground Targets - Experiment P-1. 

6.1.6.1.1 Objective. 

The objectives of this experiment are to evaluate man's performance in acquiring preassigned targets and tracking them to an accuracy 

compatible with the requirements for precise IMC determination. 

6.1.6.1.2 Experiment Description. 

The equipment required for this experiment includes a directviewing, pointing and tracking scope; a general purpose computer; and a 

coupled camera. 

The pointing and tracking scope will be an optical device similar 

to a bombsight in design in that it will have a gimballed optical element for 

viewing in elevation and a rotatable barrel for azimuthal viewing. These 

adjustable elements will be driven by suitable servo motors based on computer input which will nominally hold the scene fixed in the field of view. 

The movement of the scene will be taken out by the astronaut tracking the 

target with a set of manually controlled cross hairs. Error signals 

SSM- 50A 

6-8 -SEC-RETMit document compos ,nfpcmcp.on offectmo the nafionol Detente 01 the Un'ed Slates ...oho the cneomng of the Etwonoge tont 

Title IS. U.S.C., Section 791 and 794. the Puntnust.on of tuh.ch .n on ), monnet to on unnutho.recl pemon wah.boled by no 
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RELEASE 1 JULY 2015 

-SERETproportional to the cross hair displacements will be fed into the computer 

and the nominal rates of the servo drive adjusted to center the target in the 

field of view, trim the rates, and eliminate the drift. Additionally, since 

wider fields of view at less magnification are desirable during the acquisition phase, and narrower fields of view at higher magnification during the 

tracking phase, the optical configuration will be capable of being zoomed 

over a range from 6 to possibly 100 power, the exact powers to be determined as part of the Pre-Phase I Study and Simulation effort. 

The computer will be a general purpose stored program type to 

allow it to be adaptable to other experiments. It will compute the tracking 

rates using geometrical considerations and smooth tracking data, and will 

compute the correct image motion compensation rates for taking high resolution pictures. Inputs to the computer will include both pointing and tracking 

scope data and inertial platform angular reference data. 

The pointing and tracking scope will have a coupled camera which 

allows pictures to be taken through the same basic optics used by the astronaut for viewing. The purpose of this camera is to verify that the astronaut 

has acquired the proper target and to permit evaluation of the man's performance in accomplishing the tracking function. During the tracking run, 

periodic photos will be taken, with the manually controlled cross hairs 

superimposed on the image, to determine the ope'rator's proficiency in 

keeping the cross hairs on the target. 

The test procedure is to fly over preselected targets in the ZI 

which may include military airfields, operational missile sites, AMR, 

naval bases, and specifically prepared target sites. The typical scenario is 

as follows: 

1. The astronaut aligns the vehicle in yaw by pointing the PTS 

at the ground underneath him with a grid in the field of view 

and with a zero azimuth angle. The grid lines will be parallel to the vehicle longitudinal axis and yaw alignment errors 

will be indicated by target points drifting across the grid 

lines instead of parallel to them. 

SSM-50A 

6-9 

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Tale 18 LT S C Seccon 793 c-ct '94 me k. 04 ^ :••1 77,•o- r•,- o •nn b■ 
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-SECRETZ. At the appropriate time, based on knowledge of orbit 

ephemeris, the astronaut scans the land area where he 

expects to find the target using his direct-viewing, pointing 

and tracking scope at low magnification. 

3. The astronaut attempts to identify some segment of that land 

area with the reference photo of the target area which will 

be supplied before lift-off. 

4. Upon matching the target area, the astronaut centers the 

particular target in the field of view of the telescope and 

initiates the tracking mode. 

5. During the tracking run, the astronaut attempts to keep the 

cross hairs of the pointing and tracking telescope positioned 

on the target, and the computer will smooth the tracking 

data. 

To evaluate the man's proficiency in target acquisition, the 

reference photos of the various targets will be intentionally varied in quality. 

Repeated acquisition and tracking tests will be made to evaluate the astronaut's proficiency under varying conditions of lighting, and the target areas 

so selected as to provide various background and color conditions. 

The evaluation procedure is to take photographs with the coupled 

camera during the acquisition and tracking operation showing the position of 

the cross hairs relative to the target, as well as the time. Analysis of these 

photos will enable determination of the accuracy to which the required IMC 

would have been determined. On-board film processing equipment would 

permit analysis of the test results and thereby limit communication/data 

retrieval requirements and provide additional measures of man's utility. 

6.1.6.1.3 Importance of Test. 

Future land observation missions may require the capability to 

obtain very high resolution photographs, for example, for technical intelligence purposes. Very high resolution photographs can, in theory, be 

obtained if a sufficiently large optical system is provided, and if precise 

image motion compensation can be accomplished. 

SSM-50A 

6-10 

Thn document contotns Infottnntton nitett.ng the "IC Undeli 5,t1.01 ,he Ineentng of the Tiptonoqe toe. 

Tile IS. U S C Scone 793 o.d 794 . the Ittlemn,s,.on ol .11 nny money, to on unnuthotterel pew, ponS•bord by lot 
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-SEGRET6.1.6.1.4 Vehicle Requirements. 

The weight of the PTS with the coupled camera is estimated as 

400 lbs, the computer 50 lbs, and the film processing gear as 75 lbs, for a 

total of 525 lbs. The actual equipment volume includes 3. 5 cu ft for the 

PTS, 1. 5 cu ft for the computer, and 1.0 cu ft for the film processor. 

The power levels are expected to be low on the order of 200 watts. The 

stabilization requirements for the PTS are not critical; however if the IMC 

data were to be useful, then the target must pass through the field of view 

of future high resolution sensors. This would result in a requirement for 

vehicle pointing accuracies of approximately 0. 1° and rate accuracies of 

0, 001°/ sec. 

6.1.6.2 - Experiment P-2. 

6.1.6.2.2 Experiment Description. 

SECRET SSM- 50A 

6-11 

This document contains otto,mohon &Iwo° the not ■Onel aelense of the Untied Stables *ohm the meaning of the Esponage tows 

Tote le. U.SC Seaton 793 and 794, the Itomm.won of whtth en ony manner to on unouthottieti person t, plohtbdeti by to.. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECRET 

SSM- 50A 

6-12 -BRET111,

1 document conlo.ns mleumco.on olleet.ng lee^01.0,b ne,enw co .re 11,•teo n.th.n th.• meanmg of the E ■ rt'0^,t9e Lo", 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECRET 

6.1.6.2.3 Importance of Test. 

6. .6.2.4 Vehicle Requirements. 

6.1.6.3 Direct Viewing for Ground and Sea Targets - Experiment P-3. 

6.1.6.3.1 Ob•ective. 

The objective of this experiment is to evaluate man's ability to 

scan and acquire land targets of opportunity, to scan and detect ships and 

surfaces submarines, and to examine ships and surfaced submarines for 

classification purposes. 

6.1.6.3.2 Experiment Description 

The pointing and tracking scope and general purpose computer 

provided for in Experiment P-1 will be used for this experiment. The procedure to be employed for land targets is to have the astronaut on selected 

orbital passes operate the direct viewing system in an automatic or manual 

scanning mode at the lowest magnification and attempt to detect certain 

types of targets of opportunity. Repeated tests with the direct viewing 

system should be made at various magnifications and scanning rates to 

IfeREf SSM-50A 

6-13 

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SECRET 

determine the percentage of targets detected and correlate results with 

ground and aircraft simulations. 

Upon detection of a target of interest the astronaut engages the 

tracking drive and zooms the viewer. He notes his observations with a 

direct voice recorder. In some cases it may be desirable to obtain verification pictures with the directly coupled camera. 

The ship and submarine detection experiment will be carried out 

using the same equipment (1. e., the PTS), but equipped with filters both 

chromatic and polarizing in order to minimize contrast attenuation. 

The test procedure will involve placing target vessels in otherwise deserted ocean areas which lie near or under the MOL orbital path 

during local daylight hours. The astronaut will be given pointing instructions (or approximate target geo-coordinates depending on computer-servo 

implementation) and be required to perform a visual search of the prescribed 

area of the ocean surface during the overflight. Parameters to be measured 

include detection capability as a function of target ship size, contrast 

(color), speed (wake), line-of-sight angle, sea state, atmospheric condition 

(contrast transmittance), magnification, filtering, etc. Additional tests will 

include search for targets of opportunity in densely populated shipping areas, 

observation of Kepplerian wakes from cooperative submerged submarines, 

and recording of results with the coupled camera and/or such other means 

as are appropriate to both the operational and scientific aspects of the 

detection tests. 

The ship identification experiments will also use the PTS. The 

targets should include as many classes of ships as possible, both naval and 

merchant vessels. The ships should be deployed in selected ocean areas 

having low probability of cloud cover. A relatively small number of vessels 

are required in the controlled tests, augmented by tests on normal ocean 

traffic using low flying aircraft (or other means) to provide identification 

simultaneously with spacecraft overflight. 

SSM- 50A 

6-14 -BRETTh.. document conto.n, .nlormnt.on ottect.ng 1nr e01,0nn,clornie ot ,ne Unded Synte, *dem ohe mean.n0 01 the E%p.o,,age lor.l 

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S

r 

The typical scenario is envisioned as follows: 

1. Following the detection experiment, the astronaut selects 

a target, slews the scope to Flut the target into the field-ofview,at low magnification. 

2. The scepb is zoomed as rapidly as possible (without losing 

the target) to a specified magnification and the tracking 

drive engaged. 

3. The astronaut spends a specified time examining the target 

and records his impression of ship class, heading, and any 

uniquely identifying features he can discern. 

6.1.6.3.3 Importance of Test. 

Detection and acquisition of data on land targets of opportunity 

could be of significant value to future reconnaissance and surveillance operations. It is a unique function that man can do becausecof the real time 

requirement. Detection of ships at sea and the ability to classify ships is of 

great importance to the ocean surveillance mrAqort. , hese functionS could 

be valuable for a Cuban-type crisis requiring.a rxav4.blockade. • Optical 

detection may be a problem bepause of the low .doiitia.sttransmissibility f• 

on clear days over the .sea. However, the experiment will allow correlation 

with the considerable simulation data developed by the Navy, and with 

restrictOd scanning and higher magnification greater detection probabilities 

, • 

may be achieved than in the simulations. 

6.1.6.3.4 Vehicle Requirements. 

No additional vehicle capabilities are required over and above 

those of P-1. 

• 

6.1.6.4 Electromagnetic Signal Detection - Experiment P-4. 

6.1.6.4.1 Objective. 

The objective of this experiment is to evaluate man's capability 

for making semi-analytical decisions and control adjustments to optimize 

the orbital collection of intercept data from advanced electro-magnetic 

emitters. 

--SEGREfSSM-50A 

6-15 

Ihrt document conform inlormot.on allechno the nohonoi cletente ot the United States *Ohm the meoning 01 the Esp.onoge tont 

Title It, U.S.C., Section 793 and 794, the IICMST.11.011 Of which m any monnerto on unouthoneeri person n proh.b.ted by la. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

6.1.6.4.2 Experiment Description. 

The equipment involved in this experiment includes antennas, 

receivers, displays, control console, and'.recorders. 

Additional supporting equipments needed in the performance of 

the experiment are ground and sea-based emitters as sources of specific 

known signals. Since emphasis of this effort is on sophisticated emitters, 

such targets will include frequency agility, long pulse internal coding, and 

SSM-50A 

6-16 -SECRETTh., document econtn.ns ,nlotmot.on attecl•no the nahOnni new,,, at the Undeel Stnte% n.th.n the theunalc of the botono,le Lou. 

Tale 18. U.S C . Section 793 and 79.1. the ttonvn.i,.on OI ..h.ch on, toonttot to nn onottlhot.iert wish hord ho Inn 
NRO APPROVED FOR 

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-SERETother intentioned parameter modulations or complex scan modes. Use of 

vessel-based emitters under U. S. Navy or U. S. Air Force control (i. e. , 

missile launch cruisers and tracking vessels such as ARIS) could provide 

fairly sophisticated targets in light density environments. 

The extension of simulation program results to orbital test will 

require some calibration of the initial performance capability of the operator 

as a frame of reference to subsequent performance. It is therefore necessary to utilize targets representative of those employed in aircraft simulation 

tests, thus providing continuity in evaluation. 

For MOL testing purposes, on-orbit inclination will be chosen 

to give some continuous overflight of ZI territory, or other areas well controlled, accessible, and in good communication to the MOL Flight Control. 

The basic matrix of tests includes: 

1. Light vs dense signal environments. 

2. Simple versus highly complex signal parameters. 

3. Self versus machine-aided alerting. 

4. Maximum vs minimum precognition or instruction. 

On each available orbit including day and night crossings of the 

test points, the console operator performs successively more difficult 

problems in terms of the above-mentioned matrix of choices. 

Specific control actions required by the console operator include: 

1. Main frequency tuning adjustment to center signal in 

pass-band. 

2. Choose optimum bandwidth for S/N improvement. 

3. Set gain controls for dynamic range control in recording 

most important sections of strong signals or extracting 

weak ones. 

4. Adjust synchronizing controls of displays to maximize or 

minimize effects of interleaved clutter signals. 

5. Employ time gating or frequency exclusion gating for 

removing clutter. 

6. Select appropriate detector outputs for display, particularly 

with reference to clarifying signal coding. 

SSM-50A 

6-17 

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7. Select appropriate recording medium and length of 

recording. 

8. After a pass, play back recordings, as desired, for evaluation of next pass procedure, or improvement of approach. 

9. Monitor and report "events" in "activity level", unusual 

noise level, etc. 

10. Alert other sensors. 

The evaluation of test results will, in part, be a function of the 

data reporting system available. A combination of "hot-flash" verbal 

reporting, video signal readout, tape and/or photo recovery, while in flight, 

will exercise and grade the operator on his accuracy, quality of intercept, 

and ability .to compress data. Specific scoring elements should include: 

1. Recognition and recording of significant signal parameter 

modulations. 

2 Recognition and recording of emitter radiation patterns. 

3. Recognition of aperiodic, "noninstructed" activity level 

events. 

4. Speed of acquisition and processing time per test intercept. 

5. Response to "system degradation" or "failure" modes of 

operation. 

6.1.6.4.3 Importance of Test. 

Automatic systems have certain inherent limitations, including: 

quantizing of intercept parameters, limited logic and possible loss of intelligence,, conserving data storage in long missions; need for frequent readout 

or recovery for wide-band analog data; sensitivity Joss to reduce false 

alarms; and tendencies to "lock up" program logic on strong or saturating 

signal conditions. 

Semi-automatic manned systems, although inherently limited by 

man's slow time constants and requiring visual/aural displays, have certain 

potential advantages: optimum adjustment of collection system controls; 

_ - 

lower false alarm threshold; recognition of anomolous signal characteristics; 

conservation of wide-band recording media; real-time adaptive redirection 

of mission objectives, and override of logic routines. 

SSM- 50A 

6-18 SECRET 

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SECRET 

6.1.6.4.4 Vehicle Requirements. 

Major Equipment 

Weight 

(lb) 

Volume 

(ft3) 

Power 

(w) 

Antennas 75 1.5 50 

Receivers 100 1.5 200 

Display console 200 3. 0 300 

Recorders 125 2.0 200 

500 8.0 750 

Vehicle stabilization of ± 0. 25° is required. Apertures may be 

required for control cables and possible mechanisms for erection and/or 

extension of antenna arrays. 

6.1.6.5 In-Space Maintenance - Experiment P-5. 

6.1.6.5.1 Objective. 

The objective of this test is to evaluate man's capability to 

perform malfunction detection, repair, and maintenance of complex mili-' 

tary peculiar equipments. 

6.1.6.5.2 Experiment Description. 

This experiment will be carried out in conjunction with Experiment P-4 equipments. The additional equipments include a malfunction 

detection panel for fault isolation, spares, appropriate tools and a portable 

checkout unit. 

The experimental procedure is to evaluate malfunctions of two 

types. One involves flight degradations which must be detected by the 

operator by noting erratic or substandard equipment performance. The 

other type involves complete failures of sequential elements causing major 

degradations in equipment operation. The operator on noting failure will 

detect the errant chassis with the malfunction detection panel and will then 

work down to the replacable modular elements with the portable checkout 

equipment. 

-SECRET- SSM-50A 

619 

This document contours Inlotmohon olNanio the nmwnal 0110,110 orthe Untied States wolun the mecmung of the E19.0.0Q. lows 

Title 18. U. S.0 . Section 793 and 794. the Irensensis$On of whet In ony monnef 10 On unOu1110.terf person a dioh.b.led by low 
NRO APPROVED FOR 

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--SECRET - 

Evaluation will be achieved by the astronauts maintaining 

maintenance records to be compared with mission success. 

The equipment is to be located so that a camera will take a 

series of pictures of the operation with time recording on each picture to 

allow for later analysis and comparison with ground and aircraft simulation 

data. 

‘: 4 

In addition to this specific maintenance experiment, it is 

'expected that other maintenance and assembly will be performed by the 

astronauts on basic spacecraft components and subsystems as a result of 

random failures. By incorporating the proper recording procedures considerable additional data relative to man's in-space proficiency for 

maintenance could be obtained. 

6.1.6.5.3 Importance of Test. 

In future military space missions one of the key factors in 

achieving economic feasibility and cost-effective operations is attaining 

high reliability of the necessarily complex military peculiar electronics 

equipment. If man can provide effective malfunction detection and effect 

repairs of these equipments with relatively few standardized replacement 

modules, then the inherent equipment reliability limitations will be overcome with the corresponding reduced operating costs. 

6.1.6.5.4 Vehicle Requirements. 

Weight Volume Power 

Malfunction Detection 

Panel 30 5.0 100 

Portable Checkout 

Unit 7 0. 2 Selfcontained 

Tool Kit 5 

Camera and Lights 20 1. 0 750 

62 6. 2 850 

SSM-50A 

6-20 -SEGRETThis document contort tnlotmot•on &lett •ot ono• oetrm. ce tt, Uric,, S ntrc A•t.,^ the meln.tici 01 the 

Lft. 13. U C Se0.0,, 793 and 794 the Itt:m.u.s,ot, of «0,h .ct tiny manner to on rnosilhor ',riff prison .s ptoh hard by Inw 
NRO APPROVED FOR 

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-SECRET6.1.6.6 Extravehicular Activity - Experiment P-6. 

6.1.6.6.1 Objective. 

The objective of this test is to evaluate man's ability in the 

performance of extravehicular operations peculiar to future military operations, including external spacecraft maintenance. 

6.1.6.6.2 Experiment Description. 

The basic equipment required for extravehicular operations 

includes: tetherlines, strap-on maneuver and control unit, and environment control system. In addition, task peculiar equipment, other than 

basic hand tools, will include those necessary to carry out the following 

tasks: 

1. Replacement Task (e. g. , solar cell). 

2. Connecting Task (e. g. , 2 fuel lines). 

3. Patching Task (e. g., external pressure patch). 

4. Retrieval Task (e. g. , recovery of ejected target). 

The test should be designed in such a manner as to minimize 

the astronaut hazards and to provide an evaluation of how effectively both 

tethered and untethered extravehicular activities can be carried out. In 

order to perform the extravehicular capability the astronaut must have his 

own environmental control system and a suitably designed spacesuit. It is 

essential that a measure of the difficulty of the task (i. e. , man's BTU 

output) be made so that environmental control capabilities and capacities 

can be established. The purpose of this experiment is to investigate locomotion, powered and unpowered. 

46 

First the tasks will be performed inside the laboratory to deter., 

mine life support and performance information. The conditions to be 

considered include: operation with and without the suit; various suit pres-. 

sures; different environmental system flow rates; tests with both astronauts, 

with and without the extravehicular ECS and maneuvering units(s); and 

various alternate procedures. 

-SECRET- SSM-50A 

6-21 

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-METAfter satisfactory completion of the above tests, the testing in 

space will proceed. The same information will be recorded as was in the 

in-capsule tests and photographs will be taken with a TV monitor as the 

astronaut proceeds through the air lock, moves over the exterior surface, 

operates while tethered, and performs with the maneuvering unit both 

tethered and untethered. The actual procedures used will depend upon the 

results obtained in ground and aircraft simulations as well as the experiments performed inside the spacecraft. The capacities of the extravehicular 

environmental control system and maneuvering unit will be set based on 

ground simulation and checked in the spacecraft before attempting space 

operations. 

. 6.1.6.6.3 Importance of Test. 

Extravehicular operations are important to future military 

space missions for providing external maintenance of spacea.raft which are 

resupplied and stay on orbit for long periods of time.' In ,addition, military 

peculiar equipments such as large radar antennae may require erection, 

alignment, and adjustment in space. In case of failures that preclude direct 

access through internal tunnels to the recovery vehicle, extravehicular 

capability may be needed for the 'safety of the astronauts. Also extravehicular activity may prove valuable for logistic reasons to allow the 

transfer of equipments, and rescue operations. 

6.1.6.6.4 Vehicle Requirements. 

The extravehicular equipment is estimated to weigh approximately 400 pounds, will require approximately 14 cubic feet of internal 

space and, while not directly requiring power, the lighting for the TV 

cameras, the operation of the TV cameras, and the recording will require 

about 1 kw of power. Vehicle stabilization is not critical, but should be on 

the order of 1 degree, and 0.01 degree/second to make egress and ingress 

simple and to ease the difficulty of performing the experiment tasks. The 

additional equipment will include a tetherline reel and exterior hand and 

footholds, and boom mounted TV capable of retraction into the vehicle. 

SSM- 50A 

6-22 -SECRET 

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Tote IS, U S C . Section 793 and 794, the Ottnvnit,.0. Of *hall in any manner to on enoutholoed person It ptohlb.led by Ion 
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SECRET 

6.1.6.7 - Experiment P-7. 

SSM- 50A 

6-23 

'rhos document contours informotoon affecting the notional detente 01 the United Stares within the meaning of the Espionage 1.0...1 

Title 18. U $.0 . Sect■ on 793 and 794. the transmission of which on any manner to on unoutholited person is proh,bired by In. 
NRO APPROVED FOR 

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SECRET 

6.1.6.7.3 Importance.of Test. 

6.1.6.7.4 Vehicle Requirements. 

SSM-50A 

6-24 SECRET 

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RELEASE 1 JULY 2015 

SECRET 

6.1.6.8 Autonomous Navigation - Experiment P-8. 

6.1.6.8.1 Objective. 

The objective of this group of experiments is to evaluate the 

capability of a man using various combinations of equipment to act as a 

spacecraft navigator and provide autonomous navigation. Results of this 

experiment will also comtribute directly to a more precise knowledge of the 

location of positions on the earth's surface. 

6.1.6.8.2 Experiment Description. 

These experiments are to be performed with a basic equipment 

. • . 

group consisting of a pointing and tracking scope (see Experiment P-1), a 

set of horizon scanners, a precision time reference system, two automatic 

star trackers, a general purpose, reprogrammable digital computer (see 

Experiment 1;1 1) and various prepared navigational data. Of this equipment, 

oily the star trackers are not available from the equipment used in other 

experiments. Additional pkovision for display, control, and computer 

access is only a minor additional equipment requirement which may place 

demand's on the arrangement of various instruments for convenient 

observation. 

The test procedure is extremely flexible. Many different experiments can be performed without any hardware change, however, two typical 

experiments can be described: In the first type, the classical orbit determination problem is duplicated in space. A specific and well known location 

on the surface of the earth is chosen and located with the pointing and 

tracking• scope. The astronaut trains the scope on this point on the ground 

as long as it remains- visible. Two navigation stars, chosen by the astronaut to suit the geometry of the problem, are located and the star trackers 

locked on to them. While the earth site is being tracked, a time history 

of the angular relationship between these stars and the site is recorded by 

the computer and these data are smoothed. An approximate orbit can be 

generated on the basis of these observations and a priori information 

relative to the general parameters of the MOL orbit. This function is 

SSM-50A 

6-25 

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performed again with another ground location and the data refined by well 

known methods of orbit determination. Once the orbit parameters have 

been estimated, the future position can be predicted and checked against 

observations. Unknown positions on the earth's surface can also be located 

precisely by reversing the tracking sequence, i. e. , from a known orbit 

position to a surface point position. 

The last possibility gives rise to a second type of experiment, 

essentially a refinement of the orbit whose parameters are known fairly 

well in advance but are gradually changing due to air drag or other poorly 

predictable phenomena. A .specific point is selected as a desired "over-fly" 

site. The orbital trace over the earth is estimated from on-board data and 

the time angular relationship of the local vertical and several check points 

are computed and predicted. As each check point is reached, the tracking 

and spotting scope is trained on it by the operator and angular data taken 

from the scope and the horizon scanners are fed into the computer. The 

small variations in the computed position from the predicted position are 

then used.to generate new orbit trace predictions. If the future predicted 

position is to be unsatisfactory, then the proper maneuver is computed, 

performed, and the process of iterated course checking is continued. 

The evaluation of the experiments will be made on several 

bases. The astronaut's tracking capability, ability to locate and lock on 

stars, and other mechanical functions will be evaluated. The ability of the 

astronaut to use his judgment for the navigation method required to suit 

his problem, to use the computer and its input/output displays, perform 

graphical checks on the digital computations can also be assessed as well 

as his total capacity to act as a spacecraft navigator, i. e. , determining 

future position, designing maneuvers to produce the desired trajectory, 

and to operate the spacecraft without ground support. 

6.1.6.8.3 Importance of the Test. 

The navigation and position fixing experiments are an important 

part of the general objective of achieving the full potential of autonomy of 

operation inherent in a manned spacecraft. The complex array of 

SSM-50A 

6-26 SECRET 

Ih.s document 3....• • n•-cnu oven, o• tl••••ed Sow, ts,,, the ,,eon.n9 of the Fto•o^oqe 

t S C 7?) .;• .24 nni• ..”•- rn(1^-r , to n.. 7.••t n. b b. 
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SECRET 

measurements and data reduction routines which are available can be mated 

to the situation at hand. The difficult problem of terrain feature recognition 

and tracking is not required to be automated, therefore the whole navigation 

problem can be solved with manned systems. 

This capability, if developed, will liberate future space military 

systems from the extremely costly and complex ground systems otherwise 

required. This freedom will permit the simultaneous operation of many 

spacecraft and rapid response to new situations without mission control 

facility improvament. Present estimates of the uncertainty of positional 

errors of certain areas of the earth's surface are as large as 2000 to 

.5000 feet. In many cases the positional location inaccuracy of potential 

military targets is greater than acceptable for the effective employment of 

the in-being missile force. As missile accuracies are improved and 

employment against hardened point targets increase, it is essential that a 

capability be obtained to reduce geodetic inaccuracies to the minimum. 

6.1.6.8.4 Vehicle Requirements. 

As previously stated, the basic new equipment requirement is 

for the addition of two automatic star trackers, and for display and control 

of the computer. The vehicle requirements are: 

Weight Volume Power 

(lb) (ft3) (w) 

Star tracker 

Console 

15 

_ 

50 

65 

3 

4 — 

7 

100 

100 

200 

6.1.6.9 Negation and Damage Assessment - Experiment P-9. 

Deleted by direction. 

--SEGREf SSM- 50A 

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T iht;se dioRcuurnecnt contains info. mohon affecting the notional ctetense at the United States with.n the meaning of the Espionage Laws 

C . Section 793 and 79u. the Itensmis,ion of which in any manner to on onouthotieed person n of oh.b.ted by low 
NRO APPROVED FOR 

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6.1.6.10 Multiband Spectral Observations - Experiment P-10. 

6.1.6.10.1 Objective. 

The objective of this test is to evaluate man's ability to detect 

high radiance gradient background events and missile signatures using 

multiband spectral sensors and to provide additional measurements data 

an backgrounds and missile signatures. 

6.1.6.10.2 Experiment Description. 

The basic test apparatus required is an optical system together 

with several plug-in detector assemblies to be used singly for measurements in the infrared or the ultraviolet. The four basic items are: 

• 

1. 

2. 

3. 

4. 

There are five parts to the test procedure for this experiment: 

1. Infrared Background Measurements. 

Regions of strong background returns are sought visually '- 

and observed using the spatial scanning array in appropriate 

wavelengths selected by the astronaut based on monitoring 

intercepted signal strength. 

2. Infrared and Ultraviolet Ballistic Targets. 

Using the appropriate detector and filter combinations, the 

astronaut tracks cooperative ballistic targets from boost to 

re-entry, if possible. 

3. Infrared Ground Mapping. 

Using the proper filter-detector-radiometer combination, 

the astronaut points the radiometer to the region of the earth 

to be mapped. The astronaut attempts to detect thermal 

structures produced by ocean currents and sea states, 

SSM-50A 

6-28 -SEMTh.s document conto,ns ,nlotmot.on ottect■ ng the no..ono■ oetense o• tne Un.ted Suet "Aho, the .eon.,,g of the E,n.0e0oe 10^, 

Tole 18. U.5 C . SechoA 793 and 794. the oonsnuwon of .uh,h nny monnet to on unouther•ted person .s ptoh•bard by Ina 
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RELEASE 1 JULY 2015 

harbor activities, shipping and wakes, air field activities, 

meteorological formations, geological formations, underground nuclear tests, and man-made structures such as 

missile sites and underground factories. 

4. Horizon Sensor. 

Again selecting the proper equipment combination, the 

astronaut scans the horizon spatially and spectrally to 

determine its sharpness for the best spectral response of 

the radiometer. Horizon position is determined for various 

azimuth angles, latitudes, sun positions, and weather 

conditions. 

5. Detection and Tracking of High Flying Aircraft. 

The astronaut attempts to detect and track high flying aircraft against the sunlit earth background.• The astronaut's 

functions in these tests are to: make measurements in 

regions of interest only, track targets, point scan across 

regions of interest, assemble and adjust the many possible 

equipment combinations, and calibrate and maintain the 

equipment. 

The targets will consist of missiles .cooperativel,y launched 

from aircraft, ships, and submarines deployed in predetermined target patterns. 

6.1.6.10.3 Importance of Test. ••• 

The MOL provides a unique opportunity to measure the radiation 

from missiles under the most adverse earth background conditions without 

burdening the system with nonessential data. The manned function will be 

performed under conditions similar to those that would be encountered in 

future manned satellite launch detection and space based AICBM systems. 

The earth background and ballistic target measurements are- of crucial 

importance also in sensor development for future launch detection and 

space based AICBM systems. The horizon radiance data could allow 

development of more accurate horizon sensors. 

SSM-50A 

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RELEASE 1 JULY 2015 

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6.1.6.10.4 Vehicle Requirements. 

The spectral measurements equipment are estimated to weigh 

350 pounds, require 12 ft3, and use up to 300 watts of power. Stabilization 

required is 0. 5 and 0.01 deg/sec. 

6.1.6.11 General Performance in Military Space Operations - Experiment P-11. 

6.1.6.11.1 Objective. 

The objective of this test is to obtain reliable and valid 

measures of man's basic performance as it relates to applied mission 

functions and physiological changes occurring during the stresses of the 

MOL flights. 

6.1.6.11.2 Description of Experiment. 

The equipment required is a standard test battdry constructed 

either as a separate package or as part of specific subsystems. The use of 

standard tests will allow comparison of the in-space performance against 

statistically significant ground performance data. 

The test procedure is to have the crew perform the procedures 

designed to measure such basic psychological functions as visual acuity, 

auditory acuity, monitoring and processing information from dynamic 

processes, mental computation, perceptual discrimination, decision 

making, and three-dimensional tracking. It is desirable for these tasks to 

be measured at various times of the day and with respect to changes in 

workrest cycles. 

The evaluation will make use of extensive ground simulation 

and analysis to provide reliable measures of behavior against which to 

compare in-flight results. 

■ 

SSM-50A 

6-30 SECRET 

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RELEASE 1 JULY 2015 

SECRET 

6.1.6.11.3 Importance of Test. 

Whereas measures of applied military functions performed in 

the other primary experiments permit a gross evaluation of man's basic 

performance capabilities, the proposed test battery should provide: 

1. Indications of possible performance degradation in more 

extended flights not evident from physiological changes 

(performance and physiological measures usually do not 

show high correlations). 

2. Comparison against possible degradations in the applied 

mission functions which do not clearly indicate the possible 

causes for such degradation. Variables such as overloading, the intangible effects of prolonged weightlessness 

and confinement, and changes in performance associated 

with diurnal variation may be analyzed with respect to 

degradation of specific aspects of man's abilities and the 

subsystem loop of which man is an element. 

6.1.6.11.4' Vehicle Requirements.. 

The test and recording equipments are estimated to weigh 

15 pounds, requiie 1/4 ft3volume, and 20 watts power. 

6.1.6.12 Biomedical and Physiological Evaluation - Experiment P-12. 

6.1.6.12.1 Objective. 

The objective of this test is to evaluate those effects of weightlessness which can potentially compromise mission success. Sufficient 

data are required to validate supportive measures employed, devise 

improved methods, if necessary, and afford plausible estimates of biomedical status for missions longer than 30 days. 

6.1. 6.12. 2 Description of Experiment. 

By taking full advantage of pre-flight and post-flight studies, 

as well as all previous manned orbital flight experience, the only tests to 

be conducted during flight are those which fulfill the necessary and sufficiency statements given in the Test Objectives. Measurements will be 

SSM- 50A 

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Tole 18 U S C . Sechon 793 ord 794 the uon,m,...on of Nh,ch nny monnet to On vnnuthIV.ter1 oet,On otoh b.ted by low 
NRO APPROVED FOR 

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made of the following functions considering the effects of weightlessness, 

environmental loads, and body demands: (1) blood volume, pressure and 

flow; (2) the electromechanical behavior of the heart; (3) fluid and electrolyte levels and balance; (4) gastro-intestinal function and nutritional status; 

(5) metabolism of selected body materials, e. g., calcium and protein; 

(6) respiratory mechanics and rate of energy metabolism; (7) nervous 

system functions, e. g. , muscle strength and coordination, general mental 

status. Important associated environmental parameters will be measured, 

including physical and tissue equivalent radiation measurements. The 

experimental equipments will consist of the following: 

1. Sensors for electrical, mechanic.al, and chemical measurements, signal analyzers and converters, data recording 

and storage systems. 

2. Equipment for selective data transmission. 

3.. Voice communication equipment. 

4. Real time TV or motion picture recording if feasible. 

Typical procedures include donning a vest with sensors and 

leSds, • switching on recording systems, and monitoring results to assure 

adequate recording; recording fluid and food intake; measuring and record- 

• ing urine output and preserving samples for subsequent analysis; performing 

• simple chemical (spectrophotometric and electrode chemistry) determina-

. 

tions on urine and occasionally on blood. Specific sequence of procedure 

will be determined by ground-based studies and simulation in Pre-phase I 

and Phase I. These procedures will be carried out by giving one member 

of the crew the requisite training to conduct all the tests in a reliable 

manner. 

Evaluation will be accomplished by partially interpreting results 

in real time both during flight and through transmission of selected data to 

ground. Quantitative data obtained are directly and unequivocally translated 

into meaningful evaluation of normality or deterioration in physiologic 

status of the astronauts. Other data along with pre- and post-flight data 

will be used to evaluate overall results, devise subsequent test plans, and 

guide future flight procedures. 

SSM- 50A 

6-32 SECRET 

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RELEASE 1 JULY 2015 

SECRET 

6.1.6.12.3 Importance of Test. 

The physiological effects of long term weightlessness can be 

predicted to some extent qualitatively, but cannot be determined quantitatively with an adequate level of confidence through ground-based studies. 

The MOL 30-day flights presume prior 14-day weightless NASA flights; 

while these add some applicable data and an additional level of confidence, 

they do not eliminate the requirements for tests during the 30-day MOL 

missions. The measures proposed reflect a reasonable concern for both 

the astronaut's health and the need for his support to ensure mission 

succe ss. 

The mission profiles and manned operational modes envisioned 

for useful military applications (e. g., in enhancing reconnaissance capabilities) require that the crew be maintained in good physiological status. 

Tests are essential to establish that such status, in fact, exists. The 

severe configuration and operational constraints of providing an artificial 

gravity implies that it is mandatory to secure the type of test•data indicated. 

Such data will serve to devise improved preventative measures - short of 

artificial gravity - or for a major decision to employ some gravity mode. 

6.1.6%12.4 Vehicle Requirements. 

• The biomedical test equipment is estimated to weigh 260 lbs, 

require 12 cu ft ov volume, and take an average 30 watts of power with peak 

load of 300. 

The omnidirectional proton, electron, and alpha spectrometer 

should be mounted externally or extended from the unpressurized compartment ddring operation. In the cosmic ray emulsion experiment, an aperture 

must be available through which emulsions can be extended and exposed for 

predetermined periods of time. 

-SECRET- SSM- 50A 

6-33 

Th., (Ohio, °^e° ng •-e U- .en S•n'es he eneon•ng 'he ha 0^0.71e 

the 18. U 5 C . Sect, 793 and 794 the s. a- of f.^♦ n•0^'l• to v^o.,he• Zen sc.'s. 5s,s6 a •e0 by 
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RELEASE 1 JULY 2015 

SECRET 

6.1.7 Experiments versus Missions & Applied Functions. 

In order to provide a graphical assessment of how well the primary MOL experiments will provide a measure of man's utility in critical 

applied military mission functions, Table 6-2 has been prepared. All functions will be explored by at least one experiment, and in many cases several 

experiments will be performed including the same function, thus allowing 

evaluation under a variety of conditions. 

Table 6-3 indicates those experiments that support mission 

revirements. 

6.1.8 Secondary Experiments. 

The following secondary experiments are not meant to be allinclusive, but are considered representative. Unlike the primary experiments, the secondary experiments are not considered essential to accomplish 

the basic objectives of MOL. As they do have potential military mission 

value or are of scientific importance, they warrantconsideration for potential testing in MOL. Hence they should be continually assessed for mission 

value, status of development and definition and vehicular interface effect. 

S-1 VLF Communication-Propagation Experiment 

S-2 Secure Communcations Using Narrow Beams 

S-3 Laser Propagation Experiment 

S-4 High Frequency Ionospheric Ducting Communication 

S-5 

S-6 Expandable Structures Techniques 

S-7 Antenna Deployment, Alignment and Pointing 

S-8 Space Rendezvous Radar 

S-9 

S-10 Mapping and Geodetic Survey for Identified Points 

S-11 Determination of Mass 

S-12 Hydrogen Reduction Atmospheric Regeneration System 

S-13 Vapor Compression Distillation Water Purification System 

SSM-50A 

6-34 SECRET 

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RELEASE 1 JULY 2015 

S-14 Passive Propellant Settling Systems 

S-15 Coherent E-M Propagation and Antenna Loading 

S-16 Solar X-Ray Warning System 

S-17 Materials Degradation and Malfunction Analysis 

S-18 Astronomical Photography 

A summary description of the secondary experiments is 

included in Section 20. 

6.1.9 Summary of Vehicle Requirements. 

The following is a summary of vehicle requirements which is a 

composite of the individual experiments. The weights include all equipments; the volume is only the estimated equipment volume inside the MOL 

environmental module; the power is the maximum single power requirement 

assuming none of the experiments will run simultaneously. The stabilization was divided between fine and coarse because the experiments basically 

fell into two categories. Maneuvering propulsion is a gross estimate set by 

Experiment P-2.• On flights on which this experiment is not to be performe, 

a 200-foot/ sec AV will be adequate. 

6.1.9.1 Summary of Primary Experiment Vehicle Requirements. 

Weight Volume Power Stabilization Maneuvering 

(lb) (ft3) (w) (deg) (deg/ sec) (ft/ sec) 

2712 78 1000 0.1, 0.001 2000 

Fine 

0. 5, O. 01 

Coarse 

6.1.9.2 Summary of Secondary Experiment Vehicle Requirements. 

Weight Volume Power Stabilization Maneuvering 

(lb) (ft3) (w) (deg) (deg/sec) (ft/ sec) 

3000 104 1.8 0.5, 0.01 200 

SECRET SSM- 5 0.A 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECRET 

6.1.10 Summary of Simulation Requirements. 

The basic philosophy to be employed in the MOL Experiments 

Program is to make maximum use of ground and aircraft simulations and 

use MOL space testing as a selective verification and proof testing. The 

simulation program will include elementil human performance laboratory 

simulations, combined man and equipment laboratory and aircraft simulations, complete flight test simulations in ground environmental chambers, 

and possibly an aircraft simulation for zero n ig" with a complete station 

mock-up. The immediate problem is the necessary Pre-Phase I elemental 

simulations to determine feasibility and provide basic design data for the 

experimental equipments. These simulations include both proposed funded 

contractor efforts as well as in-house programs. The contractor efforts 

are: 

Simulation 

Experiment Estimated 

Number Go'sts 

Target Acquisition & Tracking P-1 Included in 

Study, ref. 

F1'aragraph 

3.3.1.2.1 . 

The in-house simulation effort will include: 

Simulation 

Experiment 

Number Organization 

General Performance Test P-11 AMD 

Battery 

Biomedical Test Sequence P-12 AMD 

6.1.10.1 Target Acquisition and Tracking Simulation. 

The basic data derived from this ground simulation will be used 

in the design study of the pointing and tracking scope and possibly could be 

performed by the same contractor. The tasks and the basic data to be 

determined are: 

1. The proper magnification, fields of view, and scan rates 

for target detection/acquisition. 

SSM-50A 

6-38 -SEW+ 

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NRO APPROVED FOR 

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2. The preferred manual techniques for target reacquisition 

after discontinuation of automatic scan mode. 

3. The preferred magnifications for precise tracking. 

4. The desirable design approaches and techniques for precise 

tracking. 

6.1.10.2 Electromagnetic Intercept Feasibility Simulation. 

This simulation consists of using existing aircraft and flying 

over a specifically prepared target pattern at V/H values that would approximate space operations. The critical aspect of space electromagnetic 

intercept is the short time the operator has for his real time analysis, tuning 

of sensors, and recording. The aircraft, pilots, and equipment operators 

would be presently trained Air Force personnel, and the study effort would 

consist of the following: 

1. Assessment of control and display functions analogous to a 

potential MOL console. 

2. Determination of suitable flight test areas providing proper, 

emitter targets. 

3. Layout of a test matrix embodying the proper parameter 

variations. 

4. Decision on type of operator selected for testing. 

5. Test plan for flights and ground coordination. 

6. Evaluation procedures capable of being extended to future 

simulations in other modes. 

6.1.10.3 General Performance Test Battery Simulation. 

This simulation will be accomplished by the Aero-Medical 

Division and will primarily involve simulating conditions in MOL and 

determining a test battery procedure which can provide adequate results 

but not require large amounts of time. 

-SECRET. SSM-50A 

6-39 

Tht, document cantons fOlotmolroo dieting the •,01.ono. ae,ense o, ,he Untted Stenos Attl,n the meon.ng of the hnt...,,g" Ions 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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6.1.10.4 Biomedical Test Sequence Simulation. 

This simulation work will be accomplished in-house by the 

Aero-Medical Division and include simulation of all biomedical tests in 

realistic sequence in a MOL environmental mock-up to establish test 

validity, equipment modification and location, and task-time requirements. 

The radiation measurements will also be simulated as part of the biomedical 

experiment. 

6.1.11 Summary of Funded Definition Studies. 

All selected primary experiments must be defined during the. 

Pre-Phase Iperiod to an extent that will allow preparation of an experiments 

interface document which can be supplied to the MOL Phase I vehicle 

contractors, and in addition allow for preparation of Phase I equipment 

RFP's that can be used for the selection of sensor contractors. These 

proposed funded contractor studies consist of the following: 

Experiment Estimated 

Study Number Cost 

Image Velocity Sensor P-1, P-2, $360, 000 

Subsystem P-3 

Manned Electromagnetic P-4, P-5 $180, 000 

Signal Detector Experiment 

Autonomous Navigation P-8 $100, 000 

Multiband Spectral P-10 $125, 000 

Observation 

All of these studies would be carried out under SSD management. 

The responsibility for the in-house studies to define the remaining experimental areas in support of SSD, the lead division in the MOL program, are: 

P-6 

P-7 

P-11 

P-12 

Experiment 

Extravehicular Activity 

General Performance in Military 

Biomedical and Physiological 

Evaluation 

Responsibility 

RTD 

RTD 

AMD 

AMD 

SSM-50A 

6-40 - 

Th., doc„...., contains informofion oflect.no the matrons,' octets* or the Witted Stoles *Ain the rweontng of the Esp.onoge tont 

Title 18. U.S.C.. Section 793 and 794, the ttansrntsston of which at any manner to an unouthor.yed person .1, ywohibttecl by In* 

-SEeRET- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-S-E-REf6.1.11.1 Pointing and Tracking Scope Study. 

While the concept of manned tracking for precise IMC determination has been explored in sufficient depth to establish general validity, it 

is particularly important to conduct a study to provide more definition for 

the experimental IMC subsystem. Included in this subsystem study are the 

direct viewing, pointing and tracking telescope, the tracking servo, the 

coupled camera, and the general purpose computer requirements. The 

importance of this subsystem is evident in that it is the primary instrument 

in four of the primary experiments and directly used in three others. The 

proposed contractor study will include consideration of the following: 

1. Pointing and tracking scope optical configuration. 

2. Coupled camera and film processing equipment design. 

3. Tracking servo system analyses and design. 

4. IMC computational requirements and associated computer 

specifications. 

. 5. . Vehicle interfaces. 

6. Functions of man with respect to set-up, operation, and 

maintenance of the IMC subsysteni. 

6.1.11.2 Electronic Intercept and In-Space Maintenance. 

A study of the electronic intercept equipment is necessary as 

this equipment will place a significant interface requirement on the vehicle. 

The study will include the following tasks: 

1. Optimum Orbit and Antenna Patterns. 

This task will explore the orbital inclination, altitude, and 

repetition pattern most suitable for conducting this experiment. 

Ground range availability, including sea-borne targets, and 

emitter choices consistent with simulation testing are to be 

studied. Antenna patterns will be explored for highest acquisition probability, spatial clutter filtering, location fixing, and 

gain. 

SSM-50A 

6-41 

Th., document canto's infotmolion offechno the nohonot °vette of the Untied Suet *ohm the theonmo of the flotonooe ton% 

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NRO APPROVED FOR 

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2. Study of Spaceborne Display Systems for Rapid Recognition 

of Signal Modulation Variations. 

The console for the MOL operator will be limited in size 

and weight. It is of great importance to be able to present 

displays emphasizing departures from simple non-varying 

signal modulations. Consolidation of display and/or correlative 

displays should be studied for possible improved presentation 

systems. 

3. Study of Recording, Storage, Readout, and Recovery of 

Selected Intercept Data in MOL experiments. 

This task is directed to analysis of the quantity of data to 

be taken and its digestion and manipulation in the testing of the 

operator's activities. Attention is directed to recording and 

storage time necessary, bandwidths, status, and monitoring 

recording. This study is interrelated with the general problem 

of on-orbit test reporting and would provide inputs to that effort. 

4. Maintenance Analysis of Military Electronic Equipments 

This task is directed at determining, the most probable 

types of malfunction and will form basic input to Task (5). 

5. Conceptual Design of the Malfunction Programmer, 

Malfunction Detection Panel, and Checkout Unit. 

6. Establishment of Vehicle Requirements. 

6.1.11.3 Autonomous Navigation Study. 

Many navigation and space position fixing schemes have been 

proposed for this experiment. A study is required. which will identify the 

techniques which would be applicable, make a comparative analysis of the 

approaches identified and select the most promising ones for Phase I 

consideration. 

For the selected navigation experiments an analysis of system 

requirements based on a preliminary system design will be accomplished to 

insure that equipment which must be shared with other experiments can be 

SSM- 50A 

6-42 -SEMTh“ document cartoon, .nformotoOn ofICO■ ng 0`e at'enie n .eie 1-1"..,Ctl Sieve, ...th.n the meaning of the Fip•of,nete 

title ,EI 11 S C Section 797 and 791 the lianym.,,ion mann, tonn unnutha• red ae,ion hied by ,r1. 
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4E0Edeveloped with an adequate appreciation of the requirements imposed by 

the navigation experiments. 

The star trackers, a unique requirement for this experiment, 

will be the subject of a survey of existing equipment to identify suitable 

hardware for Phase I study. 

A preliminary experiment opeiational plan will be developed in 

order to have the data required for experiment integration and task analysis. 

Similar data will be generated for ground equipment requirements. 

6.1.11.4 Multiband Spectral Observations. 

Much effort has been expended on spectral measurements 

equipment for missile and background measurements; however, the 

previous work was done for unmanned approaches using narrow 'spectral 

filter bands. This experiment will be tlie. first test of wide band UV/IR 

detectors under complete control of a manned operator and thus the study 

will be oriented to evaluating the man and make maximum use of the man 

for the acquisition spectral signature data. 

The proposed contractor's study will include the following: 

1. Experiment equipment requirements definition. 

2. Survey existing equipment suitable for adaptation to the 

MOL. 

3. Selection of detectors for appropriate spectral zones. 

4. Investigation of cryogenic cooling systems. 

5. Filter insertion mechanisms design. 

6. Definition of the optical system. 

7. Data recording, handling, and reduction definition. 

8. Mission Test Profile and astronaut duty cycles study. 

9. MOL installation and operational interface considerations. 

10. Manned functions in the test operation. 

11. Control and console design requirements. 

12. Target requirements definition. 

13. Checkout equipment, AGE, and launch facilities definition. 

-SECRET- SSM-50A 

6-43 

Th•t document cont.", .nlotmnhon offechng the not.OnOt neeme CO the United Stnte, n.th.n lb, nrnn.n,l of the f4hOnone out 

Lne 19, U 5 C . Section 793 nn el 794 thy tonnsrn,,,nn of «her h nny manner tonn vnn,,n” ,nn.„, • br 
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6.1.12 U. S. Navy Package. 

Numerous proposals for experiments by a number of Navy 

activities have been included, either directly or indirectly, in the MOL 

program plan as it appears to this point. This was possible because all 

proposals from Navy activities were submitted directly to USAF, Space 

Systems Division for consideration as MOL experiments. Simultaneously 

with this submission, an identical submission was made to a technical panel 

convened by the Bureau of Naval Weapons to examine the specific naval 

interests in a manned space program. 

From the recommendations of this technical panel, the.Bureau 

of Naval Weapons in turn submitted to Space Systems Division its recommendations for Navy participation in the MOL program (see Reference 14.2.4, 

U. S. Naval Research Laboratory Memorandum Report #1507, Manned 

Orbital Laboratory Technical Panel, First Preliminary Report, 17 March 

1964.) The Navy 'concept, which is described in Section 18, provides for 

aaiintegrated ocean surveillance experiment as its primary ingredient. 

It includes other specific experiments in communications, satellite surveillance and detection, ELINT, bioastronautics, and general science. Of 

these experiments, most have already been included in the list of primary 

and secondary experiments as a result of direct submission to SSD. 

Howevek, further review is required to insure complete integration of the 

Navy requirements. 

To provide a more detailed definition of the Navy experiment 

package, an early series of pre-PDP studies is planned by the Navy. For 

the integrated ocean surveillance experiment, for example, a study has 

been initiated for this purpose. In this study, the experiment will be 

analyzed in detail to effect proper technical consideration of all sensors, 

to establish the necessary and preferred relationships of sensors to each 

other and to ancillary equipment, to identify the technical and human interfaces, and to establish performance criteria for measurement of effectiveness. A thorough analysis including these factors and others will be 

attempted for all experiments in the Navy package. It is possible that new 

or modified proposals may result. 

SSM-50A -SECRET- 6-44 

This document contains information ollecting the notional °Cense of the United States within the meaning of the Espionage I. or.% 

Title 18. U.S.C., Section 793 and 794. the transmission of which in any manner to on unauthorized person is proh,bocrt by 
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4EGRH6.2 MISSION PROFILE. 

The MOL flights will be conducted from the Titan III launch complex at Cape Kennedy. Upon achieving orbit, the astronauts who are located 

in the Gemini B during launch will prepare to transfer to the Laboratory 

Vehicle by conducting a checkout of the essential Laboratory subsystems 

from the Gemini and by activation of those Laboratory subsystems which 

must be in operation during the transfer. Several methods of astronaut 

transfer from the Gemini B to the Laboratory Vehicle are under investigation. Upon entering the Laboratory, the astronauts will proceed to activate 

the remaining Laboratory subsystems and place the Laboratory Vehicle 

subsystems in a fully-operating condition before removing their space suits. 

The flight crew will be the primary source of on-orbit decisions. Astronaut 

functions will include monitoring and, if necessary, controlling vehicle subsystems operations. Status of subsystems in the Gemini B essential to safe 

return will particularly be checked. Data from the experiments, as well as 

telemetry of orbiting vehicle condition and astronaut physiological functions 

will be transmitted from the Orbiting Vehicle to ground receiving stations. 

Laboratory activities will be monitored and communication with the astronauts will be conducted on the ground from the Mission Control Center. 

Upon completion of the 30-day mission period, the astronauts 

will perform final checks of the condition of the Gemini capsule and activate 

those systems required for crew transfer. They will then put on their space 

suits, deactivate certain subsystems in the Laboratory, and transfer to the 

Gemini. After separation from the Laboratory Vehicle the Gemini capsule 

will be oriented for the retro-firing maneuver. Following re-entry into the 

atmosphere and deceleration of the capsule, a parachute will be deployed to 

lower the capsule to a water landing. 

During the entire mission, emergency abort provisions must be 

made for crew safety in the event of a malfunction. On the launch pad and 

during launch, abort will be possible by means yet to be finally selected. 

During the on-orbit period, abort may require re-entry and landing in an 

emergency recovery area. An emergency recovery force (probably serving 

SSM-50A 

6-45 

This document contains intotmohon ollechng the national oetente at the United Stoles stniihtn the meaning of the Esp.onoge tow, 

Tait 18. U.S.C., Section 793 and 794. the treninusston of whoa, .n any manner to on unouthot.ted person es ptohtbded by tow 
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both NASA and Air Force programs) will be deployed for emergency 

recovery operations. 

6.3 VEHICLE SYSTEM. 

In order to combine enhanced reliability and safety with minimum 

cost and time for development and test, adaptations of the standard Titan 

MC Launch System and of the Gemini to meet MOL requirements will be 

held to a minimum by deliberate design. Also, Gemini subsystems which 

give the NASA Gemini orbital autonomy not necessarily required by the MOL 

application will be considered for adaptation to the MOL Orbital Vehicle to 

take advantage of the development and test which these components will receive under the NASA program. Examples are: the Gemini Environmental 

Control System; the Gemini Orbital Attitude and Maneuvering System; the 

Gemini Inertial Guidance System; and the Gemini Rendezvous System. 

Furthermore, the Titan III transtage is also being considered for adaptation 

to service as an orbital attitude and maneuvering system for the Orbiting 

Vehicle. 

The subsections which follow (subsection 6. 4 through 6. 6) 

describe the major configuration alternatives still being considered for the 

Laboratory Vehicle, the Gemini B, and the Titan Specific in-house 

MOL Vehicle studies (in progress since the MOL Program was announced in 

December 1963) augmenting earlier, more generalized studies and studies by 

industry and NASA on similar vehicle concepts, have narrowed the field of 

configuration alternatives to the few leading candidates in each subsystem 

area which are discussed below. These in-house efforts will continue, 

materially aided by the Pre-Phase I studies by McDonnell on the Gemini B, 

and Martin on the Titan IIIC MOL Launch System together with selected 

Laboratory Vehicle subsystems studies. Final decisions on some configuration questions will be made prior to issuance of the Labordtory Vehicle RFP. 

Others, especially those which cannot be made independently of the Laboratory Vehicle configuration, must await the concerted definition effort of 

Phase IB. 

SSM- 50A 

6-46 

This document contains inlermohan of fect.ng the nOt■ Onol detente at the United Stales within the meaning of the Espionage Laws. 

Tale 18. U S C . Section 793 end 79e. the transrnisiion of which in any manner to on unauthoi.zed ',Men is prohibTed by law 
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6.3.1 Orbiting Vehicle (OV). 

The Orbiting Vehicle will consist of Gemini B, a Laboratory 

Vehicle (probably consisting of a pressurized Laboratory Module for the 

crew and some experiments, and a.Test Module for other experiment installations) and possible the transtage for on-orbit propulsion requirements. 

A representative Orbiting Vehicle might have a weight distribution as follows: 

ELEMENT WEIGHT (lb) 

Gemini B plus Adapter 6, 000 

Laboratory Vehicle (Pressurized 5, 910 Laboratory 

Test Module (Unpressurized) Vehicle 1, 150 

Experiment Payload Available 5, 940 

Weight Contingency 2, 000 

SUBTOTAL 21, 000 

Dry Transtage (If Retained on Orbit) 4, 300 

TOTAL 25, 300 

VThe Gemini- B weight includes only the re-entry capsule and its 

adapter without an autonomous on-orbit capability. The Laboratory Vehicle 

includes a pressurized Laboratory Module, an unpressurized Test Module, 

and an experiment payload. The transtage is presumed empty of propellants. 

Any propellants retained for orbital maneuvers must come out of this experiment payload budget. 

A 2000 lb. contingency has been provided for possible weight 

growth of the Orbiting Vehicle. There is another 2000 lb. contingency for 

any reduction of the Titan IIIC performance capability. Titan LUC is estimated to provide a 23,000 lb payload to a 200 n. mi. orbit at inclinations of 

about 30 degrees. - If the 5940 lb available for experiments is completely used 

for on-orbit maneuvering with transtage, 2500 ft/sec can be provided. A 

trade-off appears available for maneuvering experiment requirements vs. 

non-maneuvering experiment requirements. 

-SEGREfSSM-50A 

6-47 

This document contains information effecting the notion°, oetense at the United States within the meaning of the Espionage Laws 

Title le. U.S.C.. Section 793 and 794. the trensmtssion of which in any manner to on unauthorized p.rson ,s orohibded by low 
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---E-RET6. 4 LABORATORY VEHICLE. 

6.4.1 Structural Arrangement. 

A typical Laboratory Vehicle will consist of a modular structural 

arrangement comprised of a pressurized crew liiring/working area or 

Laboratory Module and an unpressurized equipment module or Test Module. 

Figures 6-2 and 6-3 illustrate Laboratory Vehicles with single and dual 

pressurized compartments. 

Mission experiment monitor and controls equipment will be installed in the aft section to permit cr -nr-ktible interfacing of components with 

the test module. Life support and oilier .;;-stems will be grouped for optimum space utilization, accessibility, and functional compatibility. Exterior 

equipment arrangements may include solar panel assemblies, side-looking 

radar antenna, communications and tracking antenna, attitude control 

reaction nozzles, and thermal control radiators. A constraint on vehicle 

geometry is the requirement for adequate living/working volumes. A design 

goal of 200 cubic feet of free volume per abtronaut'has been adopted for 

design plannifig. The probability of crew survival may be increased by 

separation of the crew volume into two pressurized compartments. Design 

goals for dual compartmentation may entail significant weight penalties, and 

the trade between system performance and astronaut safety increment must 

be made within the context of overall system safety goals. 

The Titan MC transtage diameter of 10 feet establishes a minimum desirable Laboratory diameter. Use of a larger Laboratory diameter 

involves increased aerodynamic buffeting loads, but provides a decreased 

system length which tends to minimize potential problems connected with 

launch vehicle strength and dynamics. 

The structural configuration will probably consist of a foamfilled aluminum truss-core sandwich. This approach combines effective 

strength and environmental protection capabilities. 

Final configuration of the Laboratory Vehicle will await the 

results of the Laboratory Vehicle contractor's Phase IB effort. 

SS

48

M-50A SECRET 

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SECRET 

SSM-50A 

6-50 

This document contains information collecting thy Rattan.% OHM. 01 the United Shoes within The mooning of the Espionage Lows. 

Title 18, Section 793 and 794, the transmission ol which in any manner to an unauthorixed person is prohibited by low 
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SECRET 

6.4.2 Astronaut Transfer. 

Alternative astronaut transfer methods include deployable tunnel, 

inflatable tunnel, hatch-to-hatch (Gemini rotation), hole-through-heat shield, 

and extra-vehicular (see Figure 6-4). Evaluation criteria include reliability, 

crew safety, weight, development time and cost, impact upon Gemini B and 

Laboratory Vehicle, and compatibility with system growth including docking 

and space maneuvering. 

The external inflatable tunnel-is emerging as a particularly promising method for crew transfer. This tunnel would connect the Gemini B 

crew access hatch to the Laboratory Vehicle through a porthole in the Gemini 

B adapter assembly. Emergency access to the pressurized compartments 

may be obtained through a tunnel in the Test Module. Structural and space 

provisions could be made for a universal docking and mooring mechanism 

on the aft end of the Test Module section. 

The subject of astronaut transfer will continue to be pursued inhouse, particularly from the Laboratory Vehicle standpoint, and is the 

subject of a major task in the McDonnell Pre-Phase I contract. A decision 

will probably be made before the Laboratory Vehicle RFP is released to 

industry. 

6.4.3 Environmental Control. 

Trade-off studies to date favor an atmosphere control system for 

the Laboratory Module consisting of (1) a 7. 5 psia 50% oxygen/50% nitrogen 

atmosphere, (2) temperature control by way of a heat exchanger, (3) carbon 

dioxide absorption using a silica gel-molecular sieve and (4) trace contaminant removal by absorption and catalytic burning. Subcritical cryogenic 

storage appears desirable. The life support system for the Laboratory 

Module must include (1) food provisions, (2) disposal of waste, (3) hygiene, 

and, probably (4) water-recovery. However, the adaptation of two Gemini 

life support systems is also being considered. This 5. 0 psia all-oxygen 

system has the very real advantages of simplicity and proof through development and space use by NASA. However, it is considerably heavier and its 

SSM- 50A 

6-51 

This document contains information affecting the notional amense or the United States within the meaning of the Espionage Laws 

Title IS, U. S C , Section 793 and 79e. the transmission el which in any manner to On toroulhoirzed perrrn is prahrhited by In. 
HATCH IN GEMINI HEAT SHIELD INFLATABLE TUNNEL 

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SECRET 

SSM— 50A 

6-52 SECRET 

This document conforms inlorrnolion ollecting the norionot oetense of the United Stoles within the intoning of the Espionope tow, 

Title IS, U.S.C., Section 793 and 794, the transmission of which in any mann.er to on unoethoiited person is Prohibiled by low 
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RELEASE 1 JULY 2015 

-BRETsafety aspects for MOL use are still under investigation. A final decision 

will probably await participation by the Laboratory Vehicle contractor. 

Artificial gravity is not planned as a feature of the MOL System. 

However provisions for exercise, including measures which provide selfinduced accelerations are being studied for inclusion in the Laboratory 

Vehicle. 

S.4.4 In-Space Maneuvering. 

This topic applies to the entire Orbiting Vehicle. It includes 

maneuvers in orbit required by experiments and maneuvers to effect 

rendezvous and docking. For either purpose, the transtage presents a 

"ready-made" propulsion capability. It must be adapted to these uses by 

providing pilot-in-the-loop provisions involving displays in the Gemini B 

or Laboratory cockpit and controls leading from the Gemini to the transtage. 

Investigating solutions to this requirement is an item in the McDonnell PrePhase I study with Martin support. The transtage presently is capable of 

only a few restarts, and would require improvement in this respect. An 

altetnite approach to using the transtage would be to add low level thrustors 

to the Laboratory and separate the transtage at orbital injection. 

A requirement for docking provisions may be imposed on the 

Laboratory Vehicle design as a result of astronaut rescue and/or system 

growth considerations. Feasible docking alternatives include tail-to-tail, 

nose-to-nose, and side-by-side (see Figure 6-5). Evaluation criteria include ease of cargo transfer, ease of vehicle approach maneuver, drag 

area presented by docked configuration, and design implications on the 

Gemini B and Laboratory Vehicle. 

The degree to whicl "provisions for" rendezvous and docking will 

be built into the initial version of the MOL Vehicle and ground systems is 

still in the early investigative stage. 

Rescue, a topic bearing on this issue, is to be studied during 

Pre-Phase I contract study activity, with coordinated inputs by Martin and 

McDonnell. Furthermore, as an aid to deciding the degree to which 

SECRET SSM- 50A 

6-53 
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TAIL TO TAIL 

acT NOSE TO TAIL 

a. 

(GEMINI ROTATED) 

TAIL TO TAIL 

he, .41 

MEM EMI 

SIDE BY SIDE 

Figure 6-5. Docking and Mooring Concepts 

SSM-50A 

6-54 SECRET 
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rendezvous and docking should be incorporated initially, trade-off studies 

balancing the cost in dollars, weight, and complexity of incorporating elements of the rendezvous and docking system initially against the cost in 

dollars and time to incorporate it later will extend into Phase IB. 

6.4.5 Crew Duty Cycle. 

Crew duty cycle, task priorities, and physical capabilities and 

limitations under Orbital Laboratory conditions directly influence Laboratory design in the following primary areas: reliability, safety, availability, 

and the trade-off between redundancy and maintenance. These in turn influence system weight, volume, operational flexibility, and cost. Bioastronautic experiments are expected to be primarily manual. Military experiments will probably be semiautomatic, and will be designed to take advantage of astronaut capabilities for calibration, selection, monitoring, and 

partial control. 

The following general times may be assigned to those items not 

related directly to the performance of the specific MOL mission. The times 

assigned are based upon a 30-day or longer mission. 

A representative crew duty-cycle is shown in Table 6-4. 

Table 6-4. Representative Crew Duty Cycle (2 Man Crew) 

Task Man hrs /day 

1. Sleep 16 

2. Eat 2 

3. Exercise 2 

4. Hygiene 2 

5. Leisure 3 

6. Station operation 4 

7. Experiments 11 

8. Maintenance 4 

9. Miscellaneous 4 

Total 48 

IfeRETSSM-50A 

6-55 

This document contoins informotion affecting the nOttOnO, oetense of the United Stoles ....thin the meoning of the Espionage to., 

"(Me 18. U S C Section 793 and 794, the itoevetss•oe of whtyh ,hany mon„,, to on venothot•yerf person ,s oto',•btfed by low 
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SECRET 

6.4.6 Navigation and On-Orbit Control. 

Determination of the requirement for a navigation system to be 

included in the Laboratory Vehicle must await definitions of the experiments 

program. Meanwhile alternative solutions are being investigated over a 

range of possible requirements. Improvements to the Gemini system are 

being studies in-house as a potential solution; McDonnell participation is 

planned for the Pre-Phase I contractual period. 

The requirements being used in attitude control system investigations are as follows: 

Attitude 

(Mode) 

Control 

(Attitude Deg. ) 

Requirements 

(Rate, Deg/Sec) 

Coarse .* 0.50 0. 01 

Fine 0. 10 0. 001 

Preliminary studies indicate that a constant thrust two-level 

hypergolic bipropellant propulsion system for reaction control should be 

adequate. 

6.4.7 Electrical Power. 

Power estimates indicate an average power level for normal 

station operation of about 1. 2 kilowatts exclusive of the experiments, the 

Gemini B, and the transtage. Further study is required to determine what 

additional power is required for experiments. The impact of short duration 

(approximately 10 minutes) high power level requirements such as 5 to 10 kw 

radar for experimental equipment must still be evaluated. The basic power 

could be supplied by a solar cell array with batteries and/or fuel cells incorporated to provide electrical power during the pre-launch, launch, 

activation, orbital nighttime passages, and peak power loads. Other 

methods are also being considered, including fuel cells, 

APU's, and hybrid arrangements of these. 

SSM-50A 

6-56 SECRET 

71,4 document contatn4 ■ nlatmotIon ollechng the,,o,onol oetense at the United States ...Oh, the rneon,ng ol the ftn.0^0olt 

The 18, U S C Section 793 and 794, the oo,rn.f1.0o of which ,n one mann, to a^ r",0-• h..,1 b. 
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6.4.8 Data Processing and Communications. 

As the experiments and vehicle studies become more firm, 

specific studies of data management will be made. A preliminary investigation indicates that the Gemini computer would be limited in capacity for MOL 

data management and its reliability may also be a problem. 

Communication requirements for the Laboratory Vehicle consist 

of transmitters, receivers, beacons, antennas, and auxiliary equipments 

required to provide a capability for space-to-earth voice communications, 

experiment and spacecraft telemetry, video (TV), tracking, and command 

communications. The Gemini communications system augmented by the 10 

me capability (New Hampshire and Vandenberg) of the Air Force Satellite 

Control net may provide an adequate basis for the experiments as currently 

envisioned. Consideration is being given to FM/FM and PAM/FM/FM 

telemetry, and to the USAF integrated S-band system or the NASA unified 

system. 

6.4.9 Reliability, Monitoring, and Checkout. 

A reliability trade-off exists between subsystem redundancy 

and on-orbit manned maintenance. Decisions made in this area specifically 

influence all details of subsystem selection, and exert strong direction upon 

vehicle arrangement. It presently appears prudent to consider a design 

philosophy in which most manned maintenance operations are regarded as 

noncritical experiments rather than mission-critical functions for the early 

MOL Program. 

Several operating and-display consoles will be required for the 

operation monitoring and checkout functions for each of•the Orbiting Vehicle 

subsystems. The consoles will enable the crew to monitor the status of 

critical components, provide automatic warning indication, provide means 

foi isolating malfunctions, and monitor and checkout the Gemini re-entry 

vehicle subsystems during storage. 

SSM-50A 

6-57 

That document contorni information offechng the nohonof ovense of the Untied Stote‘ *ohm the meaning of the Espfonoge laws 

Tale 18. U S C . Section 793 and 791. the If ontm.ss■ on of which In any monny, by 0, unOarhor•ted ',von is pinh.b•'.d by In. 
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6.4.10 Weight Breakdown. 

The MOL Vehicle preliminary weight estimates for a typical 

single pressurized compartment configuration are as follows: 

Subsystem or Item Weight (lb) 

Electronics 

Leak Detection System 

Electrical Distribution System 

Heat Rejection 

Air Circulation System 

Pressure Suits and Suit Circuits 

Atmosphere Re supply 

Water Management 

Waste Management (Including Disposal System) 

Food 

Cleaning Materials 

Disposable Clothing 

Reaction Control System 

Solar Array System 

Laboratory Structure 

Displays and Furnishings 

Spare Parts 

685 

Laboratory Module Subtotal 

Test Module Structure 

Experiment Payload 

Subtotal 

MOL Vehicle Total 

6.5 GEMINI B. 

6.5.1 General. 

335 

50 

150 

292 

158 

160 

989 

172 

50 

216 

24 

24 

306 

824 

1, 

345 

130 

5, 910 

1, 150 

5, 940 

7, 090 

13, 000 

Paragraph 3. 3. 1. 3 lists the Gemini B design problems to be 

studied by McDonnell during the Pre-Phase I contract period to define the 

Gemini B as precisely as possible prior to release of Laboratory Vehicle 

RFP. • The discussion which follows is based largely upon in-house efforts 

which have been exerted by Aerospace up to this time. Most of the configuration questions in this discussion are covered in the McDonnell study. 

SSM- 50A 

6-58 SECRETThis document contains tnlormohon offetling the notional detente of the United State, ...th.n the meaning of the Etptonoge Lot, 

Tale 18. U 5 C . Section 793 and 791 the ttentnutston of ..11,th in ht., mariner to on uenohey.terl porton t pfol,b.leri by In 
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SECRET 

The Gemini B is composed of a re-entry capsule, an escape 

tower (if required), and an adapter. A possible Gemini B configuration is 

shown in Figure 6-6. The re-entry capsule is essentially the NASA 

Gemini re-entry capsule with modifications required as a result of the change 

in mission. An escape tower similar to the Mercury tower may be required 

for use in event of an abort on pad or during early phases of powered flight. 

The adapter shown in Figure 6-6 is a new component and contains the retrograde propulsion subsystem, power and environmental control subsystems 

for use during the launch phase, and an inflatable tunnel for crew transfer. 

The Gemini B will be an integral part of the Orbiting Vehicle, probably with 

no maneuvering capability, and self-sufficient only during the launch and reentry phases. 

6.5.2 Design and Modification Considerations. 

The modifications to the NASA Gemini for the MOL application 

will probably consist of the deletion of subsystems not required for the MOL 

mission and alterations required by the Titan IIIC launch environment, the 

Laboratory Vehicle interface, and the 30-day storage on orbit. Subsystems 

added likely will include the crew escape tower or alternative, provisions 

for crew transfer, and provisions for on-orbit monitoring and checkout of 

the Gemini B from the Laboratory. Possible modifications of subsystems 

because of the on-orbit semi-dormant storage include replacement of 

cryogenic storage bottles with high-pressure bottles, and replacement of 

fuel cells with batteries. The present Gemini inertial guidance system may 

be replaced by a simplified system capable of supplying attitude reference 

for retrofire and re-entry. The existing Gemini IGS could be used either as 

the primary or backup guidance system for the launch phase. 

6.5.3 Gemini Subsystems. 

The structure of the Gemini must be slightly strengthened if an 

escape tower is used or if a transfer hatch is added within one of the large 

existing hatches for crew transfer. The current NASA Gemini heat shield 

concept will be used. A slight increase in thickness (adding about 20 pounds) 

-SECRET- SSM-50A 

6-59 

This document contains information affecting the notional °Vent, of the United Stoles within the meaning of the Espionage lows 

Title 18. U.S.C.. Section 793 and 794, the trcnsmission of which on ony manner to an unauthorized person os prohibited by low 
SSM- 50A 

6-60 

Figure 6-6. GeminiB Vehicle 

This document eomoins inform.on affecting the national omense of the United States within the meaning of the Espionage taws 

Title 18, U.S.C., Section 793 end 794, the housings,an of which in any manner to on unauthorized person is prohibited by low 
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RELEASE 1 JULY 2015 

-S-EGRETmay be made to accept a wider range of re-entry conditions. The NASA 

Gemini parachute recovery system with waterlanding will probably be used 

and a new adapter section will likely be required. 

6.5.4 Interfaces. 

Provisions will be made for monitoring and checkout of the 

Gemini B from the Laboratory and monitoring and activation of the Laboratory from the Gemini B. In addition, the Laboratory Vehicle will probably 

supply power and environmental control to the Gemini B during the on-orbit 

period. There appears to be no major interface between the Gemini B and 

the experiments except that it may be necessary to add provisions in the 

Gemini to return small data packages from orbit. 

6.5.5 Major Problem Areas. 

The launch abort problem has been aggravated by the change 

from the GLV to the Titan IIIC because of the greatly increased size of propellant load and because of altered flight characteristics, including accelerations and dynamic pressures. An escape tower, among other alternatives, 

is being assessed as an approach to improve the Gemini B escape capabilities. 

Several alternative methods of crew transfer from the Gemini 

B to the Laboratory require investigation. Only extra-vehicular transfer 

has no major effect on the Gemini B design. The other alternatives require 

changes to the heat shield or to the access hatches, considerable relocation 

of equipment in the re-entry module, and additions of tunnels or mechanisms 

to the adapter. 

After a 30-day period of semi-dormant storage in space many 

of the Gemini B subsystems must be reactivated. This. requirement will 

require a review of the subsystems and may lead to the addition of redundant 

subsystems or replacement by simpler and more reliable subsystems. 

4EGRET- SSM-50A 

6-61 

This document contains information affecting the Met../10t ovens* or in. UnitedStates within the meaning of the Esponoge taws 

Title 18. U S C . Sedan 793 and 794, the transm.st.on of ish.ch m any manner to on unauthor.zed person .1 prol,bited by low 
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6.5.6 Gemini B Preliminary Weight Breakdown. 

Re-entry Module 4, 372 

Structure 1, 407 

Heat Protection System 318 

Attitude, Stabilization and Control 359 

Retrograde, Landing and Recovery 217 

Navigation Equipment 138 

Tele -Instrumentation 113 

Electrical Power System 277 

Communications System 58 

Crew and Survival 940 

Miscellaneous and Contingency 220 

Adapter Module 1, 628 

Structure . 290 

Crew Transfer System 180 

Retrograde System 509 

Electrical Power System 200 

Environmental Control System 257 

Tele-Instrumentation 88 

Miscellaneous and Contingency 104 

Escape Tower (Effective On-Orbit Weight = 100 lb) 2, 500 

Total Gemini B Weight at Launch 8, 500 

Total Gemini B Weight On-Orbit (equivalent) 6, 100 

6. 6 LAUNCH VEHICLE. 

6.6.1 Description. 

The launch vehicle for the MOL Program is the standard Titan 

111C vehicle. The vehicle is comprised of two segmented solid propellant 

motors, modified 'Titan II liquid propellant stages, and a pressure-fed upper 

stage (transtage) including a control module (Figure 6-7). 

6.6.2 Modification Considerations. 

Modifications may possibly be made to the electrical, attitude, 

and guidance systems to permit their performing on-orbit functions, if 

desired. In addition, the inertial guidance system may be deleted. The 

SSM- 50A 

6-62 

This document contains information affecting the national aetense or the United Stoles within the rneoning of the Espionage tons 

Title 18. U S C Section 793 and 791. the tiansmission of which in any manner to on unouthariteci person .s ptnh,b,ted by In* 
STAGE I-STAGE!! Kam 

SEPARATION 

PLANE 

STAGE 

5 SEGMENT 

SOLID MOTOR 

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Figure 6-7. Titan ILIC Vehicle 

-SECRET- SSM-50A 

6-63 

This document contains information affecting the notional defense of the United Stoles within the meaning of the Espionage loos 

Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthonzed person is prohibited by low 
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SECRET 

control module may possible be used to perform certain functions for the 

Orbiting Vehicle; for example, the transtage could provide attitude control, 

at least in limit cycle modes, for the life of the Laboratory Vehicle. Additionally, the transtage suitable modified could provide on-orbit maneuvering 

propulsion capability. These possibilities plus a description of the abort 

environment faced by the Gemini and Laboratory design constraints imposed 

by the Titan III are to be developed by Martin under a Pre-Phase I study. 

6.6.3 Interfaces. 

The major interface with the Laboratory is the common mechanical joint, launch-vehicle-imposed structural and acoustical loading, and 

possible use of transtage subsystems on-orbit. Major irlterfaces with the 

Gemini B include structural and acoustical loading, crew safety, and possible use of the Gemini IGS as guidance for the launch phase. 

6.6.4 Problem Areas. 

Principal problem areas include the launch vehicle constraints 

on the payload with respect to diameter, length, strength, and c. g. location, 

and the effect of the Titan IIIC on crew safety. 

6.6.5 Payload Capability. 

The payload capability used in the MOL study is 21, 000 pounds 

for a. nearly-east launch from AMR into a 200 n. mi. reference circular 

orbit. This includes a launch vehicle payload pad of 2000 pounds for possible 

performance contingencies.. 

6.7 GROUND SUPPORT. 

6.7.1 Checkout and Launch (Launch Site). 

The checkout and launch facilities at AMR will include new 

facilities and AGE for receipt and inspection of the Laboratory and the 

Gemini B. The Titan IIIC ITL facility (see Figure 6-8) will be used for 

SSM-50A 

6-64 -ERE+ 

Th.s doCum.ni conlo.n, .nfoem.hon o11ec'shg no, ,0n0, e'en ye or she Limped S.ntes the m ,nr .nq 01 she ho•r,^el•In ! ■ 7••• 
Titan II C I ITL Facility 00 

-SECRETSSM-50A 6-65 

Tha document canto.% mitt/mown aflechng fhe nahonat amens. of the United Stoles oath. the meantng al the !wattage loot 

Tide U.S.C•. Sechon 793 and 791. the tfonsmown of oh.ch in any mannet to an unouthoticed p.,04 prolubaed by law 
NRO APPROVED FOR 

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assembly of the Titan IIIC booster, for integration of the Laboratory and 

Gemini (which may be performed in the VIB or on the pad), and for complete system checkout prior to launch. 

6.7.2 Mission Control Center. 

The Mission Control Center will be located at Cape Kennedy and 

will consist of a number of separate Centers including the Launch Control 

Center, the Range Control Center, the Range Safety Control Center, the 

Recovery Control Center (physically located in the MCC), the VehicleAstronaut Control Center (located in the MCC), and the Experiment Control 

Center. It is presently contemplated that the Gemini Mission Control 

Center will be utilized. Facilities and equipment for certain of the above 

Centers are adequate as existing or planned; these will be used to the maximum extent possible. For the other Centers, requirements for additional 

facilities and equipment are under study. 

6.7.3 Remote Station Network. 

Network support requirements include extensive coverage on 

ascent and until vehicle system status is established, nominal on-orbit 

coverage of once-per-orbit (with possible decreased frequency with successful on-orbit performance), provisions for extra coverage for special events 

(crew transfer and deboost), and provisions for emergency abort and 

recovery impact prediction. It appears that MOL requirements for remote 

station coverage can be met by using a combination of existing locations 

(assuming that joint use of certain sites with other national space programs is possible) augmented by at least one additional station. Studies of 

alternative network configurations are in process. 

6.7.4 Tracking, Communications, and Control (TC and C). 

As part of the MOL System design, detailed study is being performed of requirements of each subsystem and experiment for TC and C 

data types, quantities, accuracies, frequency response, sampling for control 

vs analysis, etc. Guidelines will be established for information flow and 

SSM- 50A 

6-66 --SECRETTh•s document conto.hs tnfott,totgon oftect.ng the nat,onol oetense at 're Un.sed Senses *dn.n the meontog of the Esptoroge lames 

Tote 18. U S C Secttoh 793 and 794 the If ne,m.,,oe 01 h .e ,or oon^e, to co unnuthn••cen ne,o^ n•nh•h.•rd hi In., 
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processing on-board the vehicle, at the tracking station, and at the 

Control Center. 

Based on data obtained to date, the objective that no development of TC and C ground equipment shall be necessary appears to pose 

little constraint to the MOL System, with the possible exception of wideband data links for special experiments. However, a 10 Mc link capability 

already exists at two SCF stations which may suffice, with little modifications, for experiments usage. 

The application of integrated systems such as the NASA Unified 

S-Band System and the Air Force Space-Ground-Link Subsystem to the MOL 

is being studied. Although such systems will offer 'significant advantages 

when operational, the fluidity of present implementation plans do not indicate 

the advisability of a commitment of the MOL Program to them at this time. 

6.7.5 Satellite Recovery Complex. 

The recovery operation will require a Recovery Control Center 

(paragraph 6. 7. 2), a communication network connecting the Control Center 

and the recovery forces, a weather data collection point in the Control 

Center, the recovery forces, and logistic support bases for the recovery 

forces. Water recovery 'sites will be selected to provide a near onceper-orbit recovery capability. Recovery over land will occur only in 

emergencies. 

6.7.6 Data Processing. 

Real-time selection and processing of telemetry data and processing of command data in large blocks of digital words is a present 

feature of the SCF and the Gemini network and is expected to be required 

for the MOL. Digital processing of tracking data is a normal process 

within the planned capabilities. Data reduction in less than real time will 

be handled by normal NRD procedures. Use of NRD facilities is planned. 

SSM-50A 

6-67 

Th■ s document contoms .nformotion ollechog the notmnot detente of the Unaed Slates *ohm the meomng of the Eswonoge tons 

Tale 18. U S C . Section 793 and 794. the Ircrism.ssmn of *1,0 ony manner to on unouthor.zed person ,t ornh•b•ted by 
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--SE-RET6.8 MANUFACTURING AND GROUND TEST FACILITIES. 

The manufacturing and ground test facilities for the MOL 

Program are those applicable to the Titan III Program (Ref SSP for T-III, 

31 January 1964), those applicable to the Gemini B contractor (MAC); and 

those applicable to the Laboratory contractor (to be determined). Certain 

existing buildings at Cape Kennedy Air Force Station (CKAFS) have been 

tentatively identified as desirable for ground test for the program, but will 

require some modification to meet test requirements. These facilities are 

Hangars AF, S, and L. Additional test facility requirements have not been 

determined at this time, but the NASA Merritt Island facilities, the AEDC 

facilities, and the AFFTC facilities are being examined. 

6.9 COMPONENT AND SUBSYSTEM DEVELOPMENT TESTING. 

It is the objective of the MOL Ground Test Program to perform, 

to the maximum extent possible, complete subsystems and.systems integrated testing to verify, with the highest degree of confidence, the flight'-

worthiness of the program equipments. 

To accomplish this objective, a philosophy of ground testing has 

been established which will require the spacecraft, Laboratory, experiments 

and launching system to have completed extensive simulated launch, injection, on-orbit, de-orbit, and profile integrated testing at the manufacturers' 

facilities prior to shipment to CKAFS. 

It is anticipated that prior to Government acceptance at the 

manufacturers' facilities, the manufacturers will have demonstrated the 

flight-worthiness of the flight articles by successfully conducting an allsystems test. Upon satisfactory completion of the all-systems testing of 

the Gemini B and Laboratory at the manufacturers' facilities, it is likely, 

although not certain, that the Gemini B will be shipped to the Laboratory 

contractor's facility as Government Furnished Equipment (GFG). The 

associate contractors (Gemini B, Laboratory, experiments) and astronauts 

would then perform integrated MOL tests to demonstrate MOL subsystems 

compatibility. 

SSM- 50A 

6-68 

This document contains informat.: , &fitting the .ofionol ovens, of the United States ...thin the meaning of the Esp.onage fans 

Tale 18. U S C . Section 793 and 794 the ttansmits.on of .hich in nnY monnet to on UnOvthO'rl,1 PC,,0" •, b'ed tty tn. 

■ 
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Two methods of operation at CKAFS appear possible at this 

time. These are (1) installation and checkout of the Gemini B and Laboratory with the Titan MC in the VIB, or (2) installation and checkout of the 

Gemini B and Laboratory with the Titan IIIC at the launch complex. 

In the event of a major malfunction or modification, it is anticipated that the complete article (Gemini B or Laboratory) would be returned 

to the manufacturer's facilities for repair, replacement, or rework, as 

required, and that the systems would be revalidated prior to return to 

CKAFS 

6.10 SYSTEM FLIGHT TEST AND OBJECTIVES. 

6.10.1 Test Operations Concept. 

The following test operations concepts will be observed in the 

conduct of the MOL Program. 

a. "Buy-in" as cheaply as possible by making effective 

use of available DOD/NASA resources. 

b. Maximum use will be made of NASA Gemini planning 

hardware test results and opportunities for training. 

c. Test Force Direction and primary mission control 

will be performed by the USAF. 

d. Flight crews will be selected and trained by the USAF. 

e. Primary flight control will rest with MOL crew. 

f. A governing factor in mission success is crew safety. 

g. Crew and mission simulation (with appropriate network 

exercising) is a significant part of the System Test 

Program. 

h. Delivery of launch-ready flight hardware to launch site. 

i. Minimum launch site checkout. 

j. Earliest manned flight possible. 

k. Water recovery. 

1. Primary recovery is the Atlantic (Puerto Rico). 

m. Secondary recovery area is the Pacific (Midway). 

n. Secure de-orbit (or alternative secure disposition) of 

Laboratory Module is necessary. 

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6-69 

This document contours .nlotmotfon of fect,n9 the not•one oetenie of •ne Un•ted Sfotes «•th•n the meon.ng of the Esp•onoge to*, 

Tale 18. U.SC . Section 793 and 791. the to on unoutho••red pe,son •s of oh•b•ted by lo. 
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SECRET 

6.10.2 Flight Test Planning. 

For initial planning purposes, the MOL flight program will 

consist of six flights. This number is not considered inalterable should 

studies during Pre-Phase I or Phase I show sufficient reason for a different number. 

An objective of program definition studies will be to obtain the 

maximum return in terms of MOL test objectives accomplished as early as 

possible and for the least dollar investment. In terms of flight program 

planning, this objective indicates that as many as possible of the MOL 

flights should be manned flights of the complete MOL system including 

experiments. 

In addition to making maximum use of systems and subsystems 

which will have been space flight tested in other programs, and employing 

ground testing, simulation and aircraft testing to the maximum practical 

extent, full scale "piggyback" testing will be investigated to reduce to a 

minimum the number of MOL flights programmed for unmanned systems 

verification. One approach to be explored will be to test the Gemini B on 

Titan LTIC test flights, including investigating the practicability of using recovered NASA Gemini capsules refurbished and modified to the minimum 

extent necessary to yield valid test results. A structure would be used to 

join the Gemini to the Titan III which is dynamically similar to the Laboratory Vehicle. 

6.11 ACQUISITION SUPPORT. 

The requirements for the acquisition support items listed 

below will be determined during Pre-Phase I. 

a. Reliability 

b. Quality Assurance 

c. Configuration Management 

d. Maintenance/Operations 

e. Spare Parts/Support Support 

f. Propellant Support 

SSM- 50A --SECRET- 6-70 
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g. Transportability 

h. Transportation 

i. Packaging & Preservation 

j. Human Engineering 

k. Safety Engineering 

1. Photographic Programs 

f..12 PERSONNEL TRAINING. 

Flight crew members will be selected from the pool of graduates 

of the Aerospace Research Pilot School. Complete evaluation will ensure 

that the selected MOL astronauts are in excellent physical and mental 

health, and are physiologically normal in all respects. Criteria for medical 

evaluation will be those established by the USAF,School of Aerospace Medicine for the evaluation of space pilots and those additional criteria deemed 

necessary to eliminate abnormalities which would predispose to medical 

Problems upon exposure to the combined stresses of the space environment. 

Each selected MOL astronaut will have had a basic scientific or 

engineerit.; education as well as a sound indoctrination in the principles of 

space flight. Additional training prior to flight will be in the following 

categories. 

a. (no change) 

b. (no change) 

c. (no change) 

d. (no change) 

e. Simulations: Individual operational and experimental 

tasks and full mission simulation will be used both for 

training purposes and to validate proposed procedures 

and plans. 

f. (no change) 

g. (no change) 

h. (no change) 

i. Medical Support: Medical evaluation and monitoring 

teams and recovery and rescue teams will be trained 

and integrated into the overall operational support 

program. 

-SERET-- SSM-50A 

6-71 

This document COAIMns onlormotooet allectong the notional defense of the United Stotts within the meaning of the Esplonage Lows. 

TO. 18. U.5 C . Sect.on 797 and 791. Iht bantmittion of which in any moment' In on unautho,.ted person Is pwohibited by low 
Contract 

Number 

Responsible 

Office 

or Center 

NASw-776 OMSF 

NASw-775 

NAS8-5344 MSFC 

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6.13 MOL SPECIFICATIONS. 

The MOL system specification will include the performance 

and design requirements for each segment of the MOL system. The preliminary system specification breakdown is presented in Figure 6-9. Supporting the system specification will be the Contractor End-Item (CEI) 

specifications for each item to be procured for the program. These CEP s 

will be identified (through the top levels) prior to release of the Phase I 

RFPs, and will be provided to the contractors for further expansion during 

the proposal period and the Phase I effort. 

6.14 RELATED STUDIES. 

List of NASA MOL Studies 

Study Title 

a. Mission Definition Studies 

Biomedical Requirements 

Advanced Orbital Launch Operations 

b. Logistics Systems and Operations 

Studies 

Modified Gemini Ferry 

Modified Apollo Ferry 

Operations and Logistics 

12-Man Ballistic Concepts 

12-Man Lifting Body Concept 

100 Ton Reusable Launch Vehicle 

10-Passenger Reusable Ferry Vehicle 

NAS1-3121 

NAS9-1506 

NAS9-1422 

NAS9-1666 

NAS9-1689 

NAS8-5036 

NAS8-5037 

NAS8-2687 

LRC 

MSC 

MSC 

MSC 

MSC 

MSFC 

MSFC 

c. Small MOL Studies 

MORL Concepts -- Phase I 

Extended Apollo Concepts -- Phase I 

NAS1-2975 

NAS1-2974 

NAS9-1963 

LRC 

LRC 

MSC 

SSM-50A 

6-72 SECRET 

Th. document (01,1.4, ,n1pernol,on oll.c.ng the notional defense of the Un.ted States the meon.ng of the f sP.onOge tows 

1.11, is. 5 c 793 and 704 the 0ons.n•ss.on of 0.h.th .0 n•nnner to nn kono.thn..f•1 oe•tnn .t d.nh.h.ted by In.. 
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-SE-CRETList of NASA MOL Studies (Cont) 

Responsible 

Contract Office 

Study 'Title Number or Center 

d. Large MOL Studies 

Zero G Station Concepts NAS9-1688 MSC 

Rotating Station Concepts NAS9-1665 MSC 

Electric Power Systems NAS9-1307 MSC 

Large Life Support NAS9-1498 MSC 

e. Supporting Studies 

Small Life Support System NAS1-2934 LRC 

Nuclear Reactor Power NAS3-1460 . LeRC 

Nuclear Isotope Power NAS3-1461 LeRC 

Artificial G Cable Concept NAS1-2946 LRC 

Sealing Study NAS9-1563 MSC 

Titan III Launch Vehicle Study NAS1-3308 LRC 

-SECRET- SSM-50A 

6-73 

This document co/drum Inlotrnotton ollectino the notton01 defense of the United Stoili within the meaning of the E1117ton0be Lows. 

Tole la, U S C . Sectton 793 and 791 the rronsm,su on of whah in any manner to on tynoothonyed pe■ snn q rpoh,b.fed by low 
MOL System Specifications 

SSM- 50A 

6-74 SECRET 

Thee document COMOIRI Infolmohon affecting the notional defense of the United Steam within the meaning al the Espionog. tows. 

Tate IT. U.S C. Section 793 and 791, the hanttnission of which in any moaner to an uisaoclhorised poison it prohibited by foot. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECTION 7 

CIVIL ENGINEERING 

• 

NOT APPLICABLE AT THIS TIME 

THIS SECTION IS BASICALLY ADDRESSED TO THAT CIVIL 

ENGINEERING PECULIAR TO PHASE III OPERATIONS. 

CIVIL ENGINEERING PECULIAR TO PHASE II SYSTEM ACQUISITION IS 

- DISCUSSED IN SECTION 6 (ACQUISITION) 

SSM- 50A 
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SECTION 8 

LOGISTICS 

NOT APPLICABLE AT THIS TIME 

THIS SECTION IS BASICALLY ADDRESSED TO THE LOGISTICS 

REQUIREMENT OF PHASE III OPERATION. 

LOGISTICS UNIQUE PHASE II SYSTEM ACQUISITION WILL BE OUTLINED IN SECTION 6 AS ACQUIRED DURING PHASE IB 

SSM-50A 
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SECTION 9 

MANPOWER AND ORGANIZATION 

NOT APPLICABLE AT THIS TIME 

THIS SECTION IS BASICALLY ADDRESSED TO PHASE III OPERATIONS. 

MANPOWER REQUIREMENTS FOR STAFFING THE SPO IS • 

OUTLINED IN SECTION 3 - PROGRAM MANAGEMENT 
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SECTION 10 

PERSONNEL TRAINING 

NOT APPLICABLE AT THIS TIME 

CREW TRAINING AS IT PERTAINS TO ASTRONAUT 

REQUIREMENT FOR FLIGHT TEST DURING 

PHASE II - SYSTEM ACQUISITION IS DISCUSSED 

IN SECTION 6 (ACQUISITION) 
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RELEASE 1 JULY 2015 

INDEX 

SECTION 11 

FINANCIAL 

Page 

11.0 INTRODUCTION 11-1 

FIGURES 

Number Title Page 

11-1 TOTAL MOL PROGRAM FUNDING APPROPRIATION 

SUMMARY 11-2 

11-2 PRE-PHASE I FUNDING ESTIMATE 11-3 

11-3 MOL PHASE I FUNDING ESTIMATE 11-4 
NRO APPROVED FOR 

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t 

SECTION 11 

FINANCIAL 

11.0 INTRODUCTION. 

When submitted to AFSC Hq at the end of Pre-Phase J, the revised 

Preliminary Technical Development Plan for the MOL will contain estimated 

funding requirements for the complete program. These estimates will be 

reviewed and finalized during Phase I so that firm contractor proposals 

will be available for negotiation on Phase II. However, in this PTDP only 

costs pertaining to the Pre-Phase I and Phase I are included. Because of 

the cursory nature of this document and the constant changes which occur 

during Pre-Phase I planning and programming, no detailed cost analysis 

has been presented. As the Phase I requirements come more sharply into 

focus and with the issue of the revised PTDP, the detailed cost breakdowns 

will be presented. 

Figure 11-1 presents the estimated total funding requirements for 

the MOL program as presently foreseen. Figure 11-2 presents a more 

detailed breakdown of how the Pre-Phase I funds will be used to conduct 

selected essential studies leading to Phase I. Figure 11-3 presents estimates of the funding for the Phase I effort and the areas where the funds 

will be applied. 
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SECRET SSM- 50A 

11-3 

This document contains inlormotuon affecting the notionot avenge of the United States within the meaning of the Espionage Lows. Title CE, U.S.C.. Section 793 and 794, the trensmissuan of which in ony manner to on unouthorized person is prohibited by low 
SECRET 

0 0 0 0 In 

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ORBITING VEHICLE CONT

RACTOR 

0 

SUPPORTING ST

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0 

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SSM- 50A 

11-4 SEeREF 

This document contains information affecting the national detente at the United Stain within the meaning of the Espionage Lows. 

Title la, U.S.C., Section 793 and 794. the transmission of which in any manner to on unauthorised anion is prohibited by low 
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SECTION 12 

REQUIREMENTS 

. . 

NOT APPLICABLE AT THIS TIME 

DATA PERTINENT TO THIS SECTION WILL BE 

GENERATED DURING PHASE I 

. - 

SSM- 50A 
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INDEX 

SECTION 13 

AUTHORIZATION 

Page 

FIELD LEVEL MANAGEMENT OF THE MOLS PROGRAM 13-1 

CHARTER FOR THE DEPUTY COMMANDER, SPACE SYSTEMS 

DIVISION FOR MANNED SYSTEMS 13-2 

MANNED SPACE PROGRAM 13-3 

TWX FROM AFSC TO SSD - 10 MARCH 1964 13-5 

AFSC LTR (MSF-.1), 8 MAY 1964, TO DCMS, SSD 13-8 

IfeREF SSM-50A 

13-i/ii 

Th.* document contoms ,nlotenconon 014(1,9 the not.onot oeteme at the Umted States nah.n the meomog of the ftwonoge Ions 

7,11. 18. U S C Socha. 793 end 794. the ”c^s..“.0. Ot ..h.(11 monnm to an aolaoho,qed pvtom .1 o,o■• b,ed by 
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HEADQUARTERS 

AIR FORCE SYSTEMS COMMAND 

United States Air Force 

Andrews Air Force Base 

Washington 25, D.C. 

REPLY TO 

ATTN OF: SCG 

SUBJECT: Field Level Management of the MOLS Program 

COPY 

10 Mar 1964 

TO: SSD (Major General Ben I. Funk) 

Air Force Unit Post Office 

Los Angeles 45, California 

1. Forwarded for your information and compliance . 

2. Procedures are being developed stipulating the manner in 

which the MOL Program and its primary elements are to be 

handled by field activities, Headquarters AFSC, and higher 

authority. Pending approval of the special management procedures, the Deputy Commander, SSD, for Manned Systems, 

is authorized direct access to the Commander, SSD, and 

Commander, AFSC. 

Signed 

B.A. SCHRIEVER 

General, USAF 

Commander 

1 Atch 

Charter for the Deputy Cmdr 

SSD, for Manned Systems 

1st Ind (SSG) 

Hq SSD, AF Unit PO, Los Angeles, Calif. 90045 

TO: DISTRIBUTION: A-1, 5 

General Schriever's letter is forwarded for your information and 

necessary action. Specific procedures will be furnished when 

developed. 

Signed 

BEN I. FUNK 1 Atch - n c 

Major General, USAF 

Commander 

I'OR OFFICIAL MD ONLY 

SSM- 50A 

13-1 

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T.tte ta. U S C Sector 793 and 194 the ',my..., of .n,•.h • man', to an uroolho,ted pe“on .t ntoh,h,,ed by low 
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CHARTER FOR THE DEPUTY COMMANDER, 

SPACE SYSTEMS DIVISION FOR MANNED SYSTEMS 

The Secretary of Defense has directed that the Air Force initiate the development of a Manned Orbiting Laboratory (MOL). Specific guidance from 

OSD and OSAF has emphasized the need for deviation from standard management structure and procedure because of the complex nature of the program, 

the cooperative effort with the NASA that will be involved, and the requirement for participation by the Secretary of Defense, the Secretary of the Air 

Force, and their staffs. The Air Force Systems Command, through its 

Space Systems Division, has complete responsibility for management of the 

MOL program, including its essential elements within the framework of 

approved program plans. 

To accord the MOL program the requisite integrated field level management, a Deputy Commander, SSD, for Manned Systems, will be appointed; to 

facilitate the early attainment of the program objectives, he will have unusual 

and extraordinary autonomy and authority. The following principles will be 

employed: 

1. The Deputy Commander, SSD, for Manned Systems will be appointed 

in the authorized grade of Brigadier General. 

The Deputy Commander, SSD, for Manned Systems, is delegated 

full uthority for field implementation of the approved MOL program. 

3. The Deputy Commander, SSD, for Manned Systems, is authorized 

direct access to streamlined channels which have been established for 

expedited action on Designated Systems Programs and the MOL Program. 

4. As the overall field level program director for all aspects of the 

MOL program, the Deputy Commander, SSD, for Manned Systems, will 

have complete control of allotted financial resources and will follow established procedures to assure support of all elements of the program. 

5. Field detachments at test sites and factory representatives at selected contractors' plants will be established as required, and will report 

directly to the Deputy Commander, SSD, for Manned Systems. 

6. Military and civilian personnel will be assigned as required to implement the approved program. 

""PCIR-erlortekortrti&E-49144331- 

SSM-50A 

13-2 4EGRETTho document cameo's mfottneo.on elteettng the not,onol ante,. co the Un.ted States ...oho, the mcon.ng of the hp•onoge Ions 

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c ma- IDENTIAL) 

HEADQUARTERS 

AIR FORCE SYSTEMS COMMAND 

United States Air Force 

Andrews Air Force Base 

Washington 25, D.C. 

REPLY TO 

ATTN OF: SCG 

SUBJECT: Manned Space Program 

COPY 

16 Dec 1963 

TO: SSD (SSG, General Funk) 

AF Unit Post Office 

Los Angeles, Calif 90045 

1. The Department of Defense has directed the following actions: 

a. Termination of the X-20 Program . 

b. Initiation of a Manned Orbiting Laboratory (MOL) Program. 

c. Expansion of the ASSET Program to provide basic technology for future space vehicles. 

2. It is incumbent upon AFSC to manage the allocated resources in 

order to provide the best possible program. The ground rules for 

action follow: 

a. The lead division for management of this entire manned 

space effort, including ASSET, is SSD. The full support of the 

other divisions and centers is essential. 

b. Manpower spaces made available by the termination of the 

X-20 Program will be converted to presently validated space requirements of the division or center involved. No manpower 

spaces will be transferred at this tim7117ii--n one division or center 

to another as a result of the decisions enumerated in paragraph 1. 

c. Upon termination of the X-20 Program, all possible funds 

will be recovered consistent with the additional instructions which 

follow. 

3. The X-20 Program must be closed out in a manner which provides maximum benefit to the Government. It is therefore necessary to take action to terminate all activities in support of the 

X-20 as rapidly as it can prudently be accomplished. Much of the 

materials, components, subsystems, studies, techniques, etc., 

from the X-20 Program will be useful in other efforts. As a part 

75r4 51- SSM- 50 A 

13-3 
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of the X-20 termination, these items will be made available to fulfill 

the requirements of other agencies. Military construction currently 

under contract which will be useful for other programs may be completed. 

No new contracts will be let. A briefing and report of the plan and status 

of X-20 termination will be provided to this Headquarters and to Hq 

USAF as soon as possible. The X-20 contractor efforts should be terminated in a manner similar to the actions taken in the GAM-87 Program. 

It is specifically desired that the program termination remain under the 

direction of the X-20 SPO until after decisions are made as to what effort 

should be continued, transferred, etc. Normal termination procedures 

will be applied as early as possible following the preliminary report to 

USAF on 16 December 1963. 

4. With the termination of the X-20 Program, it is necessary to consider expansion of an ASSET type program to obtain hypersonic flight 

data during lifting re-entry. SSD is assigned management responsibility for this expanded ASSET type project within the total MOL Program. A plan should be immediately prepared covering the proposal 

for modifying or augmenting the existing ASSET Program. The specific 

objective of the program should be immediately prepared covering the 

proposal for modifying or augmenting the existing ASSET Program. The 

specific objective of the program should be to settle basic design 

questions using unmanned scale models that will be required preliminary 

to a decision to initiate an advanced manned ferry vehicle. In the review of the X-20 Program, specific attention should be given to the 

possible use in the ASSET Program of the materials, components, and 

subsystems which are surplus as a result of the X-20 termination. 

RTD and ASD will provide their recommendation to SSD for use in preparing reoriented ASSET program plan. The plan should incliide a 

discussion of the possible cooling techniques for advanced re-entry 

vehicles in matrix format against critical parameters, which will be required to support your recommendation. Consideration should be given 

to the promising approaches which merit development of the technology 

and flight testing to demonstrate capability of the techniques. 

5. The plan should be available for review by this Headquarters on 27 

December 1963 prior to its presentation to OSD by 31 December 1963. 

Signed 

B .A. SCHRIEVER 

General, USAF 

Commander Similar letters sent to ASD, 

ESD, and RTD 

SSM- 50A 

13-4 

4C.014F-133ErN-T-ileekt 

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ACTION: SSB 

1964 Mar 10 AM 6: 32 

SSGE, SST , SSM 

DE RUEAGL 157 09/2232Z 

R 092218Z 

FM AFSC 

TO SSD LOS ANGELES CALIF 

BT 

Sri.C.R-EFT--MSF -9 - 3-13 SECTION 1 OF 2. 

FOR SSG SUBJ: PRELIMINARY TECHNICAL DEVELOPMENT PLAN (PTDP) 

FOR THE MOL PROGRAM. 1. IT IS APPARENT THAT APPROVAL OF A 

PLAN FOR DEVELOPMENT OF THE MOL PROGRAM WILL NOT BE FORTHCOMING FROM DOD UNTIL WE PRESENT TO THE SEC OF DEFENSE A 

CONVINCING ACCOUNT OF MOL PROGRAM EXPERIMENTS WHICH WILL 

SATISFY THE OBJECTIVE OF DEMONSTRATING QUALITATIVELY AND 

QUANTITATIVELY THE MILITARY USEFULNESS OF MAN IN SPACE . THE 

PRELIMINARY DEVELOPMENT PLAN OUTLINE SUBMITTED TO•DOD ON 

7 JAN 64 DID NOT FULLY MEET THIS REQUIREMENT THEREFORE, THERE 

IS A NEED TO SUBMIT A PTPD WHICH EMPHASIZES THE APPROACH TO 

BE TAKEN TO MEET THE PROGRAM OBJECTIVES. 2. ACCORDINGLY, 

SSD IS REQUESTED TO PREPARE A PTDP WHICH WILL SERVE THE FOLLOWING PURPOSES: (A) IT WILL SERVE AS THE SINGLE AUTHORITATIVE 

REFERENCE DOCUMENT ON THE MOL PROGRAM AND, AS SUCH, PROVIDE THE FRAMEWORK WITHIN WHICH ALL SUBSEQUENT PROGRAM 

ELEMENTS AND ACTIONS CAN BE INTEGRATED BY SUBSEQUENT PERIODICAL UPDATING. THUS IT WILL PERMIT FOCUS WITHIN A SINGLE 

DOCUMENT UPON ALL ACTIVITIES INITIATED IN SUPPORT OF THE MOL 

PROGRAM. (B) IN ITS INITIAL VERSION, IT WILL DESCRIBE IN DETAIL 

THE PRE-PHASE I STUDIES AND EFFORTS TO BE UNDERTAKEN IN DEFINING EXPERIMENTS REQUIRED TO SUPPORT THE CONTINUING EFFORT 

IN THE MOL PROGRAM. IT WILL THUS SERVE TO INSURE THAT THESE 

EFFORTS WILL BE CORDINATED AND, IN AGGREGATE, CONSTITUTE A 

COMPLETE AND VIABLE PRE-PHASE I EFFORT UPON WHICH THE PREPARATION OF THEMOL PHASE I RFPS CAN BE BASED. IT WILL SERVE 

AS THE DOCUMENT TO OBTAIN DOD APPROVAL FOR STUDIES IN THE 

PRE-PHASE I PERIOD WITHOUT COMMITTING DOD TO THE APPROVAL 

OF THE ENTIRE MOL PROGRAM. (C) IN ADDITION, IT WILL CONSTISTUTE AN OUTLINE AND FORMAT OF A COMPLETE TDP FOR THE CONDUCT OF THE MOL PROGRAM. HOWEVER, THE INITIAL DOCUMENT NEED 

NOT GO INTO DEPTH IN THE PROGRAM ACTIVITIES REQUIRED AFTER 

THE INITIATION OF PHASE I. THESE SHOULD BE COVERED IN GENERAL 

TERMS AND WHERE INFORMATION IS NOT AVAILABLE, SIMPLY INDICATE 

THAT SECTIONS ARE OMITTED AND WILL BE INCLUDED WHEN THE 

INFORMATION IS AVAILABLE. THIS WILL PROVIDE FOR THE ORDERLY 

UPDATING OF THE ENTIRE PACKAGE. 3. PROPOSED STUDIES AND 

OVER-ALL APPROACH IN PRE-PHASE I SHOULD BE DIRECTED TOWARD 

SECRET SSM- 5 0 A 

13-5 
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THE DEFINITION AND SYNTHESIS OF EXPERIMENTS WHICH MEET THE 

APPROVED CRITERIA. IE: THEY WILL ESTABLISH QUALITIVE AND 

QUANTITATIVE MEASUREMENTS OF MAN'S USEFULNESS IN SPACE IN 

PERFORMING MILITARY TASKS. THE PROPOSED EXPERIMENTS SHOULD 

HAVE CONSIDERED THE ENTIRE SPECTRUM OF POSSIBLE MILITARY 

APPLICATIONS. IN THIS REGARD, THEY SHOULD BE FOCUSED UPON 

THE ROLE OF MAN RATHER THAN UPON THE ROLE OF SPECIFIC EQUIPMENT. 4. WHILE EXPERIMENTS WHICH WOULD ASSESS MAN'S ROLE 

IN RECONNAISSANCE MAY BE CONSIDERED, IT IS EMPHASIZED THAT 

THE DEVELOPMENT OF A MANNED RECONNAISSANCE SYSTEM IS NOT 

AN APPROVED OBJECTIVE FOR THE MOL PROGRAM. EXPERIMENTS 

RELATED TO RECONNAISSANCE WILL ATTEMPT TO DETERMINE MAN'S 

CAPABILITIES, WITH APPROPRIATE AIDS TO POINT AN INSTRUMENT 

WITH ACCURACY BETTER THAN ONE HALF MILE, TO ADJUST FOR IMAGE MOTION TO BETTER THAN 0.2 PERCENT, AND TO FOCUS PRECISELY (IF T:DS IS NECESSARY). A. ALL MOL DEVELOPMENT PLANS 

AND BRIEFINGS LIst RELATION TO RECONNAISSANCE OBJECTIVES WILL 

BE CONFINED TO THESE PARTICULAR OBJECTIVES AND EVERY STEP 

WILL BE TAKEN TO AVOID SPONSORING OR ENCOURAGING ANY EFFORTS 

TO PROPOSE ACTUAL RECONNAISSANCE CAPABILITY OR TO DESCRIBE 

THE ESTIMATED STATE OF THE ART IN SATELLITE RECONNAISSANCE. 

ALL AFSC IN-HOUSE AND CONTRACTOR WORK, INCLUDING DISCUSSIONS 

WITH CONTRACTORS, WILL BE CONFINED TO THESE OBJECTIVES . 

B . PHOTOGRAPHY OF RECONNAISSANCE QUALITY WILL NOT BE USED 

TO RECORD OR VERIFY PERFORMANCE. IMC AND FOCUS EXPERIMENTS 

WILL BE PERFORMED USING A TELESCOPIC SYSTEM. POINTING 

ACCURACY CAN BE RECORDED WITH A SIMPLE COLLIMATED CAMERA 

OF RESOLUTION EASILY AVAILABLE FROM UNCLASSIFIED EQUIPMENT . 

IMC PERFORMANCE CAN BE RECORDED BY PHOTOGRAPHING STARS OR 

BY USE OF LONG EXPOSURES OR IN OTHER REASONABLY UNSOPHISTICATED WAYS. FOCUS EXPERIMENTS, IF NECESSARY , CAN BE CONDUCTED AT SUCH MAGNIFICATION THAT RECONNAISSANCE CONDITIONS 

ARE SIMULATED WITHOUT BEING DUPLICATED. 5. IT MAY BE 

ASSUMED THAT ADDITIONAL EXPERIMENTS WILL BE UNDERTAKEN 

LATE IN THE PROGRAM. DETAILS OF THESE PROPOSED EXPERIMENTS 

WILL BE PROVIDED AT A LATER DATE BY SEPARATE CORRESPONDENCE . 

NO CONSIDERATION NEED BE GIVEN TO THESE ADDITIONAL EXPERIMENTS IN THE 1 APRIL SUBMISSION OF YOUR PTDP . 6. THE FOLLOWING ADDITIONAL GROUND RULES APPLY: A. THE PTDP SHOULD BE 

FORWARDED TO THIS HQ (ATTN: MSF-1) AS SOON AS POSSIBLE BUT 

NO LATER THAN 1 APRIL 1964 AND ACCOMPANIED BY AN APPROPRIATE 

BRIEFING. B . ALL RFPS AND WORK STATEMENTS OF ALL CONTRACTS 

RELATED TO MOL EXPERIMENTS WILL BE SUBMITTED TO THIS HQ 

PRIOR TO DISCUSSION WITH CONTRACTORS. C . MAXIMUM UTILIZATION 

WILL BE MADE OF EXISTING STUDIES CONDUCTED BOTH WITHIN THE 

AIR FORCE AND BY OTHER AGENCIES IN ORDER TO MINIMIZE THE TIME 

REQUIRED FOR PROGRAM APPROVAL. D. MAXIMUM USE WILL BE 

PROPOSED OF GROUND TESTS, SIMULATION, AIRCRAFT TESTS, AND 

USE OF EXISTING SPACE PROGRAMS FOR TESTING. EXPERIMENTS 

SSM- 50A 

13-6 -SECRET- 
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--SEGRETCOPY 

PROGRAMMED FOR THE MOL SHOULD BE THOSE WHICH CANNOT BE 

ACHIEVED IN ANY OTHER WAY OR IN WHICH THE ACTUAL EXPERIMENT 

IN MOL CONSTITUTES PROOF TEST OF EXPERIMENTS PRIMARILY CONDUCTED IN OTHER AREAS. 7. THIS MESSAGE IS CLASSIFIED SECRET 

BECAUSE IT CONTAINS SPACE PLANNING INFORMATION VITAL TO 

NATIONAL DEFENSE. GP-3 BT. FINAL SECTION OF 2. 

SSM-50A 

13-7 

Thq document conto:ns ,n10•mat.on cuect ng 'he nnt,onni deie^se n •ne .e0 S,ntes meot...10 01 the Esn•onnge 

T.tte 18. U S C Sec ,o^ 797 c-d '94 the t•ansrn ..-on 01 0^ r)h t,d b., H. 
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ATTN OF: MSF-1 

SECRET 

-teerrrpreferrphtfty 

HEADQUARTERS 

AIR FORCE SYSTEMS COMMAND 

United States Air Force 

Andrews Air Force Base 

Washington 25, D. C. 

COPY 

8 May 1964 

SUBJECT: Approval of USAF FY-1964 RDT&E Manned Orbiting 

Laboratory (MOL) 

TO: SSD (DCMS) 

Air Force Unit Post Office 

Los Angeles, California 

1. References: 

a. MOL Preliminary Technical Development Plan (PTDP), 

dated April 1964. 

b. D&F 64-11c-84 dated 13 April 1964, with attached 

Form 111. 

c. Memorandum, DDR&E (Dr. Brown) to SecAF, same 

subject, dated 29 April 1964, copy attached. (Attachment #1) 

d. Memorandum SAFRD (Dr. Flax) to Vice Chief of Staff, 

USAF, same subject, dated 4 May 1964, copy attached. 

(Attachment #2) 

e. Letter AFRDC to AFSC, same subject, dated 6 May 

1964, copy attached. (Attachment #3) 

2. You are hereby directed to proceed with the pre-Phase I 

study program as outlined in the April 1964 PTDP, subject to 

the conditions listed below. PA and BA authorization is being 

forwarded under separate cover. 

a. Contract negotiation for the following studies will be 

deferred pending specific authorization by this headquarters to 

proceed: 

(1) APOLLO ' 

(2) GEMINI (One-Man) 

(3) Pointing and tracking scope definition 

(CONFIDENTIAL) 

SSM- 50A 

13-8 --SEGREf 

This document canto..., ,nfotmotton offechng tee ...co ono, oe'ente o• Un•ted Stntet .•th.n gnu meon.ng of the Ftin•onoge 

I■ sle 18. U S C Seet.on 797 ond 79.1 theIre,• ■■•ti. a. a; •••••• ■■ a 1^, mon,- ta e- ne,,n- ,to^ t, b, 1,„ 
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(4) Autonomous Navigation 

(5) Electromagnetic Intercept 

COPY 

b. Prior to initiating any study effort for which sole source 

procurement action is contemplated, other than those already 

identified in paragraph 13(g) of Form Ill, reference 1. b. , as 

being sole source efforts, you will submit to this headquarters 

the proposed work statements and an appropriate statement 

identifying the proposed sole source contractor and the justification underlying your recommendation for sole source procurement. 

c. Request that you review the work statements for the 

Pointing and Tracking Scope Definition (3. 3.1. 2. 1) and Autonomous Navigation (3. 3. 1. 2. 6) studies as to the feasibility and 

desirability of extending the experiment efforts to include experiment tasks in geodesy and gravimetry which may be generally 

useful and provide complementary inputs to the two experiments 

concerned. Your recommendations, including revised work 

statements or a statement of justification for non-inclusion, 

should be forwarded to us as soon as practicable. 

d. Request that you review the proposed experiment P-9 

(Negation and Damage Assessment) in the light of the results of 

Program 706 studies. Your recommendation for its deletion or 

justification for retention should be submitted to this headquarters as soon as practicable. If retention is recommended, your 

submission should be supported by a statement of the need and 

importance and should include the extent of proposed in-house as 

well as the requirement if any, for contractor support. 

e. Particular emphasis should be given in all experiments 

studies to the inclusion, wherever possible, of provisions for 

ground simulation. 

FOR THE COMMANDER 

Signed 

RICHARD K. JACOBSON 

Colonel, USAF 

Asst Dep Comdr for Space for MOL 

(CONFIDENTIAL) 

3 Atch 

1. Memo, DDR&E to 

SecAF, 29 Apr 64, same 

subject. 

2. Memo SAFRD to 

AFCVC, 4 May 64, same 

subject. 

3. Ltr AFRDC to AFSC, 

6 May 64, same subject. 

4EGRETSSM-50A 

13-9/10 

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SECTION 14 

GENERAL INFORMATION 

14.0 REFERENCED REPORTS. 

14. 1 US Naval Research Laboratory Memorandum Report 1507, Manned 

Orbital Laboratory Technical Panel. First Preliminary Report dated 17 

March 1964. 

14.2 • Experiments for MOL, Mission Analys.is Panel, SSTA-IM-3, 11 

March 1964. 

14, 3 A Preliminary Description of Experiments for Manned Military 

Orbital Systems, Aerospace Corporation, TOR-269(4531-41)-1, R. Glasser, 

20 Jan 64. 

14. 4 • Proposed MOL Experiments RTD. 

14.5 Bioastronautics Panel Report, 11 Mar 64. 

14. 6 General and Scientific Panel Report, 11 Mar 64. 

14. 7 Reconnaisance and Surveillance Panel Report, 11 Mar 64. 

14.8 MOL Experiments_Working Group Augmented Data, 23 Mar 64. 

14. 9 Candidate Experiments for Manned Orbiting Laboratory, Volume I, 

1 April 1964, SSTA-1-9. 

14. 10 Candidate Experiments for Manned Orbiting Laboratory, Volume II, 

Parts 1 and 2, 1 April 1964, SSTA-1-10. 

SSM- 50A 

14-1/2 

This document contains infolmotion affecting the notional °creme of the United Shales within the meorang of the Espionage tows 

Title 18. U.S.0 . Section 793 and 794, the transmission of which m ony enonner to on unoulhoiired person is prohibited by low 
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SECTION 15 

SECURITY 

NOT APPLICABLE AT THIS TIME 

DATA PERTINENT TO THIS SECTION WILL BE 

GENERATED DURING PHASE I 

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INDEX 

SECTION 17 

Page 

17.0 INTRODUCTION 17-1 

17.1 ACTIVITY SCHEDULES AND NETWORKS 17-1 

17.1.1 Action Network 17-2 

17.1.2 Pre-Project Definition Phase Planning Network. . . 17-2 

17.1.3 Phase I Planning Network 17-3 

17.2 MANPOWER AND FUNDING 17-3 

17.3 REQUIRED PHASE IB PRODUCTS 17-3 

17.3.1 Associate' Contractors Final Report 17-3 

17.3.2 Phase II Proposal 17-3 

17.3.3' Aerospace Corporation Products 17-4 

17.3.4 System Program Office 17-4 

FIGURES 

Number Title Page 

17-1 ACTION NETWORK 17-5/6 

17-2 PRE-PROJECT- DEFINITION PHASE PLANNING NETWORK 17-7/8 

SSM-5QA 7-i/ ii 

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SECTION 17 

PRELIMINARY DEFINITION PLAN 

17.0 INTRODUCTION.. 

The purpose of the Preliminary Definition Plan (PDP) is to establish a framework for the eventual development of a specific plan for the 

accomplishment of the MOL Project Definition Phase (PDP). The final 

PDP plan will include all the activities to be accomplished by the SPO/ 

Aerospace/Contractors during Phase IA, IB and IC, and will indicate how 

these activities will be effectively integrated. Since many of the activities 

to be accomplished by the contractors during Phase IB will not be known 

until Phase IA is underway, the complete Definition Plan will not be available until the results of Phase IA are available. 

In this Preliminary Technical Development Plan (PTDP) the basic 

framework for the Definition Plan is presented. The framework consists 

of schedules of Phase I activities with their interrelationships and the products of these activities. 

17.1 ACTIVITY SCHEDULES AND NETWORKS. 

During Phase I the DOD, USAF Headquarters, AFSC Headquarters, 

Space System Division, Aerospace Corporation, and selected contractor 

organizations will be involved. The successful completion of Phase I will 

require specific activities to be accomplished by each of these organizations; 

activity schedules in this section identify these major activities and indicate 

their relationship and interdependency. 

This plan is based upon what are judged to be minimum realistic 

times for all echelons to accomplish required activities. No administrative 

delays are presumed and, if any occur, the schedule will slip. 

SSM-50A 

17 -1 

Th.% document conto.ns .nlotmot.on ollechno thy not•Onot Oetense or the United Stotts the meon,ng of the ho.onooe Ions 

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17.1.1 Action Network. 

The Action Network presents the flow of the mainstream activities 

required by the OSD, Hq USAF, AFSC, SSD/Aerospace, and the contractors 

to accomplish Pre-Phase I and Phase I. The network indicates when contractor in-house study efforts are to be initiated, completed, evaluated, and 

reported; how the various activities are dependent on each other and when 

program outputs are scheduled for submission to Washington for review and 

approval to proceed with the next step. Since this network is intended to 

present only mainstream activity, detailed presentations of the activities 

within organizational entities require reference to other sub-networks. 

17.1.2 Pre-Project Definition Phase Planning Network. 

The many in-house and contractor efforts required during this 

initial phase are presented in the Pre-Project Definition Phase Planning 

Network. Many activities have been underway during the past months, and 

these have been included to show how the various technical, management, 

and procurement tasks that are required to prepare for the initiation of 

Phase I efforts are interrelated. These activities include such tasks as: 

program planning; establishment of a SPO Cadre; preparation of Requests 

for Proposals, procurement guides, and technical work statements; accomplishment of preliminary trade-off studies; development of management 

control procedures; preparation of preliminary system specifications; and 

the preparation and updating of program documentation, such as this PTDP. 

The importance of this type of planning network lies in its use to 

determine which program elements are pacing or critical to the attainment 

of the overall program objectives. A typical example is the requirement to 

define adequately the experiments to be conducted in the MOL prior to the 

release of RFP's for the Laboratory Vehicle to industry. Both in-house and 

contractor efforts (OSSS) are involved in this definition, and until they are 

accomplished the follow-on activities are constrained. Numerous other 

interdependencies become obvious by means of this type of network planning 

and the impact of specific discussions on the total program can be readily 

evaluated. 

SSM-50A 

17-2 SECRET 

This document contains lnformotton olfectng the national ',cense of the Untied Stoles within the meaning of the Esptonage Lows 

Title 18, U.S.C.. Section 793 and 79A, the tionsmission of which in any manner to on onanthoriteri person is prohibited by law 
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17.1.3 Phase I Planning Network. 

A detailed Phase I Planning Network is a required element of the 

plan for the PDP. However, it is dependent upon the results of the PrePhase I studies and has not been included in this PTDP. As the various 

tasks in Pre-Phase I are completed, the total planning network will be developed and included as part of the revised PTDP. 

17.2 MANPOWER AND FUNDING. 

The proposed manpower and funding requirements for the MOL 

Phase I program are presented in Section 3 Program Management and 

Section 11 Financial respectively. This information is not repeated in this 

section of the PTDP, but they will be further defined during Phase I. 

17.3 REQUIRED PHASE IB PRODUCTS. 

The SPO is required to prepare a Proposed System Package Plan 

(PSPP). The PTDP forms the basis for preparing this PSPP, but the results of the SSD/Aerospace/Contractors Phase IB efforts will be required 

to complete the document. Therefore, specific items will be required as 

products of the Phase IB study efforts, but these are not all identifiable at 

the present time. A major purpose of Pre-Phase I is to identify these 

items. However, the following paragraphs indicate the typical products to 

be expected from the Phase IB effort. 

17.3.1 Associate Contractors Final Report. 

The contractor final reports will include a summary, technical 

data resulting from trade-off studies, a base-line system/subsystem 

description, performance/design requirements specifications, program 

schedules, and the management plans required to conduct the program. 

17.3:2 Phase II Proposal. 

The contractors will prepare a detailed proposal for the Phase II 

program. It will include all functional plans, work statements, system 

--SfeREI- SSM-50A 

17-3 

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specifications, a PERT/Time & Cost system, incentive features, and any 

other item necessary to the successful accomplishment of the program 

objectives. 

17.3.3 Aerospace Corporation Products. 

The Aerospace Corporation will perform General Systems Engineering and Technical Direction (GSE/TD) during the Phase IB period. 

These major products will be reflected in the products provided by the contractors under their technical direction and technical documents prepared 

for the Air Force and for distribution to the program contractors. Under 

the General System Engineering function they will be responsible for the 

overall integration and engineering for the complete MOL system. In addition to the GSE/TD role, the Aerospace Corporation will technically support 

the SPO and perform selected technical trade-off studies. 

17.3.4 System Program Office. 

The SPO will manage the Aerospace and industry contractors efforts, prepare program documentation and briefings, perform procurement 

functions as required, prepare the PSPP, and accomplish all tasks required 

to prepare for the anticipated Phase.11 program. 

■ SSM-50A 

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▪ 

ECRETThis document contains information affecting the nolo:mai defense or the United States within the meaning of the Espionage Tows 

Title 18. U.S C . Section 793 and 791. The Itcnsmission al which in ony monner lo on unauthorized person is prohibited by low 


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SECRET 

INDEX 

SECTION 18 

CONCEPT FOR US NAVY EXPERIMENTS 

IN THE MOL PROGRAM 

Pa g t18.0 INTRODUCTION 1 8 - 1 

18.1 OCEAN SURVEILLANCE 18 - 1 

18.2 COMMAND AND CONTROL 18-16 

18.3 COMMUNICATIONS 18-17 

18.4 18-17 

18.5 E LINT 1 8 - 1 c' 

18.6 BIOAST RONA UTICS 1 8 -22 

18.7 GENERAL SCIENCE 18-24 

SS NA 

18 
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FIGURES 

Number Title Page 

18- 1 Over-all Summary of Experiments 

Recommended for MOL 18- 

18- 2 Ocean Surveillance State of the Art, 

Sensors 18- 3 

18- 3 Coverage Obtained with Simple NonRotating Radar Antenna as Shown 

in Figure 18-2 18- 5 

18- 4 Ocean Surveillance - Concept 18- 7 

18- 5 Ocean Surveillance, Use of Sensors 18- 9 

18- 6 Situation 1 - Surveillance of Harbors, 

Ports and Shipping Lanes 18 -10 

18- 7 Situation Z - Directed Search by Ground 

18-11 

18- 8 Situation 3 - Detailed Inspection of 

Major Ports 18 -13 

18- 9 Ocean Surveillance Experiments 18-14 

18-10 Weight Estimates for Ocean Surveillance 

18-15 

18-11 Communications Experiment 18 -18 

18 -12 18-20 

18-13 ELINT Experiment 18-21 

18 -14 Bioastronautics Experiments 18-23 

18-15 General Science Experiments 18-25 

18-16 General Science 18-26 

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18-iii/ iv 

docvmeo. 'fie•.o,onn, of ..e Unoed .he *enn,ng of the 

Command 

Experiments 
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SECTION 18 

CONCEPT FOR US NAVY EXPERIMENTS 

IN THE MOL PROGRAM 

18.0 INTRODUCTION. 

A preliminary report of the Navy MOL Technical Panel has been prepared for submission to the Bureau of Naval Weapons. In all, the Panel 

received eighty-nine proposals or ideas for experiments. From these were 

selected those experiments to be proposed for the MOL program . The number of experiments submitted in each area, the number recommended for 

support by the Navy, and the preliminary estimates of costs for these 

experiments are given in Figure 18-1. 

Major interfaces between these experiments exist on data management, 

structural arrangements, vehicle stabilization and control, position determination, communications, etc. These require further study. 

The experiments proposed are within the state of the art and can be 

orbited in the 1968-1970 time period. They are also well within the payload 

capability of the MOL vehicle. 

The experiments described here are intended to study means for 

improving the performance of naval missions. Their inclusion in the MOL 

program is highly recommended. 

18.1 OCEAN SURVEILLANCE. 

In view of the obvious importance of ocean surveillance to Navy missions, a separate study group consisting of Panel representatives from the 

Institute of Naval Studies, the Applied Physics Laboratory, the Naval Air 

Development Center, the Naval Research Laboratory, the Naval Photographi( 

Interpretation Center, and the Bureau of Naval Weapons met at the NRL to 

develop further this topic. The problem in ocean surveillance is to survey 

ships, harbors, and ocean lanes. It is necessary to detect and classify all 

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18-1 
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Over-all Summary of Experiments Recommended for MOL 

Experiments Costs (Millions) 

Mission Area Reviewed Recommended FY '65 Total 

Ocean Surveillance 26 1 (8 parts) $2 . 75 $39 . 25 

Command and Control 2 

Communications 3 1 0.60 2.0 

1.50 7.0 

ELINT 4 1 Included (?) Included (?) 

Bio-astronautics 14 3 0.30 3.25 

General Science 35 10 0 .70 6.85 

89 $6 . 00M* $59 . 00M* 

*Preliminary estimates only. Not for budget purposes. 

Figure 18-1. Over-all Summary of Experiments Recommended for MOL 

vessels found in either harbors or ocean lanes. The problem is complicated 

by the fact that the oceans are vast, that the targets are continually on the 

move, andthat good data must be obtained to be useful. Tardy, incomplete, 

and inaccurate data is of little value. It is obvious that an astronautic syster 

cannot supply the total requirement, but only supplement other means of 

maintaining ocean surveillance. It is probably true that the Navy's problem 

is not the same as that of the AF or the Army. Thus, the Navy's problem 

revolves around keeping track of ships on a global basis. The targets are 

relatively large but continually on the move. Hence, the naval requirement 

seems to be for a system of nominal resolution and very wide coverage. 

Any consideration of the problem of ocean surveillance must begin 

with an understanding of the state of the art for the available sensors. 

Figure 18-2 gives (in summary form) the most essential information with 

respect to each possible sensor. Some changes may be required in the final 

selections. It may be necessary, for example, that an optical system be 

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procured having a 96"-focal-length lens, rather than the 48"-focal-length 

lens given in the table, to secure the desired resolution of 12' and permit 

at the same time some degradation of performance of the camera while in 

the spacecraft. The best choice for radar is similarly unsettled at the prc 

sent time. Two possible choices are given: one with a rotating antenna sytern and one without. Note that the radar system with the non-rotating 

antenna leaves large gaps in the coverage of the earth below the spacecraft 

See Figure 18-3 for coverage obtained with the simple non-rotating antenna 

proposed. 

The concept for ocean surveillance developed by the sub-panel is as 

follows: there mus' be advanced detection of all shipping targets followed ' 

classification by the astronaut, appropriate data processing, and read-out 

by ground stations. 

To perform the function of detection in advance of the satellite the 

most promising sensors seemed to be radar, television, and infrared -

in that order. It is desired that this advance detection take place as long 

as one minute in advance of the time when the spacecraft is over the target 

on the earth. At the orbital rate of travel of the spacecraft this corresponc 

to 250 miles; thus the detection range for the broadly scanning sensor systems should be approximately 250 miles in advance of the spacecraft. Allweather radar systems having this capability can be devised. Television a; 

infrared systems can provide initial detection under favorable conditions 

where the weather is clear or clouds are only thin or broken. Optical 

systems can also perform this function when the weather is clear or when 

clouds are thin and broken; but optical systems of high-resolution, particu 

larly, are not as well adapted for automatic searching of large areas as 

is radar. 

After the target has been detected, the next step involves classificatio. 

Here, provided the weather is clear, a set of binoculars having variable 

magnification and directed by the astronaut to the coordinates indicated by 

the advance detection means would be used to find the target. If desired, 

then, through servo controls, the high-resolution camera can be caused to 

SECRET SSM -50A 

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IERETphotograph automatically the target under examination. The 

pictures would be used for detailed study on a deferred basis. If the weather 

is not favorable, then the astronaut must depend upon other systems to determine friend from stranger. The directivity of an IFF-type interrogating 

device operating from the radar antenna or a separate 5-foot dish mounted on 

MOL is good enough to separate ship from ship under most conditions. The 

ELINT also can provide from coarse to good resolution and separate "friend" 

from "stranger." The same is true with respect to ultra-high-frequency 

beacons carried by friendly merchant shipping or aircraft. 

The third part of the ocean surveillance concept is that automatic position deterrninaCpri must be provided to the astronaut. This should record 

automatically the coordinates of any target selected by the astronaut. Such 

a system can be devised depending upon ephemeris data carried within the 

orbiting capsule, a gyro-stabilized platform, and means for relating the position of the classification device or camera with respect to the MOL vehicle 

attitude. There must be storage of all classification information provided by 

the astronaut. It may involve no more than operation of push buttons. There 

must be capability for command read-out of all data stored at such times as 

when the MOL capsule is over a friendly ground station desiring such information. Finally, there must be means within the data processing for instructed search to be initiated by ground command and acted upon by the 

astronaut. The command for instructed search given by the ground stations 

may be stored automatically for delivery to the astronaut at the proper time 

in orbit. 

The astronaut may, at times, be saturated by targets; therefore, data 

processing techniques must be employed to reduce this problem. Automation 

must be provided wherever possible. High-resolution film must be used to 

record the nature and position of selected visible shipping and harbors and 

their contents for later study and classification by the astronaut. Provisions 

for directed search and classification aids are needed to limit demands made 

upon the astronaut. The several factors involved in the concept of the integration of the hardware for this experiment are shown in Figure 18-4. 

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Figure 18-5 provides a view of the MOL astronaut engaged in ocean 

surveillance using his search or detection equipment to illuminate areas 

some 250 miles in advance for detection purposes and using his optical and 

other systems for inspection of targets detected. 

Three situations have been devised to illustrate the usefulness of ocean 

surveillance capabilities which can be provided the Navy by a manned astronautic system . Figure 18-6 is the layout for the first situation which illustrate 

the problem of ocean surveillance with respect to Cuba. There it is required 

that an unfriendly country be kept under surveillance to determine its shipping both in ocean lanes and in harbors, and the departure ports as well as 

the term'nu.1 ports. In the performance of this mission the astronaut provides the following contributions: (1) he can be selective and look only for 

certain kinds of shipping; (2) he can concentrate on certain areas and spend 

the whole of the time he is in the area of a fixed target (e.g., Havana -

approximately two minutes) in surveillance of that target alone; (3) he can 

filter out a target from a low contrast or noisy background; (4) he can give 

rapid response • ) a command for search, the time required, if his orbit is 

over the target, being less than the orbital period; (5) he can make optimum 

choice of the sensors to be used; (6) he can optimize performance of the sys -

tem by providing necessary adjustments; (7) he can improve reliability; 

(8) he can enhance accuracy. One further point in favor of man is that our 

capacity as a nation to orbit increasing payload, thus enabling man and his 

necessary environment to be included, seems likely to improve at a faster 

rate in the next ten years than is our capacity to orbit reliable, sophisticated 

systems able to replace man. 

Situation 2 shown in Figure 18-7 depicts a condition existing when directed 

search is to be instituted by ground command. In this case an area of the 

Sulu Sea is known to contain four ships in the locations marked with crosses 

in the diagram. It is also thought to contain two ships in the general location 

shown by stars on the diagram. The problem is to identify these unknown 

targets and provide their location. The instructions to the astronaut can be 

stored in the data processing equipment of the vehicle from any ground station 

over which the astronaut passes. At the appropriate time the astronaut 

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18 -8 
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Figure 18-5, Oc ean Surveillance 

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18-11 

This document comma inlotenotion affecting the notional °C.C.S! Or the Untied Shan within the meaning a the Espionage tows 

Title IS. U.S.C. Section 793 and 791. the Ponsoustion of which in any manner to an unathorired. person .% proh.biled by low 
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will be given signals from his data storage to inspect the area outlined by the 

dotted lines. If he is able to use the optical systems he is likely to obtain 

ready classification of the targets . If he is forced to use all-weather sensors 

then he can determine whether the unknown targets are captured by his sensors, whether they are friends or strangers, and their positions. If he is 

able to detect no target, but can see the surface areas whose coordinates are 

given, he has'provided information which may help to determine whether or 

not the unknown targets are submarines. 

Situation 3 is depicted in Figure 18-8. Here the problem is to determine the trend in world shipping as a portent for some future operation of 

an unfriendly power . The need is to inspect something like twenty ports 

around the world, e.g., to catalog and count the ships in ports and in lanes 

to these ports . The illustration chosen is that of a northern port where certain lanes may be ice-closed. With optical equipment in suitable weather the 

astronaut can survey with high resolution the harbors and the approaches to 

the harbors and classify shipping in these areas. He can also determine 

which shipping lanes are open and which are closed by ice. If weather is 

unfavorable he can count ships which are in the lanes using equipment such 

as radar, IFF, ELINT, and beacons. At night, in favorable weather, he 

may obtain a shipping count through the television system. Here again man 

gives selectivity or the ability to look for only certain kinds of information; 

he gives the ability to concentrate on certain areas; he gives the capability 

for optimizing all sensors used; he gives rapid response; and he can correlate 

and filter data. In short, he provides more accurate, more reliable data. 

Figure. 18-9 is a preliminary estimate of the total cost to fund an ocean 

surveillance experiment on means for satisfying the naval mission requirements. In summary, it is a system utilizing radar, optical, television, 

infrared, ELINT, IFF, and beacon-type sensors. None of these sensors 

alone can do the job. All of these sensors used intelligently together can 

obtain great amounts of valuable information. 

An estimate of the over-all weight of hardware for the ocean surveillance experiment is included in.Figure 18-10. 

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Weight Estimates for Ocean Surveillance Experiments 

Component Weight 

Integration and Data Processing 350 lb 

Radar 1,500 lb 

Optical Sensors 800 lb 

Television 150 lb 

Infrared 150 lb 

IFF 25 lb 

ELINT 200 lb 

Beacon 25 lb 

3,200 lb * 

*This is a preliminary estimate only. Weight for primary 

power and gyro-stabilization is not included 

Figure 18-10. Weight Estimates for Ocean Surveillance Experiments 

SECRET SSM -50 A 

18-15 

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There are a number of elements of the proposed ocean surveillance 

system which require further study. For example, it is necessary to determine whether the radar antenna can be a rotating one as is preferred, or whether it must be fixed to avoid disturbing the optical system . Second, it is 

necessary to determine whether the radar antenna can provide the multiple 

usage capability required by the IFF, the ELINT, the beacon, and the radar 

systems. It may be necessary to provide a second antenna (perhaps a 5-foot 

aperture dish) for use by the LFF, the ELINT, and the beacon systems to 

classify the targets. Third, it is necessary to determine how the optical 

cameras can be made adequately directive. (It is considered that an essential eleme.nt of this system is that the camera should be quite flexible in its 

ability to be trained upon any point on the earth within 250 miles or so of the 

astronaut.) A fourth question has to do with the need for a camera of focal 

length of 98". (The 48"-focal-length camera will give the required resolution 

only if it is operating at its maximum effectiveness. To allow for some 

degradation of performance it may be necessary to use 98"-focal-length optics 

The camera apertu e may need to be increased from 12 to 18 inches. Schedules are yet to be determined. Much more accurate cost data are required. 

The many interfaces between the various sensors must be thoroughly examined 

and properly related one to another. Also, it is necessary to determine the 

cost in effectiveness which will ensue to the over-all experiment if certain 

portions must be omitted for one reason or another. 

18.2 COMMAND AND CONTROL. 

In the specific area of Command and Control the Technical Panel received no experiment proposals of note. This is an unsatisfactory situation 

because there is a problem which exists in this area. The obvious technical 

requirements for command and control posts, whether in space or on shipboard, include data sensors and processors, means for communication, 

means for presentation of information, and means for storage and response 

to direction and command. The hardware already envisioned for the MOL 

vehicle to perform the Navy ocean surveillance mission can take care of sur - 

veillance, data processing, and communication functions envisaged for the 

command and control function, and therefore will support the Command and 

SSM -5 0A 

18-16 -SEORETThis document confomt mlotrn0000 ollecong the oc00000l deleo%* of the Unwed Stole, odh., toe meorong of the Etreonooe Lae. 

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Control mission. However, no suggestions with respect to specific experiments in command and control are provided herein. It is suggested that 

sponsors be sought within the Navy to develop a suitable command and control 

experiment. 

18.3 COMMUNICATIONS. 

There is much work under way on unmanned space communication experiments; however there is still a place for special experithents. The 

Navy has a wide interest in global communications, hence the Technical 

Panel accepted a communications experiment proposing further work in VLF, 

ELF, and HF areas. This experiment will check out the efficiency of global 

communication to a spacecraft on the opposite side of the earth from a 

ground station using VLF. It proposes to measure antenna impedances 

and propagation characteristics within the frequency ranges listed. 

Man can be very useful in tuning and adjusting the equipment to optimize the 

performance of the experiment and enhance its reliability and accuracy. 

Figure 18-11 provides a summary of the factors involved in a communication 

experiment. Sponsors for the proposed experiment include the NRL and 

NADC. 

18. 4 

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18.5 ELINT. 

In the area of the ELINT mission, man can provide selectivity to examine 

signals which appear to be of most interest; he can filter out noise; he can 

provide better accuracy, and better reliability; and he can provide correlation of data input with respect to other information. Furthermore, the 

manned astronautic vehicle is the only manned vehicle now available for 

passage over foreign territory. It therefore enables the development of capability for selective, tactical, ELINT analysis which appears to be promising 

during the .1968-1970 period. This is particularly so in view of the fact that 

man's capability to launch larger payloads is presently increasing faster than 

is his capability to launch highly reliable, adequately sophisticated, unmanned 

systems to obtain some kinds of information which are desired. At least four 

Navy laboratories could be selected as sponsors for a selective, tactical 

ELINT analysis project. These include the NRL, the NADC, the NMC, and 

the NOL (White Oak). Costs of the hardware needed for performing the experiment are included in the estimates for the ocean surveillance system; 

however, some additional funding may be required to cover costs of the sponsoring activity for this particular experimental area. A summary of the 

factors considered in the ELINT problem is given in Figure 18-13. 

SECRET SSM-50A 

18 -19 

This document contains inhumation °Ilion the notional detente of the United Slate, *ohm me rneorion of the Espionage Lows. 

Title IS. U.S.0 , Section 793 and 791, the tronsrmssmn of *Inch on ony mantle, to an unauthotired person is prohibtted by tou. 
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NOT UNIQUELY NAVY, MUCH AF ACT VIT I Y. 

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SSM- 50A 

18-20 -SECRET 

This document contains information affecting the national defense at the Untied States within the meaning of the Espionage tows. 

Tide le, U.S.C.. Section 793 and 794, the Itcnsmission of which M nay roomer to on unauthorised person is prohibited by Ipne 
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-SEMSSM-50A 

18-21 

This document caldrons inlarrnation alt«ting the notional defense of the United Stain «ohm In, meaning of the Espionage tow, 

T111. IE. U.S.0 Sertion 793 and 791, the transmission al ohortt in any manner to an unclothed:eel poison is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECRET 

18.6 BIOASTRONAUTICS. 

In the mission area of Bioastronautics there are several factors to be 

considered. In the first place, NASA has planned the launching of a series of 

at least six 1,000-pound bio-satellites . These are to be orbited for periods 

extending from three to thirty days. It is also to be remembered that the 

directives for the MOL program state that work in the area of bio-astronautics 

is not to be overdone. Hence, the Panel considered that only those experiments 

should be considered for naval participation in which the Navy can make some 

unique contribution or has some special reason for performing the experiment. 

The summary included in Figure 18-14 shows that only three experiments were selected in the bio-astronautics area. The first one of these is 

an extension of Project ARGUS in which the Navy has been making at the 

Naval Medical Research Institute an extended study of the capabilities of man 

to exist in small parties of from 2 to 15 in number for extended periods of 

time in deeply submerged vehicles which are completely cut off from mankind. In such a vehicle man encounters many environmental conditions 

which are like those in space. Therefore, it is considered that the Navy can 

make a considerable contribution to the national effort by relating and extending its ARGUS studies to the MOL system. In the case of the remaining 

two experiments on nuclear radiation monitors proposed by the Naval Radiological Defense Laboratory , it is considered advisable that these be included in the MOL vehicle because NRDL has certain advisory responsibilities to DOD which require it to obtain first-hand information on the space 

environment encountered by man. Also, in the case of the heavy-particle 

dosimeter experiment proposed by NRDL recovery of records is necessary 

for further study. 

SSM -50A 

18-22 SECRETThis document contains tnfortnehen &lean the neh0n01 defense of the United Slate, *oho, the meaning of the Espionage Low,. 

Title 113, U. S.0 , Section 793 and 794, the ltansm.stion of wh.ch to any manner to on unauthorized person d prohthtted by low 
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SECRET SSM-50A 

18-23 

This document COMeillt information alfectinp the national delentt of the United States within the meaning of the EsPionat). Low.. 

Title 18, U.S.C., Section 793 and 794, the hananission of which in nay manner to an unauthorized person is ptahtbaed by low 
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RELEASE 1 JULY 2015 

SECRET 

18.7 GENERAL SCIENCE 

The Navy has much capability in the area of General Science, and 

consequently the Panel had many experiments to review. Those ultimately 

selected are thought to have potential military value. Considered first were 

experiments that are related to the MOL vehicle and deal with space and 

plasma physics. For example, the proposal of the NRL to study plasma 

surrounding the MOL vehicle by scatter of RF energy is included. Similarly 

the proposal to study by the use of probe techniques the density and temperature of electrons within this plasma was included. The far -UV orthicon was 

included because of its military mission interest, its need for manned operation, and the inherent value of background information with respect to UV 

radiation in near-earth space vehicles. The airglow horizon photography 

was selected as being of value because the airglow is a major phenomena 

encountered by any optical sensor operating near the earth, and horizon sensors are of considerable interest. 

Of long-range interest is the cosmic radiation coming in to earth and 

it. direction of origin. This would be studied in one of the experiments 

recommended. Also, of interest is information on the white light corona 

about the sun and possible sky surveillance of the area near the sun. The 

airglow spectroscopy made possible in the MOL vehicle is also considered 

to be a valuable experiment. Finally, photography of the solar planets and 

of the geology of the earth using the camera planned for ocean surveillance 

from the MOL vehicle is worthwhile. (It is true, however, that the camera 

proposed will be only marginally effective for use in photography of the 

planets .) 

much more complete study of the Navy proposals in General Science 

has been prepared by Dr. William Faust of NRL. 

The estimated cost for General Science experiments proposed by the 

Navy are shown in Figures 18-15 and 18-16. 

SSM-50A 

18-24 -SEOREf- 

'Ms document contemn inforrnohon offechno the notional defense of the United Stoles ...ohm me meaning of the Esp,onoge to.. 

Title 18. U.S.0 Section 793 and 794, the iranon.won of which in any manner to on unouthoozed pet., pr0h,b.ted by le. 
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18-25 

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Title 18. U S C , Section 793 and 79e. the trans...won of which in any manner to an unauthorized pesson it prohibited by law 

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SSM-50A 

18-26 SECRET 

This document contains informarion affecting the notional defense of the United Slates within the meaning of the Espionage low.. 

Tills 18, U.S.0 Section 793 and 7.4, he transmission of which in any manner to on unouthoriyed person is prohibited by low 
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SECTION 19 

NASA EXPERIMENTS 

AS YET THEIR HAS BEEN NO DEFINITION OF NASA 

EXPERIMENTS. HOWEVER, IT IS EXPECTED THAT THEY 

WOULD FALL WITHIN THE SECONDARY GROUP OF EXPERIMENTS 

SSM- 5 0A 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

INDEX 

SECTION 20 

SUMMARY OF SECONDARY EXPERIMENTS 

20.1 S-1 

Pa e 

VLF COMMUNICATION-PROPAGATION 

EXPERIMENT '20- 1 

20.2 S -2 SECURE COMMUNICATIONS USING NARROW 

BEAMS 20- 2 

20.3 S -3 LASER PROPAGATION EXPERIMENT 20- 4 

20.4 S -4 HIGH FREQUENCY IONOSPHERIC DUCTING 

COMMUNICATION 20- 6 

20.5 S -5 

20- 7 

20.6 S-6 EXPANDABLE STRUCTURES TECHNIQUES . . . 20- 9 

20.7 S -7 ANTENNA DEPLOYMENT, ALIGNMENT, 

AND POINTING 20 -10 

20.8 S -8 20 -11 

20.9 S -9 

. . . 20-13 

20.10 S-10 MAPPING AND GEODETIC SURVEY FOR 

IDENTIFIED POINTS 20 -15 

20.11 S-11 20 -15 

20.12 S-12 HYDROGEN REDUCTION ATMOSPHERIC 

REGENERATION SYSTEM 20 -17 

20.13 S-13 VAPOR COMPRESSION DISTILLATION 

WATER PURIFICATION SYSTEM 29 -19 

20.14 S-14 PASSNE PROPELLANT SETTLING 

SYSTEMS 20 -20 

-SECRETSSM-50A 

20-i 

Thts document contours informobon of fecong the nohonot ovens, of the United Stoles *atmn the rneonrng of the Isporroge So.% 

Tale IS. 11 S C . Sechon 793 and 791. the Iransmrss.orl of which to, any moaner to on enouthorraed person .a proh.b■ Ied by ID. 
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SECRET 

INDEX (Cont'd) 

SECTION 20 

SUMMARY OF SECONDARY EXPERIMENTS 

20.15 S-15 COHERENT E-M PROPAGATION AND 

Page 

ANTENNA LOADING 20 -22 

20.16 S -16 SOLAR X -RAY WARNING SYSTEM 20 -23 

20.17 S-17 MATERIALS DEGRADATION AND 

MALFUNCTION ANALYSIS 20 -24 

20.18 S-18 . MULTIBAND SPECTRAL OBSERVATIONS 

OF PLANETS (REV.) 20 -25 

SSM-50A 

20-ii SECRET 

This document contains informotion &letting the national ovens, or me United States *ohm the meaning of the Espionage tows 

Idle 18, U.S.c . Section 793 and 791, the transmission of which in any moaner to on unouihoozed person it prohibited by on 
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-SEMSECTION 20 

SUMMARY OF SECONDARY EXPERIMENTS 

20.1 VLF COMMUNICATION-PROPAGATION EXPERIMENT - 

EXPERIMENT S-1. 

20.1.1 Objective. 

The objective of this test is to investigate VLF propagation between 

globally distributed ground terminals and the orbiting MOL. It is also required to determine the effects of the diurnal variations of the ionosphere on 

the above propagation characteristics and deduce communication system 

capabilities for space-ground-space links. The astronaut will be required 

to monitor the VLF band for noise background and detect signals of known 

transmissions. He will also operate the transmitter in cooperation with 

ground instructions and vary the length of the VLF antenna for best coupling 

to the ionospheric plasma.. 

20.1.2 Description. 

The experiment is based on having a capability in MOL to transmit 

and receive in the VLF range. Signals transmitted from VLF ground installation, (Jim Creek, Cutler, etc) will be monitored in MOL and signal profiles 

will be recorded for future analysis. Monitoring of particular transmissions 

will be performed initially for at least full orbit. to determine if reception is 

continuous and global. Subsequently, monitoring will be for shorter periods 

based on diurnal variations of the ionosphere and position of MOL. 

MOL will transmit on assigned frequencies (not during reception) 

and be monitored by ground receiving stations. Antenna tuning capability 

will be required for maximum coupling to the ionosphere. To support the 

test, a VLF tunable receiver, transmitter, variable length antenna, earphones, and recorder will be required. Recorded profiles will be transmitted to ground at an opportune time. - 

SSM-50A 

20-1 

This document contains information affecting the notion°r oetehse ot the United Stales within the meaning of the EsP,0^0941 tows 

Title le, U.S.C.. Section 793 and 794, the transmission of which in any marine, to on unauthorized person is prohibited by taw 
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20.1.3 Importance of Test. 

The current information on the propagation of VLF energy transmitted between space and the earth is inadequate to determine the full potential 

of this frequency range to provide global capability using a space-mission 

vehicle in the extension into space of the VLF network. Such a capability 

would improve the global coverage of the VLF net and ensure alternate routing 

of traffic following the degradation or destruction of ground facilities. VLF 

communication traffic normally transmitted from large ground antenna systems could be transmitted to a space vehicle at other frequencies and retransmitted from space at the VLF net frequency to the dependent weapon 

system. 

20.1.4 Vehicle Requirements. 

Power: 500 watts on transmission/2 watts on 

reception 1-3 full orbits initially thereafter 

2-15 minute periods per day 

Volume: 2 cu ft 

Weight: 4 lb 

Stabilization: No rapid rotation during test periods 

Aperture (window): No unique requirement 

Miscellaneous 

20.2 SECURE COMMUNICATIONS USING NARROW BEAMS -

EXPERIMENT S-2. 

20.2.1 Objective. 

Tests will be performed to determine the feasibility of using a 

millimetric wavelength system for secure communications between MOL and 

aircraft and MOL and ground. Because of the narrow beamwidth (": V)) 

possible at this wavelength, the experiment will require accurate aiming by 

the astronaut of the antenna system. He will establish, via MOL communication support equipment, voice contact with the airborne or ground terminal 

SSM-50A 

20 -2 

This document contains information allotting the nationai mittens, or the United States within the meaning of the Espionage lows 

Title It, U.S.C.. Sectron 793 and 79e, the transmission of which in any manner to on unauthorized person is prohibited by low 
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SECRET 

and will transmit taped information on the millimetric system and record 

received signal profile. He will also orally monitor the received signal and 

evaluate its quality. The results of tests will be debriefed when opportune to 

do so. 

• 

20.2.2 Description. 

This experiment has two major parts. The MOL-Aircraft link will 

use the 60-75 KMC's frequency range and the MOL-Ground link will use the 

90-100 KMC's range. Both experiments need not be carried out in any one 

MOL, but could be alternated. 

The first experiment will require an aircraft flying at an altitude of 

40,000 feet or higher and along the track of MOL with test equipment similar 

to that in MOL. The experiment contact time will be 5 minutes average. 

After a link has been established, a modulation sequence can be transmitted. 

Both the MOL and aircraft will record received signals. The ground terminal 

for MOL-Ground link can be larger and a 15-foot diameter antenna is already 

available. The procedure for establishing the link will be the same in each 

case. As soon as the antennas are co-aligned and link acknowledgment is 

attained, automatic track will be used. 

20.2.3 Importance of Test. 

In order to provide a reliable and secure command capability between 

ground command posts, airborne command posts, and space command posts, 

the communication system must be resistant to jamming and interception by 

the enemy. Narrow beam systems respond to both these vital requirements. 

The test is necessary in order to respond to questions relating to the establishment of narrow-beam communication links between moving terminals. Because of the relative velocity of the terminals (i.e., space vehicle-to-space 

vehicle and space vehicle-to-aircraft) and, therefore, the high tracking rates 

involved, the initial acquisition is an important system consideration. If this 

experiment shows that man can contribute to initial link establishment by 

being able to accurately point the antenna, it would reduce the complexity 

SECRET SSM-50A 

20-3 

th,s document c0n10,ni 1910. mohon &feeling the aoldthot defense 01 the Untied Slestet edhot the meono0 01 the f spoilage 10, 

Tale IS. U S C Sec..on 793 and 791. the ocnoad%dya of ..hdh m nny manner 10 on unoathotthed pe■ son p1071,b.ted by law 
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(weight, power, space) which otherwise would be necessary in an automatic 

link establishment procedure when using narrow-beams. 

20.2.4 Vehicle Requirements. 

Power: 100 watts (during contact periods, 

not exceeding 10 minute duration) 

Volume: 2.4 cu ft 

Weight: 70 lbs 

Stabilization: High rotational stability of vehicle 

during test periods 

Aperture: Antenna system must be ca2able of 

being oriented through ± 90' to the 

vertical 

20.3 LASER PROPAGATION EXPERIMENT - EXPERIMENT S-3. 

20.3.1 Obi ective. 

The objective of this experiment is to determine the potential of 

narrow beam LASER radiation for communications and reconnaissance 

applications. This test will examine scattering, absorption, refraction and 

phase scintillation caused by the atmosphere. The role of the astronaut will 

be to point a receiver/transmitter antenna in the direction of a ground 

terminal. 

20.3.2 Description. 

This experiment has two primary parts. The first involves a 

LASER receiver capability on the MOL and a LASER radar on the ground. 

The ground terminal will track the MOL and the signal profile of the radar 

pulses will be detected and recorded in MOL. Pointing of the optical receive 

for maximum signal will be done by the astronaut. The second part involves 

the use of a LASER transmitter on-board the MOL and it will be required to 

direct the transmitted output toward a pattern of optical receivers on the 

SSM-50A 

20-4 SECRET 

Th.% document eantoter tnlermahon allechno the flamenco aerente at the Untied Stater ortthin the meaning of the Esponoge La.% 

Tole 19, u. s c Sedan 797 and 79A. the tlantrntst.on of oduch in any manner to on unaulhot.eed pylon n proh,bded by la. 
NRO APPROVED FOR 

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ground. A time/amplitude analysis would be done from information received 

in the ground complex to determine beam scattering, refraction and scintillation. 

Both experiments need not be incorporated in each MOL but could 

be alternated. The total configuration in MOL would involve receiver, for 

time, angle of arrival, signal profile and a voice channel. 

20.3.3 Importance of Test. 

LASERS have a diverse potential for future space missions because 

of their extremely narrow ber..mwidths, which would be advantageous for 

secure, wideband communication links, and for reconnaissance. The results 

of the tests will be significant in the continuing development of LASERS for 

these applications. The tests are necessary to evaluate the effects of the 

atmosphere on LASER radiation and the test will permit the evaluation of the 

narrow beam acquisition problem. This experiment can only be conducted in 

conjunction with a space platform since there is no reasonable way to simulate the effect of the atmosphere. 

20.3.4 Vehicle Requirements. 

Power: 

Volume: 

Weight: 

Weight of Steerable 

Platform: 

Stabilization: 

Aperture: 

LASER RX 

On-Board Only 

25 watts for 5 min 

periods 

1 cu ft 

20 lbs 

-SECRETLASER TX 

On-Board Only 

500 watts during 

contact period 

(5 min) 

1.5 cu ft 

50 lbs 

100 lbs 

SSM-50A 

20-5 

High rotational stability during test 

Laser system must 

be able to see radar 

transmitter thru corn- Same 

plete contact period 

(t 90°) 

This document contains information attesting the national atomise of the United Stores within the meaning al the Espionage taws 

Tide te, U.S.C., Section 793 and 791, the transmasion of which in any niannet to an unauthorised ;semen rs proh.bded by low 
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20.4 HIGH FREQUENCY IONOSPHERIC DUCTING COMMUNICATION - 

EXPERIMENT S-4. 

20.4.1 Objective. 

The test is to investigate the propagation characteristics of high 

frequency radio waves and to determine their potential to provide beyondline-of-sight communication links between space vehicles (at altitudes in the 

order of 200 N.M.) and globally distributed ground terminals and aircraft. 

The astronaut will be required to monitor and detect signals in the H. F. 

frequency band, and establish and maintain communications with ground 

terminals and aircraft. He will subjectively evaluate quality of the signals 

received and debrief results' to the ground. 

20.4.2 Description. 

The experiment is planned in two major phases: 

1. Detect and monitor the H. F. Band and note identifiable transmissions, particularly those which represent beyond-line-of-sight reception. 

Specific transmissions from ground terminals and aircraft, which already 

exist in large number, can be programmed in order to obtain duration and 

last-point contact with respect to the position of MOL. 

2. Establish communications with ground stations and aircraft 

and maintain contact as long as possible to ascertain if H. F. two-way links 

can be global and continuous. The equipment required on board will be H. F. 

panoramic receiver, H. F. transmitter, graphic recorder, with time reference and a twin track voice recorder. If H. F. support communications is 

planned for MOL, then this equipment could form the basis of the experiment 

if modified as may be necessary. Quality evaluation of a voice link will be 

done by the astronaut and also at the other terminals (ground, aircraft). 

SSM-50A 

20-6 SECRET 

Th.. document tOnt0.1St tnitl,.<1.0, affect...0 the .ta..oacti tieteate a. lee (Jaded Stntr. wOhtn the meaning of the ftp.oaoge la.. 

Tale 18. U S C . Sett,ea 793 and 794 the of racta..et In c^ vem,that•terl pcf,0^ Wan tt•tha It, 
NRO APPROVED FOR 

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20.4.3 Importance of Test. 

From the data obtained, it will be possible to determine the number 

and location of ground terminals and aircraft, which are necessary to insure 

maintaining continuous contact with orbiting space vehicles, and to predict 

the frequencies and power requirements for such communications. While the 

communication channels are likely to be limited in bandwidth, and therefore 

may not serve the purpose of linking an Orbiting Command Post to the ground 

for high rate data transmissions, they still can form an extremely effective 

back-up system for the essential elements of command and control. Further, 

a beyond-line-of-sight communication capability between Airborne Command 

Posts (AbCP) and OCP is highly desirable. 

20.4.4 Vehicle Requirements. 

Power: 100 watts when transmitting; 10 watts 

receiving only 

Volume: 

Weight: 

Stability: 

Aperture: 

2 cu ft 

50 lbs 

Not critical 

Not critical (antenna extension only) 

Thif document contotnt information °Heeling the notionoi oetente of one United Slates ...thin the meaning of the Stoionase.towt 

Title IS. Il.S.0 . Section 793 and 794, the trown.won of .0,0 o n one manner to on uwaotho.eef person is oteh•bitee be le. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SSM -50A 

20-8 -SECRETTh., document conto,n, ,nfotmot•on ottect,ng the not•onnt oetense o. the Untied Slates ..,th,n the mteonmg of the E,D.onnoe to., 

T.1. 18 U S C Sec on 79) 0,1 794 ,he Of Hn.rh .0 nny monne, to on vnoutho,•red person t, p•nh,b.ted by in.. 
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RELEASE 1 JULY 2015 

20.6 EXPANDABLE STRUCTURES TECHNIQUES - EXPERIMENT S-6. 

20.6.1 Objective. 

This experiment will provide the USAF with the capability of boosting 

into orbit minimum package-size structures which can be expanded into useful 

larger MOL's and space structures. The results of this experiment will have 

a direct bearing on whether or not any portion of a relatively large future 

space system, which of necessity must be partially formed and erected in 

space, can be so designed. 

20.6.2 Description. 

Four small expandable structure cylinders would be deployed early 

in the MOL mission. Orie cylinder will be constructed of airmat, one of 

expandable self-rigidizing honeycomb, one of a foamed-in-place structure, 

and one telescoping structure. Each cylinder will be pressurized to the cabin 

pressure of the MOL and will be inspected by the astronaut for structural 

integrity. Two small expandable solar collectors will also be expanded and 

rigidized to determine the ability to form useful solar energy conversion 

devices in space. These solar collectors will also provide sufficient test 

data to determine the feasibility of utilizing these types of structures for 

antenna systems. 

lEeREfSSM -50A 

20-9 

ihn document commni ffiformarion °fleeting ihe not.onol aete,te of the United States within the nleomeg of the Fswonag• 

Tate 18. U.S C • Sechon 793 and 794. the 'commission of which in any manner to on unauthorized person it prohibited by 10. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

20.6.3 Importance of Test. 

This experiment is needed to determine which of several types of 

expandable structures show potential for space application. Such applications 

include complete space stations, space station components, solar collectors 

and antennas. MOL will afford the earliest possible platform from which 

these experiments can effectively be conducted. Man will be needed to make 

detailed inspection of the rigidized shapes. 

20.6.4 Vehicle Requirements. 

Power: 

Volume: 5 cu ft 

Weight: 100 lbs 

Stabilization: 

Aperture: 36" x 18" 

Miscellaneous: A target is required. 

20.7 ANTENNA DEPLOYMENT, ALIGNMENT, AND POINTING - 

EXPERIMENT S-7. 

20.7.1 Objective. 

To deploy, align and point as necessary an antenna typical of those 

that may be employed in spaceborne high resolution radar equipment. 

20.7.2 Description. 

The astronaut will deploy (unfold or unfurl) an antenna of approximately 25 feet in length. Studies have indicated that this is a minimum 

length antenna for even experimental spaceborne radar equipment. After deployment, the astronaut will check the alignment of the antenna and adjust as 

necessary to maintain a phase relationship of 1/8 - 1/16 wavelength. If the 

antenna is designed for operation at X band, the alignment must be maintained 

to within .5.1 cm along the entire 25 foot length. The alignment must be 

SSM-50A 

20-10 -SEREThts document contains information ollectinp the notionoi defense of the United States within the meaning of the Espionage tn., 

Title 18. U.S.0 Section 793 and 791, the Iranimqvan 01 which tn ony manner to an unoutheiitect person it piohibited by low 
20.8 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECRET 

maintained in spite of the severe temperature variations that will be encountered as the MOL moves in and out of the earth's shadow. After alignment 

and at an appropriate time the astronaut will position the vehicle so that the 

antenna will point at a calibrated ground target range. Coherent R/F energy 

will be transmitted and the reflected energy recorded and stored aboard the 

MOL vehicle. If suitable equipment exists, data processing and signal analysis may be done aboard the MOL and the astronaut may adjust equipment as 

necessary to optimize the performance of the system. 

20.7.3 Importauce of Test. 

The application of high resolution radar techniques in space reconnai5 

sance is a tremendously complicated problem in which there are many scientific and engineering unknowns. Some of the major problems of the antenna 

are: its construction, deployment, and alignment, the transmission of R/F 

energy through the microwave plumbing. It is questionable if these problem 

areas can be overcome in space without a man performing a vital role. 

20.7.4 Vehicle Requirements. 

Power: 1 kw (short periods only) 

Volume: 20 cu ft in spacecraft 

Weight: 1000 lbs (includes extra batteries) 

Stabilization: 05 / Sec 

Aperture: Small viewing ports for astronaut to observe 

antenna and to assess antenna adjustments. 

-BRET- SSM-50.A 

20-11 

l'h,e document tome:sins onformohon °heeling the nahonot defense at the Untied Slates eedhln the meaning of the Espionoge Loyes 

Tole le, U.S C.. Section 793 and 794, the itansmqvion of wh,ch in any manner to en onaohoneed avian tt eitoh.boed by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

fi 

SSM -5 OA 

20 -1 2 

Thts document can't:m, onlormaiton affecting the nottonot oetenre of the Untied States *ohm the meorttng of the Erptonage 1.0.1 

Title IS. U.S.C., Seaton 793 and 794, the IrensmissIon of *itch n any manner to on unauthorised person is ptoh.bded by low 
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20-13 

This document contains information ollechng the Aor.o,,ol aerense or the tinted Stoles within the meaning of the Esc nonage sows 

Tale 18. U.S.( Section 793 and 791. the transnhts.on of which in any manner to on unauthot.ted person n ploh.btted by law 
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SECRET 

SSM -50A 

20 -14 SECRET 

This document contains information onecting the •ot.onai netense of me United States ...thin the meaning of the Espionage lo.s 

Title 18. 

U 5 C . Section 793 and 794. the transmission of which in any monnet to on unnuthoi.ted petson .s pioh b•ced by In. 
SSM -50A 

20-15 

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20.10 MAPPING AND GEODETIC SURVEY FOR IDENTIFIED POINTS -

EXPERIMENT S-10. 

This experiment has been deleted. The primary objective of this 

experiment is reflected in Experiment P-8, Autonomous Navigation. 

MIS document contain, inloemplion offect.na tne not•onoi nee,se 0. tee United Stnte, w ithin the meontna of the Etotonoge tons 

Title 18. U. S. C . Section 793 and 791, the «h•ch .n any mann,' to on unninhaiiced perion .s mob b•ted by to 
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-SECRETSSM -50A 

20 -16 

Th,s document conloonS infOrma,,en oltrc.m9 the n0.•Onoi oetemse of me United S,noes *Ohm the theonmg of the fsp,onoge 

18. U S C . Sect.on 793 and 794, the tennim.Nton of uhtch t o o■ty manner to on unouthottted per50., .5 pinh.b.,rd by In. 
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20.12 HYDROGEN REDUCTION ATMOSPHERIC REGENERATION 

SYSTEM - EXPERIMENT S-12. 

20.12.1 Objective. 

Evaluate component and system performance of a chemically regenerative atmospheric control system as an integral part of a life support 

system. 

-SEGRET- SSM-50A 

20-17 

This document contours infotrnahon afleChng the nao0,101 Cletense 01 the United States within the meonsng of the tip.onoge Lows 

Tole 18. U S,C . Semon 793 and 791, the transmission 01 which in any manner 10 on unaulhotized person Is proh,b.ted by low 
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20.12.2 Description. 

The basic system consists of a reactor subsystem in which CO2 is 

reduced to H2O and an electrolysis subsystem in which the water is dissociated 

into hydrogen and oxygen. Water removal and CO2removal systems are also 

included to make a complete atmospheric regeneration system. 

If the MOL consists of two pressurized compartments, it is proposed 

that the system be provided in one of the compartments for experimentation 

purposes. The compartment will, of course, include the basic ECS system. 

Samples of the gas stream will be taken periodically and analyzed. 

A gas chromatograph or mass spectrometer (expected to be available as part 

of the MOL monitoring equipment) will monitor all trace contaminants in the 

cabin atmosphere. 

20.12.3 Importance of Test. 

As mission times and the complement of manned spacecraft increase, 

a point will be reached in the not-too-distant future where the penalties for the 

use of expendable or open cycle atmospheric control systems will be excessive. 

Reliable high performance atmospheric regeneration systems will have to be 

developed for these long duration manned space missions. The most promising systems consist of reducing CO2 to H2O with hydrogen and subsequent 

electrolysis of the water to provide breathing oxygen. It is estimated that 

the cross-over point between this system and an open atmospheric system is 

between 30 and 90 days. Two-phase operation exists in the water condenser 

and electrolysis cell which requires verification in a zero gravity field. 

20.12.4 Vehicle Requirements: 

Power: 700 watts peak 

550 watts continuous 

Volume: 4 ft3 

Weight: 150 lb 

Stabilization: None 

Aperture (window) 

requirements: None 

SSM-50A 

20-18 SECRET 

This document content information collecting the nava:mai eetense of the United Stoles within the meaning of the Espionage taw% 

Title If1. U.S.C.. Section 793 and 794, the ttonsoliwon of which .n any moaner to on unOuth0“10d Stetson is proh.b.ted by las., 
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20.13 VAPOR VAPORCOMPRESSION DISTILLATION WATER PURIFICATION 

SYSTEM - EXPERIMENT S-13. 

20.13.1 Objective. 

Verify and evaluate operation of the system. 

20.13.2 Description. 

The basic elements of the system are an evaporator and a condenser. 

The water is boiled in the evaporator, the vapor is compressed and then condensed in the condenser at slightly higher pressure and temperature, which 

provides heat for boiling. Impurities are collected on a liner in the evaporator; as the system operates on a batch method rather than continuously, 

the liner can be replaced from time to time between batches. Liner replacement is required only about once in two weeks. 

The system is set up and waste water supplied. The quantities of 

both input and output (purified) water are measured. A chemical analysis of 

the purified water is made at increasing intervals, as system operation is 

verified. 

The crew will operate the system by supplying the unpurified liquid, 

starting the system, monitoring operation, removing the purified water, 

analyzing the purified water, and replacing the liner as required. 

20.13.3 Importance of Test. 

Waste water reclamation may be necessary for manned space vehicles 

having a mission greater than two weeks and which use a power supply other 

than a fuel cell (which produces excess water). Vapor compression distillation is attractive for military applications since it can be made compact. 

In one design of the system, it is made as a cylinder that rotates, theoretically making it independent of gravity. The history of life support system 

components and subsystems, however, shows a great reluctance to use parts 

that have not been tested in space. Thus space testing is necessary before 

the system can be considered for actual space use. 

SSM-50A 

20-19 

This document contains information affecting the not∎ ono, oete.,e of the United States »oh.n the meaning of the Ele'emege 

Tote IS. U.S.0 . Section 793 and 794. the flome.won of wh.ch in ony manner to on unouthor∎ ted person ot pfoh,boed by to» 
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20.13.4 Vehicle Requirements. 

Power: 

Volume: 

Weight: 

Stabilization: 

Aperture (window) 

requirements: 

300 watts peak 

75 watts average 

3 ft3 

45 lb 

None 

None 

20.14 PASSIVE PROPELLANT SETTLING SYSTEMS - EXPERIMENT S-14. 

20.14.1 Objective. 

Prove feasibility of using surface tension forces (wetted and/or nonwetted surfaces in conjunction with intermolecular fluid forces) to control 

location of liquids in tanks during extended periods of zero gravity. Demonstrate feasibility of expelling only liquid and/or only gas from a tank containing both, when using a fluid control device employing surface tension forces. 

20.14.2 Description. 

The basic test equipment is several transparent subscale tanks containing different liquids and different liquid control devices. Candidate liquids 

are liquid oxygen, liquid hydrogen, nitrogen tetroxide, and hydrazine. For 

the tests the tanks are placed where they can be observed and photographed. 

Still pictures are taken at regular intervals. 

If weight permits, a desirable addition to the test is to provide an 

acceleration table so that the effects of small accelerations, such as would 

be imposed by propulsion system start transients, could be studied. 

Having the astronaut as a test conductor will allow, in comparison 

with a test on an unmanned vehicle, (1) use of color film for data recording. 

(2) various camera angles and lighting set-ups, (3) selection of data, and 

(4) application of different perturbing forces. 

SSM-50A 

20-20 —SEeRET-- 

This document contains information &feeling the notionot oetense of the United Stoles within the meaning of the Espionage Loon 

Title 18, U.S.C. Section 793 and 794, the tronsmiss,on of which in any mariner to on unouthorited person is prohibited by low 
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-SEW20.14.3 Importance of Test. 

Current operational techniques of fluid control at zero gravity employ 

"active" devices such as bladders or diaphragms that physically separate the 

liquid and gas in the tank. These techniques have been acceptable for many 

applications, but are not without limitations. The "passive" fluid control 

technique holds promise of being more universally applicable and may eventually result in lighter weight, more reliable, and less complex systems than 

possible through "active" fluid control techniques. 

The "passive" fluid control technique will have applications in many 

areas, e.g., propellant systems, life support systems, and power systems. 

This experiment concentrates on applications to propellant systems, however, 

results will be applicable to other areas as well. "Passive" settling techniques promise to provide both positive expulsion of propellants only (no gas), 

and control of propellant location in the tank so that vehicle c.g. is predictable and unchanged at main engine ignition. Tests aboard the orbiting laboratory will serve to provide feasibility during extended zero gravity conditions 

and determine effects of disturbing forces created by reaction control system 

operation and propulsion system on-off thrust transients. These effects cannot be observed without orbital flight. 

20.14.4 Vehicle Requirements. 

Power: 

Volume: 

Weight: 

Stabilization: 

Aperture (window) 

requirements: 

150 watts peak (primarily for illumir 

nation for photography - may not be 

needed) 

1 - 5 ft3* 

15 - 115 lb* 

None 

None 

Miscellaneous: Recovery of film is required 

* Depends upon (1) number of liquids tested, (2) whether means are available 

to recover and use the liquids, (3) whether the acceleration table is included, and (4) whether the cameras are charged to this experiment. 

SECRET SSM-50A 

20 -21 

That document conto,n, Informo,on coilco.ng ,he eot.onot oetense of one Unded States w ,th,n the moon, og of the fsof000ge 

,A 11 S C Sert.on 793 '94 fh, I ronur",,, orof nn,0 nay manna to on onnohn,.zed persOn of oh b.,ed by Inn 
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20.15 COHERENT E-M PROPAGATION AND ANTENNA LOADING -

EXPERIMENT S -15. 

20.15.1 Objective. 

To determine phase distortion and other effects due to the ionosphere 

on e-m emanation from satellites. A secondary objective is to investigate 

the problems of antenna loading and high power r-f distribution in the high 

vacuum and temperature extremes encountered in space. 

20.15.2 Description. 

The experiment will consist of a series of tests designed to measure 

the extent of phase distortion of the ionosphere in two way propagation of r-f 

energy. Calibrated ground targets will be used. Measurements will be made 

and recorded at both the ground targets and in the satellite. Simultaneous 

measurements, performed from the ground, of the existing atmospheric, 

tropospheric and ionospheric conditions will be made to provide correlative 

data. 

The astronaut will adjust the various controls for optimum system 

performance and also vary parameters to determine loss of performance. 

An antenna and T/R unit will be required in addition to such ancillary 

equipments as tape recorders, clocks, etc. Photographs will be taken to 

determine the extent of cloud layer, moisture content and to some extent 

other boundary conditions. 

The-experiment will also determine the effectiveness of various 

design for loading the antenna with high peak powers during the experimentation. 

The astronaut will make repairs and adjustments as necessary to 

complete the experimentation. 

SSM-50A 

20-22 

Th.t document contours .nforrnot.on offecling the nat,onot netense of the Unoed Stntet wohoN the meonmg of the boo:moor lows 

Tole 18. U. S.0 . Section 793 and 794, the ocntmqi•on of och.ch .■1 nny monnel to an unnuthot•ced person .% wnh,b,rcl by In. 
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20.15.3 Importance of Test. 

The tests are needed to provide basic data for the design and development of a high resolution radar system. 

20.15.4 Vehicle Requirements. 

Power: Never more than 1 kw for short 

periods 

Volume: 10 ft3 

Weights: 250 lbs 

Stabilization: .05 °/Sec 

Aperture: Window for viewing antenna and 

antenna alignment 

20.16 SOLAR X-RAY WARNING SYSTEM - EXPERIMENT S-16. 

20.16.1 Objective. 

To monitor incidence of soft X-rays. To correlate these occurrences, 

with observed solar activity to provide a means of forecasting lethal high energy 

proton showers. 

20.16.2 Description. 

Small porportional counter and associated electronics will record 

incident X-ray flux and spectra. This information will be recorded. If the 

flux exceeds a pre-set level, a warning device will be actuated, and the astronaut will take precautionary measures against the deleterious effects of 

possible high energy proton showers. 

20.16.3 Importance of Test. 

Manned orbiting missions in a polar orbit may receive lethal proton 

dosages. It is indicated that these showers may be preceded by sharp increases 

in solar X-ray emission. If this is the case, this experiment will demonstrate 

an excellent warning technique for astronauts. 

SECRET-. SSM-50A 

20-23 

Thos document contours .niewnot.on ollechog toe .01,01 noeme a n•e Unded S•ntes ..ho the 9,e0p9..:9 . 00,4 ,:hpels9,b.0:(9d941.91:1 

T.d• 18. U S C . Sect 793 and 791, the nantniqs.on «hqn any monnol to on onoythe,*teri 
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20.16.4 Vehicle Requirements. 

This equipment may be part of the space vehicle environmental monitoring equipment. If so the experiment will be dropped. It will require a 

telemetry channel for use only when the radiation exceeds a specified level. 

Power: 100 watts 

Volume: 1 ft3 

Weight: 10 lb 

20.17 MATERIALS DEGRADATION AND MALFUNCTION ANALYSIS - 

LaPTLRIMENT S-17. 

20.17.1 Objective. 

The purpose of this experiment is to evaluate degradation and analyze any malfunction of MOL components and materials under actual space 

flight conditions. The spacecraft and its auxiliary equipment will be used as 

the object of the tests. The primary goal of this experiment is to determine 

the cause of failure or degradation, if it occurs. A secondary objective is to 

determine whether or not current strict specifications on materials and components can be relaxed without sacrifice in reliability. Maintenance and repair functions will be demonstrated by the astronaut. 

20.17.2 Description. 

Various subcomponents of the MOL vehicle will be tested at regular 

intervals for degradation and/or malfunction. These include bearings, thermal control surfaces, solar cells, lenses, windows, filters, mirrors and 

mating metal surfaces. Some carefully controlled sub-standard components 

will also be tested in order to evaluate the validity of current tight materials 

specifications, particularly in solar cells and thermal control equipment 

where the effects of sputtering, micro-meteoroid erosion and temperature 

effects will be observed and measured. Portions of other experiment equipment may be used. Recovered test samples will be used to correlate space 

and laboratory performance. 

SSM-50A 

20 -24 SECRET 

That document contoms onlottooNon otlechng the not.onu. netente ot the Un.ted Strom ...Wm the meonmta of the Etwonage 

Tole 18. U S C Seclion 793 and 794. the ttestms..on 01 .h.,h any manner to an unauthat.yed person .t ptoh.b.tect by la» 
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-SEW20.17.3 Importance of Test. 

Degradation and minor malfunctions might occur which in themselves will not compromise the MOL mission. However, knowledge of their 

magnitude will permit optimization for missions of longer duration. The relaxation of current tight specifications could result in significant cost reduction for future MOL subsystems. 

20.17.4 Vehicle Requirements. 

Power: 100 watts 

Volume: .5 cu ft 

Weight: 35 lb 

20.18 MULTIBAND SPECTRAL OBSERVATIONS OF PLANETS -

EXPERIMENTS S-18 (REV.) 

20.18.1 Objective. 

To measure portions of the IR radiation spectrum of terrestrial 

planets, Venus and Mars; to gain knowledge of the thermal and chemical 

structures of their atmospheres. 

20.18.2 Description. 

The equipment of P-10 is to be used to observe Venus and Mars. 

Scanning will be accomplished at low resolution over the entire spectrum 

available in the P-10 package. High resolution scans will be made in selected 

bands in the 3-4.5p. range (CO, N2O, Sinton bands), and in the 7-1511 range 

(N2O, CH4, 03 , CO2). Long integration times will be required, up to 30 

minutes, requiring tracking either by the P. T. S. or possibly the star 

tracker. 

SSM-50A 

20-25 

This document contains information collecting the national detente or the United States a Ohm the meaning of the Espionage Lout 

Title le, U.S.0 Section 793 and 794, the transmission of *hick any manner to on sinouther.red person is proh,bired by to* 
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SECRET 

20.18.3 Importance of Test. 

The P-10 equipment provides a unique opportunity to obtain spectral 

measurements of Venus and Mars utilizing cooled, sensitive detectors. No 

such detectors have been planned for space experiments up to this time. An 

attempt was made on Stratoscope II to observe Mars with a helium cooled 

bolometer, at 80,000 ft; atmospheric absorption was found to be still great 

enough to be a serious problem. The test is of national significance, since 

plans are being laid to explore Venus and Mars by spacecraft. Atmospheric 

compositions are still not well known. 

20.18.4 Vehicle Requirements. 

No new equipment is required in addition to that for the primary 

experiments. The long term tracking technique requires further study. 

SSM-50A 

20-26 -SEGREf 

This document contains inforniorion affecting the norionot oetense a, the United States within the mooning of the Est:00n0ge 40., 

Title 18. U.S.0 . Section 793 and 794, the tronsmission of which in any mann!, to an unQoihonred person a prohibited by low