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NRO APPROVED FOR RELEASE 1 JULY 2015
2 7 OCT 1989 411111111-
NOFORN
-FOR-REAH3f-Otittr-
PRELIMINARY
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
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NRO APPROVED FOR RELEASE 1 JULY 2015
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
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NRO APPROVED FOR RELEASE 1 JULY 2015
FOREWORD
This Preliminary Technical Development Plan (PTDP) is addressed primarily to the in-house and contractual activity planned for the Pre-
Phase 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 useful-ness of man as an element of possible future military space systems. This definition will precede 'selection of a Laboratory Vehicle con-tractor 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 pro-ceed 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 Manned Systems
SSM- 50A
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NRO APPROVED FOR RELEASE 1 JULY 2015
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.
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NRO APPROVED FOR RELEASE 1 JULY 2015
-SEM-
INDEX
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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NRO APPROVED FOR RELEASE 1 JULY 2015
SERET
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 Pro-
gram 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 pri-
mary 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.
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NRO APPROVED FOR RELEASE 1 JULY 2015
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 mili-
tary 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 per-
formed in an orbiting laboratory designed to be launched by the Titan IIIC
Standard Launch Vehicle using a Gemini B Spacecraft for personnel trans-
port. 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 de-
finition 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET 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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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET
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 experi-
ments, which provide measurement of man's utility; and, secondary experi-
ments, 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 labora-
tories' output, to develop a specific program responsive to Navy require-
ments 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 forth-
coming 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 Pro-
posal (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
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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
NRO APPROVED FOR RELEASE 1 JULY 2015
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, fabri-
cation, testing, and services required to accomplish the MOL program.
Associate contractor procedures will be used with the Aerospace Corpora-
tion 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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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET 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).
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NRO APPROVED FOR RELEASE 1 JULY 2015
-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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NRO APPROVED FOR RELEASE 1 JULY 2015
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 head-
quarters 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.
-SECRET- SSM -50A 2-1
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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
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SECRET
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 employ-
ment of state-of-the-art design, and the integral launch mode for initial
operations. The major problems that lie ahead in the definition and execu-
tion 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 proce-
dures, and the planned management structure for accomplishing the MOL
program; in addition program responsibilities and specific tasks to be per-
formed by various industrial and government organizations are presented.
The time-phasing, inter-relationships, and the major decision points con-
cerning these responsibilities and tasks are presented in the schedule net-
works 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 operat-
ing 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 tech-
nical 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 integra-
tion. 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 re-
sponsible 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, count-
down, 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 sub-
stantial 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 contrac-
tors 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 man-
agement 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 fixed-
price basis. For Phase II, the method of contracting selected must satisfy
the basic requirements for program integrity and unity. Careful considera-
tion is being given to performance as an incentive factor. The objective of
both the government and contractor should be to give the best possible prod-
uct. 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 appro-
priate. 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.
SECRET SSM-50A 3-3
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—SteREf 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 organi-zations. 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.
SSM-50A 3-4
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SECRET
The SSD organization set up for MOL facilitates central manage-
ment 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 require-ments 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 manage-ment 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 up-dating 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 spon-sors 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 respon-
sible 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, in-
jection into orbit, and functional testing of spacecraft vehicles and payload
equipment including scheduling, integrating, and conducting orbital experi-
ments. 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 experi-
ment sponsorship.
3.2.2.2 Office of.Aerospace Research (AFCRL) - Will provide Aero-
space 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.
SSM-50A 3-10 •
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-SECRET-
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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: GSE-
Overall integration of the MOL system, design compromises among sub-
systems, 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
-SECRET- integration, 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 3-12 'SECRET-
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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 respon-
sibilities 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, re- entry, 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 responsi-
bilities 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 compet-
itively 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
SSM-50A 3-14
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NRO APPROVED FOR RELEASE 1 JULY 2015
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of 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 sub-
stantially 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 infor-
mation 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 configura-
tions 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 re-
quired 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 pre-
ferred 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 head-quarters.
Task 1 - Equipment Definition and Techniques Studies Task 2 - Astronaut Functions
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--SfeRET- Task 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 per-forming 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 opera-
tion 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 consist-
ent 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 con-clusions 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 deter-
mined 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 requir-
ed 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 con-
clusions 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:
SSM-50A 3-22
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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 time-
phases 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 infor-
mation 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 con-
duct 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. Specifi-cally, 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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IfeRET- w. 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 Pre-Phase I Study).
Task 11. - MOL Experiments Studies.
Task 12 - Prepare MOL System Performance/Design Require-ments 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 engi-
neering 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 devel-opment 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 Aero-
space, 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 prelimi-
nary engineering that is required to define the MOL system along with devel-
oping 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, includ-
ing 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 de-termined 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: dis-posal 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 opti-mized 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 contrac-
tor 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 end-items 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, Docu-mentation 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 Trans-portability 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 pro-vided 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 -SEGRET-
TM 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
•
NRO APPROVED FOR RELEASE 1 JULY 2015
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 pro-
cess, 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 develop-
ment 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.
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NRO APPROVED FOR RELEASE 1 JULY 2015
SCCRET
SSM— 50A 3-34 -SECRET-
This 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
--rsEeREf- precedent 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 be-
tween 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 in-
tention of the Air Force to contract directly with McDonnell for the prelim-
inary design of the Gemini B. The work statement for the Gemini B Pre-
Phase 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
The concept for MOL includes the acceptance of NASA experi-
ments 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 -SEM-
Th., 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.
NRO APPROVED FOR RELEASE 1 JULY 2015
SECTION 4
INTELLIGENCE ESTIMATE
NOT APPLICABLE AT THIS TIME
DATA PERTINENT TO THIS SECTION MAY BE GENERATED DURING PHASE IB
SSM- 50 A
NRO APPROVED FOR RELEASE 1 JULY 2015
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
NRO APPROVED FOR RELEASE 1 JULY 2015
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
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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
NRO APPROVED FOR RELEASE 1 JULY 2015
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
NRO APPROVED FOR RELEASE 1 JULY 2015
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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GEMINI B ADAPTER -423.00 REENTRY
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1359.10
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Figure 6-1. MOL Flight Vehicle
SSM-50A 6-2 -SECRET-
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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 RELEASE 1 JULY 2015
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 per-
forming 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 spec-trum 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, air-craft 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 simula-tions or aircraft tests.
g. The cost of the experimental program should be minimum, making use of existing equipment, and provide a compre-hensive 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
NRO APPROVED FOR RELEASE 1 JULY 2015
-ffERET- i. which contribute to the development of mili-
tary technologies which are scientific experiments of national importance may be considered as secondary experi-ments, 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. situa-
tion, 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 switch-
ing to alternate equipments, adaptive programming of propellant, selection
of alternate targets, and deployment of defense measures. The servomech-
anism 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
-BRET- missions 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 neces-
sary to analyze each military space mission and determine how man could be
used to enhance the mission capability. While man can provide trivial func-
thins 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 attrac-
tive 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 pro-
vide, 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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NRO APPROVED FOR RELEASE 1 JULY 2015
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 contri-
butions 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 qualita-tively 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 perform-
ance 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 direct-
viewing, 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 com-
puter 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-RET-
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-SERET- proportional 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 acquisi-
tion 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 deter-
mined 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 reso-
lution 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 astro-
naut 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 per-
formance 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 paral-lel 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
Th.' document (onto.., •ntot — al ctt. ol1e:t :• • LP. •ca S•::•e• ••• .ne ..e.3".^; .Ne fin 0^CC:r
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NRO APPROVED FOR RELEASE 1 JULY 2015
-SECRET- Z. 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 astro-
naut'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 intelli-
gence 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
NRO APPROVED FOR RELEASE 1 JULY 2015
-SEGRET- 6.1.6.1.4 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET
SSM- 50A 6-12 -BRET-
111,1 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", Tole 18, U.S.C . Sechon 793 and 794. the ticrwn,,,on of wn.ch in any macre' to on ynovIhnt.,,r1 pennon rs pb,b.babd by lb.
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 pro-
cedure 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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NRO APPROVED FOR RELEASE 1 JULY 2015
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 verifi-
cation 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 other-
wise deserted ocean areas which lie near or under the MOL orbital path
during local daylight hours. The astronaut will be given pointing instruc-
tions (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 -BRET-
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NRO APPROVED FOR RELEASE 1 JULY 2015
Sr
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-of-view,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 oper-
ations. 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.st transmissibility 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.
--SEGREf- SSM-50A 6-15
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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 -SECRET-
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NRO APPROVED FOR RELEASE 1 JULY 2015
-SERET- other 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 neces-
sary 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 con-
trolled, 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 evalua-tion 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 intelli-
gence,, 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 Experi-
ment 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
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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 con-
siderable 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 over-
come 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 Self-
contained
Tool Kit 5
Camera and Lights 20 1. 0 750
62 6. 2 850
SSM-50A 6-20 -SEGRET-
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NRO APPROVED FOR RELEASE 1 JULY 2015
-SECRET-
6.1.6.6 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 opera-
tions, 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 environ-
ment 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 loco-
motion, 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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NRO APPROVED FOR RELEASE 1 JULY 2015
-MET- After 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 experi-
ments 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 extra-
vehicular 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 approxi-
mately 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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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET
6.1.6.7 - Experiment P-7.
SSM- 50A 6-23
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NRO APPROVED FOR RELEASE 1 JULY 2015
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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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 experi-
ments can be performed without any hardware change, however, two typical
experiments can be described: In the first type, the classical orbit deter-
mination 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 astro-
naut 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
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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 6-27
TT 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 RELEASE 1 JULY 2015
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 measure-
ments 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 -SEM-
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NRO APPROVED FOR RELEASE 1 JULY 2015
harbor activities, shipping and wakes, air field activities, meteorological formations, geological formations, under-ground 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 air-craft 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 pre-determined 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 6-29
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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET 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 - Experi- ment 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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NRO APPROVED FOR 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 over-loading, 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 ft3 volume, 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 weight-
lessness 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 bio-
medical 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 suffi-
ciency statements given in the Test Objectives. Measurements will be
SSM- 50A 6-31
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NRO APPROVED FOR RELEASE 1 JULY 2015
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 electro-
lyte 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 measure-ments, 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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NRO APPROVED FOR 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 quantita-
tively 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 capabil-
ities) 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 compart-
ment 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET 6.1.7 Experiments versus Missions & Applied Functions.
In order to provide a graphical assessment of how well the pri-
mary MOL experiments will provide a measure of man's utility in critical
applied military mission functions, Table 6-2 has been prepared. All func-
tions 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 all-
inclusive, but are considered representative. Unlike the primary experi-
ments, 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 poten-
tial 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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Tole I0, U.S C., Section 793 and 794, the ttantmitsion of which in any manner to on unautbanyea perms" is presh•b..ea by low
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NRO APPROVED FOR 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 equip-
ments; 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 stabiliza-
tion 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 6- 3-
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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 simula-
tions, 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 RELEASE 1 JULY 2015
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 approx-
imate 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
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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET
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 experi-
mental 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-REf-
6.1.11.1 Pointing and Tracking Scope Study.
While the concept of manned tracking for precise IMC determi-
nation 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 acquisi-
tion probability, spatial clutter filtering, location fixing, and
gain.
SSM-50A 6-41
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NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET 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 -SEM-
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developed 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
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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 recommen-
dations 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 surveil-
lance 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 inter-
faces, and to establish performance criteria for measurement of effective-
ness. 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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4EGRH- 6.2 MISSION PROFILE.
The MOL flights will be conducted from the Titan III launch com-
plex 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 investiga-
tion. 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 sub-
systems 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 astro-
nauts 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 re-
ceive 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 configura-
tion questions will be made prior to issuance of the Labordtory Vehicle RFP.
Others, especially those which cannot be made independently of the Labora-
tory Vehicle configuration, must await the concerted definition effort of
Phase IB.
SSM- 50A 6-46
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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 instal-
lations) and possible the transtage for on-orbit propulsion requirements.
A representative Orbiting Vehicle might have a weight distribu-
tion 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
V- The 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 experi-
ment 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 esti-
mated 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.
-SEGREf- SSM-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-RET- 6. 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 in-
stalled 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 opti-
mum 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 mini-
mum 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 foam-
filled 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.
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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 pro-
mising 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 in-
house, 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 contami-
nant 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 develop-
ment and space use by NASA. However, it is considerably heavier and its
SSM- 50A 6-51
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Title IS, U. S C , Section 793 and 79e. the transmission el which in any manner to On toroulhoirzed perrrn is prahrhited by In.
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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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-BRET- safety 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 self-
induced 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 Pre-
Phase 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 in-
clude 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 ele-
ments 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 Labora-
tory design in the following primary areas: reliability, safety, availability,
and the trade-off between redundancy and maintenance. These in turn in-
fluence system weight, volume, operational flexibility, and cost. Bioastro-
nautic experiments are expected to be primarily manual. Military experi-
ments will probably be semiautomatic, and will be designed to take advan-
tage 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
IfeRET- SSM-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 ,h any 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 investi-
gations 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 in-
corporated 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
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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 investiga-
tion 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
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SECRET 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 configu-ration questions in this discussion are covered in the McDonnell study.
SSM- 50A 6-58 SECRET-
This 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 retro-
grade 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 re-
entry 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
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ini
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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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-S-EGRET- may 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 Labora-
tory 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 pro-
pellant load and because of altered flight characteristics, including acceler-
ations 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. United States 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
NRO APPROVED FOR RELEASE 1 JULY 2015
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
NRO APPROVED FOR RELEASE 1 JULY 2015
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. Addi-
tionally, 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 mechani-
cal 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 pos-
sible 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+
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-SECRET- SSM-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
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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 com-
plete 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 Vehicle-
Astronaut 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 maxi-
mum 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 success-
ful 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 pro-
grams 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 per-
formed 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 --SECRET-
Th•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.,
NRO APPROVED FOR RELEASE 1 JULY 2015
processing on-board the vehicle, at the tracking station, and at the
Control Center.
Based on data obtained to date, the objective that no develop-
ment of TC and C ground equipment shall be necessary appears to pose
little constraint to the MOL System, with the possible exception of wide-
band data links for special experiments. However, a 10 Mc link capability
already exists at two SCF stations which may suffice, with little modifica-
tions, 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 once-
per-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 pro-
cessing 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
NRO APPROVED FOR RELEASE 1 JULY 2015
--SE-RET-
6.8 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 inte-
grated 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, injec-
tion, 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 all-
systems 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.
■
NRO APPROVED FOR RELEASE 1 JULY 2015
Two methods of operation at CKAFS appear possible at this
time. These are (1) installation and checkout of the Gemini B and Labora-
tory 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 antici-
pated 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.
-SECRET- SSM-50A 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.
NRO APPROVED FOR RELEASE 1 JULY 2015
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 dif-
ferent 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 re-
covered 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 Labora-
tory 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
--SECRET- SSM- 50A 6-70
NRO APPROVED FOR RELEASE 1 JULY 2015
SECRET
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 Medi-
cine 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
NRO APPROVED FOR RELEASE 1 JULY 2015
6.13 MOL SPECIFICATIONS.
The MOL system specification will include the performance
and design requirements for each segment of the MOL system. The pre-
liminary system specification breakdown is presented in Figure 6-9. Sup-
porting 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..
NRO APPROVED FOR RELEASE 1 JULY 2015
-SE-CRET- List 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
Syst
em
Sp
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s
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
NRO APPROVED FOR RELEASE 1 JULY 2015
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 OUT-LINED IN SECTION 6 AS ACQUIRED DURING PHASE IB
SSM-50A
NRO APPROVED FOR RELEASE 1 JULY 2015
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
NRO APPROVED FOR RELEASE 1 JULY 2015
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)
NRO APPROVED FOR 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 RELEASE 1 JULY 2015
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 esti-
mates of the funding for the Phase I effort and the areas where the funds
will be applied.
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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
NRO APPROVED FOR RELEASE 1 JULY 2015
SECTION 12
REQUIREMENTS
. . NOT APPLICABLE AT THIS TIME
DATA PERTINENT TO THIS SECTION WILL BE GENERATED DURING PHASE I
. -
SSM- 50A
NRO APPROVED FOR RELEASE 1 JULY 2015
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
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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 pro-cedures, 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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-SECRET- 7-1:71refrrientb1543"&el+brlir-
COPY
CHARTER FOR THE DEPUTY COMMANDER,
SPACE SYSTEMS DIVISION FOR MANNED SYSTEMS
The Secretary of Defense has directed that the Air Force initiate the de-velopment of a Manned Orbiting Laboratory (MOL). Specific guidance from OSD and OSAF has emphasized the need for deviation from standard manage-ment structure and procedure because of the complex nature of the program, the cooperative effort with the NASA that will be involved, and the require-ment 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 manage-ment, 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 estab-lished procedures to assure support of all elements of the program.
5. Field detachments at test sites and factory representatives at se-lected 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 im-plement the approved program.
""PCIR-erlortekortrti&E-49144331-
SSM-50A 13-2 4EGRET-
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SECRET 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 tech-nology 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 re-quirements of the division or center involved. No manpower spaces will be transferred at this tim7117-ii-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 pro-vides maximum benefit to the Government. It is therefore ne-cessary 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
754r51- SSM- 50 A 13-3
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(CONFIDENTIAL) C 0 P Y 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 termi-nated 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 con-sider expansion of an ASSET type program to obtain hypersonic flight data during lifting re-entry. SSD is assigned management responsi-bility for this expanded ASSET type project within the total MOL Pro-gram. 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 re-view 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 pre-paring 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 re-quired 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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4EeREfi- COPY
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 FORTH-COMING 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 FOL-LOWING PURPOSES: (A) IT WILL SERVE AS THE SINGLE AUTHORITATIVE REFERENCE DOCUMENT ON THE MOL PROGRAM AND, AS SUCH, PRO-VIDE THE FRAMEWORK WITHIN WHICH ALL SUBSEQUENT PROGRAM ELEMENTS AND ACTIONS CAN BE INTEGRATED BY SUBSEQUENT PERI-ODICAL 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 DE-FINING 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 PRE-PARATION 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 CONSTI-STUTE AN OUTLINE AND FORMAT OF A COMPLETE TDP FOR THE CON-DUCT 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 EQUIP-MENT. 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 IM-AGE MOTION TO BETTER THAN 0.2 PERCENT, AND TO FOCUS PRE-CISELY (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 UNSOPHISTI-CATED WAYS. FOCUS EXPERIMENTS, IF NECESSARY , CAN BE CON-DUCTED 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 EXPERI-MENTS IN THE 1 APRIL SUBMISSION OF YOUR PTDP . 6. THE FOLLOW-ING 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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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 CON-DUCTED 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
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REPLY TO 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
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(CONPIDENTIAL)
(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 justifica-tion underlying your recommendation for sole source procure-ment.
c. Request that you review the work statements for the Pointing and Tracking Scope Definition (3. 3.1. 2. 1) and Autono-mous Navigation (3. 3. 1. 2. 6) studies as to the feasibility and desirability of extending the experiment efforts to include experi-ment 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 headquar-ters 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.
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SECRET
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
SSM- 50A
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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 estab-
lish 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 avail-
able 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 pro-
ducts 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
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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 con-
tractor 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; accom-
plishment 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 SECRET 17-2
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 Pre-
Phase 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 devel-
oped 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 re-
sults 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
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This document contoms information affecting the natianel avenie at the Unaed States ..thin the ryteen.ng of the Espionage So.ss Title IL U.S.C.. Section 793 end 79A, the transrn.ssion of which in any manner to on enoetho..yed pe,son .s p.oh•b•ted by lae.
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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 Engin-
eering and Technical Direction (GSE/TD) during the Phase IB period.
These major products will be reflected in the products provided by the con-
tractors 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 addi-
tion 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 ef-
forts, 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 17-4 ▪ S
▪
ECRET- This 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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INDEX
SECTION 18
CONCEPT FOR US NAVY EXPERIMENTS IN THE MOL PROGRAM
Pa g t-
18.0 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 Non- Rotating 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
SSM -501. 18-iii/ iv
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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 pre-
pared 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 num-
ber 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 deter-
mination, 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 mis-
sions, 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
SSM-5n:\ 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 sy-
tern 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 sys-
tems should be approximately 250 miles in advance of the spacecraft. All-
weather 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
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photograph 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 de-
termine 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 posi-
tion 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 posi-
tion 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 infor-
mation. Finally, there must be means within the data processing for in-
structed 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 inte-
gration 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 astro-
nautic 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 ship-
ping 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 pro-
vides 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
SECRET SSM -50A 18 -8
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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 sen-
sors, 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 deter-
mine 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 cer-
tain 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 require-
ments. 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 surveil-
lance 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 deter-mine whether the radar antenna can be a rotating one as is preferred, or whe-ther 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 essen-
tial 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. Sche-dules 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 re-ceived 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 ship-board, 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
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Control mission. However, no suggestions with respect to specific experi-ments 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 ex-
periments; 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 correla-
tion 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 capa-
bility 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 ex-
periment are included in the estimates for the ocean surveillance system;
however, some additional funding may be required to cover costs of the spon-soring 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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SSM- 50A 18-20 -SECRET
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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
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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 experi-
ments 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 man-
kind. 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 ex-
tending its ARGUS studies to the MOL system. In the case of the remaining
two experiments on nuclear radiation monitors proposed by the Naval Radio-
logical Defense Laboratory , it is considered advisable that these be in-
cluded in the MOL vehicle because NRDL has certain advisory responsibili-
ties 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 SECRET-
This 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
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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 tempera-
ture of electrons within this plasma was included. The far -UV orthicon was
included because of its military mission interest, its need for manned opera-
tion, 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 sen-
sors 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-
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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
-SECRET- SSM-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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-SEM-
SECTION 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 re-
quired 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 instal-
lation, (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, ear-
phones, and recorder will be required. Recorded profiles will be trans-
mitted 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 trans-mitted 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 sys-tems could be transmitted to a space vehicle at other frequencies and re-transmitted 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 communi-cation 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 establish-
ment of narrow-beam communication links between moving terminals. Be-
cause 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.
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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 scintil-
lation.
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 simu-
late 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
-SECRET-
LASER 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 beyond-
line-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 trans-
missions, 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 refer-
ence 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,
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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.
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SSM -50A 20-8 -SECRET-
Th., 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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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.
lEeREf- SSM -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.
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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 approxi-mately 25 feet in length. Studies have indicated that this is a minimum length antenna for even experimental spaceborne radar equipment. After de-ployment, 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 -SERE-
Thts 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 encoun-
tered 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 analy-sis 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 scien-tific 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
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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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-SECRET- SSM-50A 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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SECRET
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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-SECRET-
SSM -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 re-
generative 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 CO2 removal 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 promis-
ing 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 VAPOR COMPRESSION 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 con-
densed in the condenser at slightly higher pressure and temperature, which
provides heat for boiling. Impurities are collected on a liner in the evapo-
rator; as the system operates on a batch method rather than continuously,
the liner can be replaced from time to time between batches. Liner replace-
ment 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 distil-
lation 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, theoreti-
cally 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»
NRO APPROVED FOR RELEASE 1 JULY 2015
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 non-
wetted surfaces in conjunction with intermolecular fluid forces) to control
location of liquids in tanks during extended periods of zero gravity. Demon-
strate feasibility of expelling only liquid and/or only gas from a tank contain-
ing both, when using a fluid control device employing surface tension forces.
20.14.2 Description.
The basic test equipment is several transparent subscale tanks con-
taining 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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-SEW- 20.14.3 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 eventu-
ally 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 tech-
niques 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 predict-
able and unchanged at main engine ignition. Tests aboard the orbiting labora-
tory 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 can-
not 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 in-cluded, 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",,, or of 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 experimen-
tation.
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 develop-
ment 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 astro-
naut 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...:900,4 ,:hpel,s9b.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 moni-
toring 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 ana-
lyze 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 com-
ponents can be relaxed without sacrifice in reliability. Maintenance and re-
pair 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, ther-
mal 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 equip-
ment 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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-SEW- 20.17.3 Importance of Test.
Degradation and minor malfunctions might occur which in them-
selves will not compromise the MOL mission. However, knowledge of their
magnitude will permit optimization for missions of longer duration. The re-
laxation of current tight specifications could result in significant cost reduc-
tion 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
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