1111111111111111 - National Reconnaissance Office · 1111111111111111" MICROFILMED BY TIM APRIL 1964 Status as of 30 JUNE 1964 r;i:,":',,j1 C.] 3‘..-ae-A-994 • SPECIAL HANDLING

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

al. CONFIDENTIAL SSM-50A ***'■ °(\

That document conto,nt .nlotrnot.on otterfing the nOttOnot delenie 04 the Unaed Stove% ..ohun tee meaning orihe Etotonnoe low.

Tole 18. U S C Section 793 and 794 the ttnn,m•s‘ton of wh.ch to nny manner to on unouthottied netion eunh•boed by Inn

NOFORN

DOWNGRADED AT 12 YEAR INTERVALS; sz) NOT AUTOMATICALLY DECLASSIFIED

DOD DIR 5200.10 1:10 I ••k


2 7 OCT 1989

This edition has been prepared to correct and to update

the April 1964 MOL Program PTDP to reflect program

activities and planning as of 30 June 1964.

NOFORN vaimF. CONFIDENTIAL SSM-50A

(This page is Unclassified) This document <entrant infoimahon allotting the netiOnet detente of the United States within the meaning of the Espionage lo.t

Title 18 U S C Section 793 and 794 the frcf,m.,,on of ..firth monad to on unauthraized poison it pinh•hited be la.


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

L S6' H ' "

. B/ AIto

E

• g

R

I

, t •

" '.Brig Gen, USA Deputy Commander for Manned Systems

SSM- 50A

the nn , re•rs. rt,• ■■•., 'Ars 11•■ •.ed ...•A • ■•■■• ol the ho.nArlor

'fl U S C 793 c^n 77.. the ••••• ,o


TABLE OF CONTENTS

Section Page

* 1 PROGRAM SUMMARY 1-1

* 2 SCHEDULES 2-1

* 3 PROGRAM MANAGEMENT 3-1

4 INTELLIGENCE ESTIMATE 4-1

5 OPERATIONS 5-1

* 6 ACQUISITION 6-1

7 CIVIL ENGINEERING 7-1

8 LOGISTICS 8-1

9 MANPOWER AND ORGANIZATION 9-1

10 PERSONNEL TRAINING 10-1

* 11 FINANCIAL 11-1

12 REQUIREMENTS 12-1

13 AUTHORIZATIONS 13-1

14 GENERAL INFORMATION 14-1

15 SECURITY 15-1

16 BIOMEDICAL 16-1

* 17 PRELIMINARY DEFINITION PLAN 17-1

* 18 US NAVY EXPERIMENTS 18-1

19 NASA EXPERIMENTS 19-1

20 SECONDARY EXPERIMENTS 20-1

* Indicates the sections included within this PTDP. The other sections are merely added in tabular form for continuity to conform to the PSPP outline which will be formulated during Phase I.

-SECRET- SSM-50A

Th., docaynenv conba.ny aslor,aa,,aa ollecbag the nobana! defense of *Mr Un,red Sm.v. tt•,n .ne Yavaa.ng of the f tom., ng e too,

7,d, 18 U S C Seo.on 793 a^d 791 the barva,..0" of wn :b nay ,aaa,e, ro a^ anaOho—zed 90,%o^ t p•nt• b••ed by In.


-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

ri

1

This document contoms rnforrno.on allechno the nolionot overlie or the Untied Stoles w Ihm the rnean.ng of Ih• Esptonog• Loon

Tole 18, U S C Sect.on 793 end 794. the tponsm.it.on of wh,ch nny manner to on unoulhor.red person Is peohtbded by low


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.

-8EGREf- SSM-50A 1-1

.■•■•••■•

Tho document contotny .nformotton affecting the not,ono, netente of Inc Untted Sintey ..,th.n the meontno of the fsghonooe Ion%

T.tie 9 U S C Section 793 and 794 the homrh,,on at nhn.h nny rnnnner to on unnuth0f.4,1 falcon 1 wrh•bord hy


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

SSM- 50A 1-2 -SEeRET-

iMf document co, ,efo,motron olleet.n9 the nat,eno$ nest's. 01 the Unless Strifes eat', the thean.ng 01 the Ete Onage toe"

18. U 5 C Section 793 and 791. the ocnsm•is,on of eh.th 11,ty manner to on unnohn,./erl person wob.b.terl by lb.


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

ihaf document contain, mlenmemon offechng the sof.oso, ovesse Usoed Stoles •ithin the meaning of the Eso.w.oge toss Tate 18. U 5 C . Section 79) and 794. the Itceitoits•on of .h.ch in any moomet to ott octoothotqect oelsc , •f Otoh b•ted by Ion


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

Th, document eent0.e■ Intottnotton ntino•no the ocot,e co o,c Un.teci S,cort ..th.n the theaelea at the f■Plee0ge tee.% T.ri, 18 U S C Sechon 793 and 794 ,he ercosm.,,,on of NImh ivy monne, to on onnothottted nett., ts otnbthord by In.


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

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

Title 18. 11. Si C . Section 793 and 794, the trons.won of which to any manner to on unauthorized person is pooh.bded by low


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

Th,1 document contains tolOtmotion &feeling the nahen0. oetense or the United Stntes within the meaning of the Espionage loot Tile It. U S C Section 793 and 791 the tronsmii,,on of which in nny mann., to an unnuthwired person •s woh.bitecl by In.


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).

-SEGRET- SSM-50A 1-7/8

This document contomt Information °fleeting the not.ona* aelente of tne United Slates v.ithin the meaning of the Espionage Lass

Title 18. U 5 C . Section 793 and 794, the Itensmission of ..h.ch in any manner to on unouthotqed pet,o, .1 caoh.b.ted by la.,


-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

This document contains information affecting the notionot oetense of the United Stoles within the meaning of the Espionage toot

Tale le. U S C . Section 793 and 794, the tronsm.ssion of which in any manner to on unauthorised person a prohibited by low


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

This document commas inlotmation ollectIng the nahono. ammo of the Undid Stales withal the mooning of the EH:nonage lows Title 18. U.S C Sect nn 793 and 794. the itonstn.ss.on of whtch In any manner to i , unouthotiten omen n otah.htted by low

2

4

0

1.<

1st

4-4

4

4

Pre

-P

roje

ct

De

fin

itio

n P

hase

0 CA La OC 0 CI

.4 Cl.. =

CL _,. Oft ›.

a an CO

>- g 4%* ca la OJ cl. i- OC toC

O. tnrs CI. to -..... 0, 2 ea a

CU 413 ft

OC innt = I- tn ...l

:3.1 . . .. oft"4 oic add; 002! t , . . ..: .1 : f I 8 . 8:21 ac n oc!

0 cil I= . t 4r) ..< ac 1- )- ca a.

>- 1- I.- z 0 (.0- 0 n)- co = c. = L., p w Cr) 41/ = 0 } ej L. OC 0 in. I..

:;;;;!!;:i ll :

La 1..2 c' cac0 44 .-144 al Es 0 u, Q, 2 c_. al cc = < ~ .E. .- 0 in• W Z p 1- 1.. 4.) Z E

cn ac .=. c3 Off _

Z-

03LaS 2 1...: :II. ti7i,t 4.. .c.-•' nil. :cot

0 La "a g a MC.% F0 406- t,ICI ...1.4 ea cr) c. 2 cz "< co Is 0 : me-) p 2. a us> i... _ 9 = ca vs — z — La Ii- ca 0 = .4 <

I.% 041) 2Li g Z> /r: 1".', s .--• 1 ..c ...ic L. 1-11. ..- : . . ..c c) ,D 1- ar a. ■Ic 2 < — 2 < ." ....1 ...1 IO li. cn 0-

II 41 41 41 41 41 4141 41 41 41 41 41 41 41 41 41 41 41

SSM -50A

2 - 2 - SEGREf This document ,nloinma ,ws ollechng the not.onoi create of tee Unaed Soon .ahat the oleo...9 al the fsptonage TIfie IT, U 5 C , $eciton 793 and 791 the itcmnu,..o.• of chick as nay monnet to on unnuthotaed pcma, .t pooh baed by to.

Pro

ject

De

fin

itio

n P

hase

9 •

a.

4

PH 11

CO

NTR

ACTS

C.) ‘1.1

CS la/ •.1 tr)

c., cc ..rc ..... 1- u, a a .,„h 1- )- _1 F:t cc 4/3 c, 5 a. cz-a 0 a CC 0 0 f„,

C., Ct c:, cr, U. C., la. = (C) .... la. 2 n.. 1...■ .... .... C:1 CI. R ° La itCe I ' 4 Z— : 6. . O

. W Co Co ...c i•-• .....F: W: lig Q.. Or 1....

CL ›. CC gri 2 rs ck- ..z 1.—

a_ I.- -..--..'"' CL.C6f3C BC°

CC tat = X ...I 0 i''' lal

LcC c:a CD

(i) CC C.7 •X 2 0 Ct

45 OC N la 2

. • • • • • • • • • • • •

AWARD PH II

CONTRACTS

SECRET SSM —5 OA 2 —3

Ma document contomt .niermoNen oltect,g the not.onot omente o• Litnted States meo..ng of the fto.er-c;e to., To1. 18. U S•C . Settton 793 and 791. the tt.mtmt,on of nntth , ,,,.^•e• to on uno.the• it, ae to s am, b.teo be tc.

4.1 c.,

a

>11

8 8

4 4

SSM -50A 2-4 4ENE-f-

4 •

;-. O

ry

4-

4 I

4

•

S

Maste

r P

rog

ram

Sum

mary

Sch

ed

ule

5

• 4

• I

•

SECRET

74.1 document coot .at .^/0,,,I,On .11.0ng fie ntven, 0/ the Utica Stores hobo. the meontog of the Eawonage loaa Lae 18 U C Sec to o, unnutho..,,r1 pets, otoh•b■ ted by love

r • : . . iy; • •• • I • ' :

10 Ili 4- ; • ••• • ' . • • ;

- • • '-'•-; 4 - : . • ; •• •. • -;•-■ ••-••••,-• •••t • 44 : ' ; ; ; ; ; . i .. • i • • • ;

, . ; . •, , , . • • • • . .. • , ; • . . .

1 ! t 111117inT , : ,..1 ,,[ MINI!

II:" . . , ; t ; ' • ..

. ; • . • ' . "

. ;

;4H

• • • • I I -I- • -•• • • • . t - i • : t"•4 • --t- :-;• •• • • : -• • • : ' • ; . • . i ; 1 r...1 • • • : ; • , • ; j j

•

. 1 , i- ;;di- till i • j j j •-•''''-' t •••••• ../. t-44- i4 1 .

• : • . , , •! ! !.,41 I.4-. t -t•

1 1 1 11 t 1 ... : . i ,

tt! I--, ..1

-l-±itli I -1 4-j-- .1...-1. ---1 !.. : . • '-- • f ./-1-.,-.I.•.: • • [_4_,.....:.. t. 1 , -• ! • ! • , •

,,,,

=, ...,-. , ; i ; i• .--t--; ■ •: -1.-

2 -..,..4-4 • , I I . 1 ; t -, • , --- t-t- I tt ' I t •i-il -14...• 1

tti ..- '!-- t--; 1: +1..:

1 ; 1 1 "1 :: ' t-i

' - 1 , - !. : : : : , I . , i - : -: •t ■ -

: ' ' 1 a -4-:-•-•'•'•"'l .••• • l''''"'l

.. , .. „ .t "--, -l- -4 - .4 - -:- • • - .'. - • -

:ki".1.44 1.4.

. ' ;4

4 "4- • ■ •

4 -, ; • I • i: I . I -:. ' I. .L..-1. • .4:._ . • ••• • ' 1 . T-I •••• ;.-. .-; 4 4 . , ,"

I

..!_4. 4...: . , .-1-4- —

.--t t--1•;;-••• . l'-i-'—

•0

E -1--;;"4-...4",:.:: : u3 ......... `-`, -.--.4 . " ; ; .. . . .. ..

. ; ;4 ; ; ;41

. I. :. 1. - ' ; ; 7 ...

. ; ;

, ..1..1 .4. ; . 1..;• ; ; -. r ! '

,I.:rt - ll:I- ! 'I' :- " : .. ; : ',-;-' ' '. - 1 : l'r-'•[=.1:'— ; ' '

• , , ..

-_L-

.• „_ ; ., : . ; ; • , : . , : . • , . . I.: - . , . ; , • . ; • ;

‘o ... ,

I :-,-L

I •

1 4

-1

.• , , ... ; ,.. 72.

. m t -

•

4 ' .

I

"

. • t 1-11. 1, ; ' •--1

o '.• .

t .4 .

. .

.. . ,

. I I I, .

i • I, 1- -I i - -I • 1-- j-lt I- 1- ■ _r i--1•74---1 I

.' I I • I 41-

2 =

'

4 !

' • - • • I i • :-• • • ' I ' • • ' I I ' I" -

I

E

,5 . •••■E

l./ N no .... :,, ,,, .4 z Z Z

at

: , a .< .4 • ;TO %7 trz 2 ... ,

i !.: , "

:: i : , ,

•1 1

I j I I I • • ; •

;

, i

1 , I;

via::

1 iti !ill! 4:4 ,... • 0 '

I • 1 1

i • ' t i — ! i

, : ,

j • Ii •

.: , :

: , 1 ' • - • 1 •

• 1 I I ' :

• • ! : • II

Or r :

-SECRET SSM -50A 2 -5

This document contains information olleming the notional oetense ot the United Staley within the meaning al the Espionage teas Title IS, U.S.C.. Section 793 and 794, the ;imam...on ot which in any manner to on unauthorized action is ptohdaded by low •

Fig

ure

2-4.

Rela

ted

Fli

ght

Te

st S

ch

ed

ule

4 a 4

a

H

0

•

SSM -50A 2 -6 -SEGRET.

•-fri -1-.1 th4

91 •

a

INA

WI

•

•

•

• • •

•

•

4

•

4

I

54

E

•

• • • a

• v • •

a

a

a

Acti

on

Sch

ed

ule

SEE

Th.s doctmen, can:cons aftecnng tne oWensc of the L.I..ted States ....ht.. ,he weantno 01 the Fsoronoge Tale 113. U S C . Sew.. 793 and 794. tho tnc tm,ct on 01 wit.ch 01 any mann.. to an anouthw•led pets°• ts pcoh.b•ted by 10...

SSM —50A 2-7/8 -SSC-

a a

a

alb

mit

U

It%

a

WyV

1 • A a 'NE

a

a

O

to

U co

O

0.

cn

0 00

Th.s document contd., ...0•"3./l, t-e -at-t-o deeeee e o• U.1.107 States 1,n the meantng of the Ettho.oge loot Tole ifl. U S C . Scion 79) and 794 the ht,ste.thc. nen1tt und.thet :en .1 ato'• b.ted by 1,,


INDEX

SECTION 3

PROGRAM MANAGEMENT

3.0 INTRODUCTION

3.1 MANAGEMENT PHILOSOPHY

3.2 ROLES AND RESPONSIBILITIES

Page

3-1

3-1

3-4

3.2. 1 Manned Systems Organization 3-4

3.2.2 Support Agencies 3-10

3.2.3 Aerospace Corporation 3-11

3.2.4 Participating Contractors 3-11

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

3.3.1 Pre-Phase I 3-14

3.3.2 Project Definition Phase I 3-28

3.3.3 System Acquisition Phase II 3-33

3.4 DOD-NASA RELATIONSHIP 3-33

FIGURES

Number Title Page

3-1 Deputy Commander for Manned Systems 3-8

3-2 MOL Systems Program 'Office 3-9

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

SECRET

SSM-50A

This document content inlormatian &letting the notional oetente 01 the United Pates within the meaning of the Espionage lows

tine IS. U S C Section 793 and 794 th e of which in any manner to an unauthorized person is prohibited by low


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

This document conto.ns infoinsol.nn ntterfing the notions defense to the United Stotet u.dhos the meaning of the Espionage lows

Tale t8. U 5 C Se,,on 793 n.ri 794 the 04 wh,,h .n nny ennnn, to nn unnuvh,,,ed person ,1 Tnnh.bitrd by In,.


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.

SSM-50A 3-2

TT,ht,iyeum o"ecr•ng • 0,01,1 cle'en40 0' .00 UÎeoe the meon.ng of the t ■n•tv■ oge Lc10,

18. U 5 C Sect•om 793 and 794 ,s•on of on, fnon"e, fo on .-c101,0,700 00,0" bt 111.•

io-


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

Th.s docvrneAt cemtn,n% airo ^q ,c • n• a. U. 'en S ■ rvm tr■■• rpew...9 f .0.,

TM, U S C Sec1.0, 793 c-q1 793 •••• nn-^r• la c- ro•,...


—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

That document coolant 'he •a' Iternie 0, mr Un ■ lvd n.lhth the ouvumfig al Ihr tio,onooe to.. Tole 18, U S C Section 793 nail 794 the thththn.,..oe of enoh .n any mann°. 10 on unovlho,eed person y peoh.b.led by In.


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

doromene IrOn,n•nt •nfol••••• f..11, r• • (1,6,11 11,1,


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.

SSM- 50A 3-6

Tht3 document tonto.n3 Informohon 011441019 tee "elt•e•^0, detente of me Untied State% the reeon.ng of the bn.c,nge to., Idle 18. U S C . Seet.on 793 and 794. the 'IL:mm.33.0n of ..h.ch r)ny marmot lo ne weouthot.4ed person .3 otoh•b•ted by le,


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.

SSM-50A 3-7

Tn.4 document eonto.n, mlenmett.on ewe,• -- err n• • . • . ne •e •■■• n Un.fen Sn19.4 n n. tne meon•ttg or 11,0 • r.o, IR U S C Sect•on )9) 0,1 '94 the t•ttn•m 1- 01 nt•-n

Dep

uty

Com

man

der

Fo

r M

an

ned

Sys t

em

s

O

3

SSM-50A 3-8 SECRET

Tins document co htems ohloth,ohen ellechhe the nohenel pelvis, at the Uhae41 States ...Pun the rneeneng of the 61.4.09e toot, tale lfl, U S C Section 793 and 794. the Itensh,y.en of eanch in any manner to on soloodhoraed person :s prohsbded by lam

MO

L S

yst

ems

Pro

gra

m O

ffic

e

■ 1 1 1 1

INIMMEN■■■

28

,o mz _ Do

0 o mo.:LK -td, Qt.a. r

r-1

1->

>.

a 0

•••■=111/

I.) CI

0

IMI1■11. V•11•11■11.

0 co

IM•1■11.

--SEGREf- SSM-50A 3-9

This document COhthilli information affecting the notional defense ot the United Stoles within the meaning of the Espionage Laws. Title U.S. C.. SeChen 793 ond PK the fronsmossion of which in ony manner ha on unautholised pesson is plohibited by low


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 •

Th., document conto,ns ,niotmohon ot.ect•ng tne • n,ono, tiven,e n. tt, Unaed Stoic, thy meon,ng of the ho.ono9e lu., 1,1. 1 8. U 5 C Sector. 793 and 794 thy 1,1, of .^,n • n fly mn.nrt 10 On unnualo,ted pet,on pint bird by In.

-SECRET-


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

-SECRET- SSM-50A • 3-11

Thq document contcn, onloomohon of t.e • 0, 0.0. nee,.. 'p. U^ teu Shirt n Pit //,000 . 00 0/ itl• to..

1.0. Is. U S C 793 and 794 the bo"..n tf 0^ of ^..ch n., mo.ne. to o• unn.the cH pe,10^ 11•/rd b, In.


-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-

TA, do,rnent Tonto.., ,n101.1n,on o..ettonci .,•■• •to.onor nee rn,r ni the Unacti S.tort ..th,n th, .91,0nong 01 the 0,“

T... 2 9 U S C Seo•n• 791 ri,f '94 •A n^ It, In.,


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

This document contains information affecting the national defense 01 the United Slates within the meaning of the Espionage Lows title 18, U.S.C., Section 793 and 794, the ttan,,,,,an of which in any manna, to an unavihatired person is pieshibiled by law


-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

document conto.ny .nlotnnot,o,, of lett•oo the e0,400. aetenw of tee United Stott., woh.n the meon,n9 of the fip.oroge taut

TO le 18. U S C Section 793 and 794. the I,Cntmutc•On of ...h.ch nny Tann!t to an unaulhOtoted Berton ptok.h.terl by In..

p


'SECRET-

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

MKT- SSM-50A 3-15

Thd docerneht combo', ,efot.eet.ort our° et, tt,e ••ri' 0";1 cle.e"fe 0. 'Pe Swrs 'he meue.n9 of the bn.o,ntye to.. Tole S C Sect en 793 rod 791 the 04 .^.'h 10 0^ yeavihe. reef petyc, t n'n' n•.eti by In.


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

SSM-50A 3-16

Th■ S 0040nem tontems 011,0,ng ,h, Unord Stoles sine Ike meon,ng of the f ■p•oneee t ow%

Tole TB. U S C Settee 79] and 194 of .1,r1t ,n nay manner le an anoulhof ■ terl (lemon ■■ m01,110444 by on


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

4EGRET- SSM-50A 3-17

Th,t document conlomt infotmobon olfeched ,he eat•onno detente of UrlPred S■ flfri ...bell the meaning of the ftwonnne Lost Tale Iff . U S C Secbon 797 and 791. 'he 11/:/.1,n, r, of un,,h mnnne, to on unnuihn..zed ne,on .t rwth.b.■ rd by


--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.

SSM-50A 3-18 —SEW-

de, ow. nt 'ewe "., o..0. Ih• • ,I•t,...• lows

T... S C S. .../1 793 noel 79,1 .by n•• ■ unn.lhn• • /rd pr•t0+ !Wok I, .4,1 by in•


SECRET

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.

--SfeRET- SSM-50A 3-19

111.1 CIOCOMIn, 10.41..1 tl,.r■ I ^0 ..e ..a. o• •• ■• 4,1 !S .W.% .1Nr of .0. (in

7,4 is U S 793 00,1 79, In, n.., n• !el p..4 0^ I•,• 1,0e. b,


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:

SSM-50A 3-20

detyMtn, icolcbm ,.no wr • 111.ntr oI tip Unded S ■ eit•t .•11,A IA. 0,•0^..0 0$ lb. 1...

My II U S C Sa hot. 19) and i94 oh, "K.* h n", ID nn v.fivikt.../.,1 In.


SECRET

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.

SECRET SSM-50A 3-21

1 h,i document conimnt .nlormnt.on ane, 1.ng thr 0. Undett the nlenning of the f ■n.onncir On, I•fle IB U S Sr.'," 79) f),(1 794 .he of r. ,,h no, m 00,0 to on 0.0,01h,,,r1 0,0 0,0, Io,


SECRET

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.


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

Th., docu,en, con,o•-, ti" ,c1 o. •


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.


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

SECRET SSM- 50A 3-23

Th., do,senenl ""0.•0^ • c• S. •e.: .• - •-ecs^ nn a ..e fin . ow.


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

SSM-50A 3-24

Thd document conto,n, .nietenn•aon r..• f•••• • j• o• Uteri A.,./t the meon.ng of filo EsO•Onogy 1.ae IB U S C '91 ... : . • ._ .^ ,1^- ••• In..


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.

-SEGREF SSM-50A 3-15

This document contains information oftetfing the notional oetente 01 the Unded Starer ...thin the meaning of the fig:nonage to.,

Title 18. U S C Section 793 and 79A. the Iton..m.i,on of ...h,ch in any manner to on unauthot.zed oettan groh.bited by 1on


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

SSM-50A 3-26

Th.f document content Pnfotmot.on Oftett.ng the .he Un.ted States «•rh.n the meon.no of the Rn•onage toes

Tote lfl. U S C Sect•on 793 and 794 the tro,,,,,.nn of ..••■1 any manner to on ,,nov thor.,,r1 nem,. n ornh bated by in.


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

-SECRET- SSM-50A 3-27

11.4 tomo.ny .nlo•n.nl.An .111....A9 Am.nnitl drl.m. al the Un.tyd S1,,evy *oh.n the enynnow3 at the tic...m.9. In..

1..1* IS. U S C Seth*. 793 and 701 the ..0.1,”41.0. o1 wfm.h an am, .AAAAt. to on unov.A0..D.1 De•ton at 0•rh.ptted by to.


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.

SSM-50A 3-28

,,,, •■ • ■ •1 et, 11••••••ti • ,,,,,, w•-•••••1•


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

SECRET SSM-50A 3-29

TK1S dO(.0nrnt yontoottt tolotototton &letting the notoonol &demi. of the United SOO., with., the rnentung of the hptonope loom

Ittle 111, U S C Sethon 777 and 791. the oon‘o,tbon of ...loch to cloy toonoet to on voonthottted Verson is p•otobtred by to.


SECRET

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.

SSM-50A 3-30

lb.. do,,,ent gonto.n‘ ■ nfo.0,1 noitonof defense of the 1.10,ed S.W.% ....Ow, Stir roenn.og of the e.p.onnq. 1,1. 18 U S C 797 and 794 the 'rant .Ton Of wh.,h .0 0.11. ^ ,̀0000 01 00 unnvfho..:erl p.,on p.ohoh,.(1


SECRET

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

-SEM- SSM-50A 3-31

I'

I

1'

'4

Th.% doc,flent ,,,1O,"3,0's 0..ere n9 nee se o• •re U,Pect 0. •me Ett .on•


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

•


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.

ER

OS

PA

CE

SY

ST

EM

S D

IVIS

ION


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

Fig

ure

3-3

, A

sso

cia

te C

ontr

ac

tor

Str

uctU

re F

or

Ph

ases

I &

II


--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

Tole f9. U S C Sect.on 793 o^c1 794 the ter. m s. o^ of ■•••• •t, om n^c ..ô^ê• to o- u,O,,0,c-te f netio^ rvoK b•,ed by In..


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.


SECTION 4

INTELLIGENCE ESTIMATE

NOT APPLICABLE AT THIS TIME

DATA PERTINENT TO THIS SECTION MAY BE GENERATED DURING PHASE IB

SSM- 50 A


SECTION 5

OPERATIONS


THIS SECTION IS ADDRESSED TO PHASE III OPERATIONS WHICH IS NOT A CONSIDERATION IN THE MOL PROGRAM AT THIS TIME

SSM-50A


INDEX

SECTION 6

ACQUISITION

Page

6.0 SYSTEM SUMMARY 6- 1

6.1 MOL EXPERIMENTS 6- 1

6.1.1 Objective of the Experiments Program 6- 3

6.1.2 Criteria for Selection of Experiments 6- 3

6.1.3 Basic Manned System Considerations 6- 4

6.1.4 Mission Analysis 6- 5

6.1.5 Experiments Definition 6- 7

6.1.6 Primary Experiments - Assessment of Man's Utility 6- 8

6.1.7 Experiments versus Missions & Applied Functions 6-34

6.1.8 Secondary Experiments 6-34

6.1.9 Summary of Vehicle Requirements 6-37

6.1.10 Summary of Simulation Requirements 6-38

6.1.11 Summary of Funded Definition Studies 6-40

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

6.2 MISSION PROFILE 6-45

6.3 VEHICLE SYSTEM 6-46

6.3.1 Orbiting Vehicle (OV) 6-47

6.4 LABORATORY VEHICLE 6-48

6.4.1 Structural Arrangement 6.4.2 Astronaut Transfer

6.4.3 Environmental Control 6.4.4 In-Space Maneuvering

6-48 6-51 6-51 6-53

-SECRET- SSM-50A

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

; 8 ■ ; S f .•,. ',1 r3,1 794 • • •• vor, .h.cM1 ••• ony n nc. to nn vnoutho•./c•d . ■ woh.h.,ed by In


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


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


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


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

Th•t document canto., •tot•no•,oe oê:• rg the -.3, a-a ne•e^te o• •ê Un•+en S•o•ns A the ,coetho of the Eto•eôae Lou,

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

GEMINI B ADAPTER -423.00 REENTRY

CAPSULE

T IIIC STA

LABORATORY LAB MODULE

VEHICLE

TEST MODULE

TITANIC

T-III C STA

1359.10

SEPARATION PLANE STA

77.000

Figure 6-1. MOL Flight Vehicle

SSM-50A 6-2 -SECRET-


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.


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


-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

SSM-50A 6-4 -sEefitf"

Th.s doc ument canto., ,IG ■ Ta,C, a••••', • a' U,,frt 5.ntes no.,” ■111, ,,,CO,'.,'() 01 PAc hil.(,(1.e

Lite 18 U S C Septet 793 ond 79.1 Inc 0• of in nn k,nnufht..,,f b. is,


-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

T ,oe 18 U 5 C St:, o^ 793 '72 •fte •• •-• -

(SNOISSIK 11113.1.-011CYI • 110 xlaansa)!) SOISSIDCrl

x )4 x X X X X X

3S1,13.130 33.17131.VS X X X X X X X

NoIl.1/113410 •TV11X1f3N X X X X X

ONI11111/ X X

20tSVNal.NIVII )4 )4 x X X X X X X X X X

.1.N3msnrav mom x x x

NoLLVOINMIXOD X x M X X X X X X X X

NOLLV1.311•11131.NI oxissaoova viva X X X X X X X X X X

70131.NOD 3131H3A X X

NOM013410 110SNSS X X X X

1.1331/1.1.511101/ 110SNaS )4 )4

DNISMIOd 110S1335 X X X X X X

NOIL0373S 110SII3S X X X X X X

01.11510V11.1. 130111/1 X X X X X X X X

NoI.I.Vm1111110S10 CINC10110XDV11Nomsmoov .130/WI

X X X X x 110111NOOD211 N113.1.1V41

Noitismoov .1301IVI x X X X X x

MA

N'S

CR

ITIC

AL

A

PP

LIE

D

FU

NC

TIO

NS

PO

TE

NT

IAL

M

ILIT

AR

Y

SP

AC

E M

ISS

ION

S

.1

). a 23 . 2o .4

V 2 t a. , g o z . < '2 2 2 ii c>4' .14 O 'z' 14 6/1

t4 ol o a

1 o 1.

1. 4 m 213 :74..

7:.d ; 1 <,.. 1.: is ...1

: A 4 °.• 2 3 li -5 g

g: ...0 A a.< 1 g -: i 3 2'.. : o: a ,t 2 5., c. gi m f:1 aZ -i Z'; 4 8 8 ux148

X P.' 1...

0 .

o u 0

..;

no

34 S

Z 14

1 .2 4

2 '''.1 w Tr, °CZ F. . 4 .11. In <

SSM-50A 6-6 lEORET-

Thts document eonto.n% tnloron000 alley:tog the .ot.000t oeteofe of Untied Stole, «,IhVI the etcontng of the Etrooltage toot Tale 18, u.s.c . Swam 793 and 791. the aces...won of «htch olny manner to an onaulhottml person s■ Noh bard by lbo

Man

ned

Mil

itary

Mis

sio

n A

ssess

me

nt


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

Th., doc,,fnent ours ,,ng the no• ona. flete.,e at the Uh.tecl Stnte, A.., the rneon.no of the E.p•onoge lo., ince 18 U S C Sect,on 793 one 794 the on of .n o••y manner to 0n vnnuthn•de,1 person- .t ptah,h.trd by In..


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-

Mit document compos ,nfpcmcp.on offectmo the nafionol Detente 01 the Un'ed Slates ...oho the cneomng of the Etwonoge tont Title IS. U.S.C., Section 791 and 794. the Puntnust.on of tuh.ch .n on ), monnet to on unnutho.recl pemon wah.boled by no


-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

Tale 18 LT S C Seccon 793 c-ct '94 me k. 04 ^ :••1 77,•o- r•,- o •nn b ■


-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


-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.



This document contains otto,mohon &Iwo° the not ■Onel aelense of the Untied Stables *ohm the meaning of the Esponage tows Tote le. U.SC Seaton 793 and 794, the Itomm.won of whtth en ony manner to on unouthottieti person t, plohtbdeti by to..


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.


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

Thd document conto.ns mlomloficm cow n the â•o•n nve-se a• Unita $m.1.1 mecm•ng of he Eso•o-e;e :ant T ■ ae 18. U.S C . Stchon 793 and 79e the non,n ty a- of :h •^ C"y 0,0^"et to 0" VÔ.thC• tem b •ea by Ian


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-

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

Tole 18, U S C . Seo,on 793 and 74e the twe.in,s•on 01 en.,h .n nny mnnnet to an unnuihoo.ted nelson .1 nroh.h.ted by Ins


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.


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.


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

Ihrt document conform inlormot.on allechno the nohonoi cletente ot the United States *Ohm the meoning 01 the Esp.onoge tont Title It, U.S.C., Section 793 and 794, the IICMST.11.011 Of which m any monnerto on unouthoneeri person n proh.b.ted by la.



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


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

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


-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

This document Cont0,,1 ..10,"0,0" 0..00 Ag tAe ■ n• neene ..e U-•ron Street the .-eott.e9 o. the Etn•e-azte lees Tole S. U.S C . Sect.on 793 o,c1 791 the f,51,15 %, 0- 0/ •h n e^r mo^ê• to e- u.tovthet ten ne.se- s b .ed by 'ee


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.


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

Th., docwroe,,, co0.0•0‘ .010,0,0,00 00,0,00 ,00 ^c0•000. ov<.0%,. 0. 0,0 I.M.'oci Sfroes wah,n 'he meon.ng of filo Esp,o00gy Ion, To?, 18 U S 0, P93 "0,1 ").1 .n.,..0. 01 ev, mnnne, It) rs, fle, f0n 0201,41.1,1 by In.


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.


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

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

tary peculiar equipments.


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

This document contours Inlotmohon olNanio the nmwnal 0110,110 orthe Untied States wolun the mecmung of the E19.0.0Q. lows Title 18. U. S.0 . Section 793 and 794. the Irensensis$On of whet In ony monnef 10 On unOu1110.terf person a dioh.b.led by low


--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.


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.


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-

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

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


-SECRET-

6.1.6.6 Extravehicular Activity - Experiment P-6.


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.


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.


TMs document contooyy thlotmot,oh ottect,p tt•c• cle•e^ye o: •t•t. U,•teo Swes tY•cot,,9 of the E. côp. yo.,

Tile 18. U S. C . Sectton 793 0...d 791 the loc.,. :h ••• 0., ^•0.-e. to 0- „.o.thc• ne•to- o •ep b,


-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.


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

Thy. document coma,hy ,h(h,nahen ollect.no the ehlieen. oetente ot the Untied Strom ,e,thIn the rneon•nsi of the lip.onage Lae*

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


SECRET

6.1.6.7 - Experiment P-7.

SSM- 50A 6-23

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

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


SECRET

6.1.6.7.3 Importance.of Test.


SSM-50A 6-24 SECRET

TI,,, doconenf contomt m101.10,0,1 ottect,9 tee rot•O^cit net,se ot tt•t• '.1"tterl Sottr, th•n the ttteon.ou of the iso.0,,o9e la..

Tale t8 U S C Section 793 and 791 the of .0...•h m nor manner 10 nn 7,1 ,ter•rv■ north 11..rd h. In..


SECRET

6.1.6.8 Autonomous Navigation - Experiment P-8.


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.


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

111.s doconen, coelo,s 91.ecl ■Pe -a• z'c ove-se .ê U^ San'es - wec,•-.3 a' E‘o e-7 ;:e Tole 1 8. U S C Seo,o,, 793 c-d 79-1 'he s• o^ c' •11 r ma"-e• c. ,..-n-lhe• fe ne..2- •e.̂.


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

known methods of orbit determination. Once the orbit parameters have

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

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

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

position to a surface point position.

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

essentially a refinement of the orbit whose parameters are known fairly

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

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

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

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

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

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

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

small variations in the computed position from the predicted position are

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

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

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

The evaluation of the experiments will be made on several

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

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

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

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

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

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

future position, designing maneuvers to produce the desired trajectory,

and to operate the spacecraft without ground support.

6.1.6.8.3 Importance of the Test.

The navigation and position fixing experiments are an important

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

operation inherent in a manned spacecraft. The complex array of

SSM-50A 6-26 SECRET

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

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


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.


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


6.1.6.10 Multiband Spectral Observations - Experiment P-10.


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.


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-

Th.s document conto,ns ,nlotmot.on ottect ■ng the no..ono ■ oetense o• tne Un.ted Suet "Aho, the .eon.,,g of the E,n.0e0oe 10^, Tole 18. U.5 C . SechoA 793 and 794. the oonsnuwon of .uh,h nny monnet to on unouther•ted person .s ptoh•bard by Ina


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

Th.1 dotvmeno confools •Mo••••,•00 n••cc, •g •-r t-- re•r-ir o• ••r S••:•r..s - •r. ••: C. 0-, .o+•


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.


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

docurne., toMo.ni offe,,ng ,efen, 01 1 ne UniS Sarr e, n•thal The meoeTng of The Eth.ohoge loos

tale I U 5 C Se,t.on 791 and 794 ,he of no.. h .n rnanPr , 10 nn unnohr,,e,1 gwrso., n ponh•hond by In.


SECRET


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.


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

Thn document conto,‘ .nformotton offechng the nohonot oetense of the United Stoles w•th.n the triconmg of the Eso.onage Lou t

Tole 18 U S C . Sechon 793 ord 794 the uon,m,...on of Nh,ch nny monnet to On vnnuthIV.ter1 oet,On otoh b.ted by low


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.


Th, dOcwrnem. co-to, •' 4,-.■ •••••;.•oP • a. ,^r, e,• • r... ,h0 SW, e. nlean.h(1 .1

U S r '.•.••••o^ 793 ,^•1 '94 ^ •.1 tel h.trdI Tic He.


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

Th., (Ohio, °ê° ng •-e U- .en S•n'es he eneon•ng 'he ha 0^0.71e the 18. U 5 C . Sect, 793 and 794 the s. a- of f.^♦ n•0^'l• to vô.,he• Zen sc.'s. 5 s,s6 a •e0 by


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

Th,t document confotn, offechng the nof•onot oetenfe of the Un.teel Stotes *offal the meant/1g of the Esptonoge to.us

Tale 19 U S C Secf.o. 793 and 794 the tf,,,,,on of «”.tb nny monnet to nn unnuthet•zed outon wob.b.,ed by Inn

SECRET

h101.1.1r1i3ci0 -Ivntivri x x

. .

3WSVINI3.INIVNI X X

..I.N2IKI.SlirCrY SITETO X

NOLIVOINMOTWOD x X X X X X X SC

X01.1.Y13)1c111311,11 010553001M V.LVG

1011.11403 3101:43A

— ,.. ^ X X X X X X X

X

NOLLV113c10 ITOSN3S X X X X

.X.NaW.T.SfIratr 110SX3S • X X

ONI.I.N10.11105243S x X x

• NO1102139 litItSM39 X

OXIX3VH.I..1.3011V1. X X

Nou.vmwmosTa CIN110130)13YEL mor.usmoov .r.aulivi. X

XOLLINDOD35l 14113ILVei Nollasinwor .r.aouv.L x x x )4

MA

N'S

CR

ITI C

AL

A

PP

LIE

D.

FU

NC

TIO

NS

PR

IMA

RY

E

XP

ER

IME

NT

•

FO

R A

SS

ES

SM

EN

T

OF

MA

N'S

UT

ILIT

Y

1

:-."

1 2 u

E Ft 4 g ?. i

-e

.: is

; g

C, . N .

1 l' 1:1 0 '

. 4.. 0 g, t .5 VI 2 t ." u 2 .,c

g 1 ] ii 5t I 1,

•1

1 t.A. i N 43 . v a 14 .5. o

irt .ri u+ ...; I-2

z

r ..r ; P,

1.1 -4

et;

i r.

8

I; ti . ; 1 111 5

6

0 41

S. g 01 .4

.,,,. 4 1- 1

—':.

7, -i; ...." gE

II, It it 7 7,4 : E C .9. o 04

...: ni

-SEOREf SSM— 50A

6-35

This document contains intotntotian &toiling the notionot aetenste ot the United Stoles within the meaning of the Espionage Law,. Title 18, U.S.C., Section 793 and 79i, the tic...v.51*n of which in any manner to an unauthorised person is prohibtled by low

NOUVRIVAa "IV0I00ÎOISS.Hcl aNVIVOIC/29901a 'Z1

anVcIS .7.13V211131 NI 3DNV191103213ci IVIl3hl30 '11

' SNO1LVA.113SEI0 1V11.1.03c1S QNVII-LLIIIw '01

X

NOTIVOIAYN snowonrolnv •ft

X

.E.LIALLOV 111/7113IllaAVIII.X3 .9

X

3DNIVN3LNEVIN a01/.3.5-NI .'S X X X X

7.1011.331.3a IVNDIS 0IS3NDV1/9013.1.03T3 't X .

SISOUV.I. V3S n ar400110 1003 ONI7O3L1.LDaUla 'E X X

X

SiI.3011V.I. aranotro ao ONISIDVILL 97 NOILISMOOV '1

X

PR

IMA

RY

EX

PE

RIM

EN

T

FO

R A

SSE

SSM

EN

T O

F

MA

N'S

UT

ILIT

Y

PO

TE

NT

IAL

M

ILIT

AR

Y

SP

AC

E M

ISSI

ON

S

it

• A • : 0 g 71 •N 1

g : z

Y ._. :

0 .2 E se, go g. ';' a a 1 jj 'di 0

f,1 1 t: i 8 4 ,... Q

. . • ,.. n o s. •O g b

Q•

A 1 p :

1 1, H• i a; ... 0

Is. ...i 4 Er a

E g o R I; ).. U 0 u r g m 0 1 70. Z., r.„

I iNghi 8 R8ilit a

a. 1..) o al

SSM— 5 OA 6— 36

Tint docsonenr contains informer.on affecting the ept,on. detente or Me United Stores *oho, the meaning col the Etpoonege mans

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

cd

55

U)

0

a)

to

a)

5. Id

5 P4

0

in to

4.) to to

0 tO

3. Id nt ,nt r—s

0 Ta

ble

6-3.


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-

dOconent (onto., '3. ore-se 0. •"c S•rve■ A ̂'he meo,..,,c) at the Em•0-0;e Tole le U S C Sect•o^ 793 c.d '94 the ‘• e0 t-y mo..e• to c- pep n.n. b •ed by In"


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+

Th., document conto.nt .ntolmot.on cP1ect.nti the nat./tot detense nt tee Un.ted Stnte, *ohm the tneun.ng of the ho.onoCie to.%

1.11, 18 U S C Sect.on 193 and ..94 on 01 ,,s.• n ,n y n ne, to nf, ",,


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

Tht, document cantons fOlotmolroo dieting the •,01.ono. ae,ense o, ,he Untted Stenos Attl,n the meon.ng of the hnt...,,g" Ions T :•!, 1,1 S C Secl•On 793 o'd 794. the wht•h to otty mo.-et to o. glt-tto. 't:.


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-


-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

Th., document canto's infotmolion offechno the nohonot °vette of the Untied Suet *ohm the theonmo of the flotonooe ton% Tole IS. U S C . Sethon 793 and 794. the tronsnhwon of .uhtch to ony mantler to on unoulhottzed person •s bred by ton.


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-

Th“ document cartoon, .nformotoOn ofICO ■ ng 0è at'enie n .eie 1-1"..,Ctl Sieve, ...th.n the meaning of the Fip•of,nete

title ,EI 11 S C Section 797 and 791 the lianym.,,ion mann, tonn unnutha• red ae,ion hied by ,r1.


4E0E-

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.


Th•t document cont.", .nlotmnhon offechng the not.OnOt neeme CO the United Stnte, n.th.n lb, nrnn.n,l of the f4hOnone out

Lne 19, U 5 C . Section 793 nn el 794 thy tonnsrn,,,nn of «her h nny manner tonn vnn,,n” ,nn.„, • br


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


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


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

This document contains inlermohan of fect.ng the nOt ■ Onol detente at the United Stales within the meaning of the Espionage Laws. Tale 18. U S C . Section 793 end 79e. the transrnisiion of which in any manner to on unauthoi.zed ',Men is prohibTed by law

NRO APPROVED FOR RELEASE 1 JULY 2015 1 1 -

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


---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.

SS48M-50A

SECRET Th7s document contours ;nfolmotton oltechhg the hohohO, antics. of the Untied Stoles *ohm the rneontm3 07 the Esp.oône tons

T.II• le, U.S C Suchen 793 end 794. the nonstn•smon of wh.ch ,n on, manner to on unoutho,ted Person tun. b••erl hr ,0.

4EGREf- SSM-50A 6-49

t‘i

.

ld P. 5 0

eu

1-4 ba

.5

0

H O ed Id

0

Id

This docomeat <swoon ialotetatten olfechag the nOltattill Ottani* el Is. Unita(' Slates within the nniOnttig of the fiptonag• tows. Title II, U.S.C., Stolen 797 and 794, the iwainntsntin of ..firth ta °ay mann to ea unouthettsed petted is ptobbded by law

t Ic KS Uf z,., 2= t• it 4 k) NM tat 5d2

hi 6141:111119P

11

II- We

et

a

r. r

le i CI

l

.

r, 10--

10

a fig. .,.... 1, i 5 1-1.111-

17. — 0 . 4.1...M a•-■. lair i r. 2 dt:

a .

e s i.i

re G

2 Ft....

at Mt/

.a1.1

00.0

<O..,

30ZWO

1r

lei

Yoe oe u ea = <Y11 ... ■ a...

HN 3.4 00 Oa

0

WAT

ER

AlIC

LA

IIA

MO

L L

ab

ora

tory

Ve

hicle

- D

ual

Press

ure

Com

part

men

t

O a O

OH 0 t

as

tY

0" Mg

a

4

4 .

SECRET

SSM-50A 6-50

This document contains information collecting thy Rattan.% OHM. 01 the United Shoes within The mooning of the Espionage Lows. Title 18, Section 793 and 794, the transmission ol which in any manner to an unauthorixed person is prohibited by low


SECRET

6.4.2 Astronaut Transfer.

Alternative astronaut transfer methods include deployable tunnel,

inflatable tunnel, hatch-to-hatch (Gemini rotation), hole-through-heat shield,

and extra-vehicular (see Figure 6-4). Evaluation criteria include reliability,

crew safety, weight, development time and cost, impact upon Gemini B and

Laboratory Vehicle, and compatibility with system growth including docking

and space maneuvering.

The external inflatable tunnel-is emerging as a particularly 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

This document contains information affecting the notional amense or the United States within the meaning of the Espionage Laws

Title IS, U. S C , Section 793 and 79e. the transmission el which in any manner to On toroulhoirzed perrrn is prahrhited by In.

HATC

H I

N G

EMI N

I H

EA

T S

HIE

LD

INF

LA

TAB

LE TU

NN

EL

•nmuuummuuua

GE

MIN

I RO

TATE

D

EXTR

A V

EHIC

UL

AR

P.

0 0 U

to

td 14 I-I ae

ni

0 4-

it

0 •.e tit


SECRET

SSM— 50A 6-52 SECRET

This document conforms inlorrnolion ollecting the norionot oetense of the United Stoles within the intoning of the Espionope tow, Title IS, U.S.C., Section 793 and 794, the transmission of which in any mann.er to on unoethoiited person is Prohibiled by low


-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



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


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


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

The 18, U S C Section 793 and 794, the oo,rn.f1.0o of which ,n one mann, to a^ r",0-• h..,1 b.

swishers

Line

swishers

Line


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

That document contorni information offechng the nohonof ovense of the Untied Stote‘ *ohm the meaning of the Espfonoge laws Tale 18. U S C . Section 793 and 791. the If ontm.ss ■ on of which In any monny, by 0, unOarhor•ted ',von is pinh.b•'.d by In.


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


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)


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

Fig

ure

6-6

. Gem

ini

B V

eh

icle

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


-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


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


Figure 6-7. Titan ILIC Vehicle


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


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+

Th.s doCum.ni conlo.n, .nfoem.hon o11ec'shg no, ,0n0, e'en ye or she Limped S.ntes the m ,nr .nq 01 she ho•r,êl•In ! ■ 7•••

Tit

an I

IIC

ITL

Fac

ilit

y

00


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


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 oonê, to co unnuthn••cen ne,o^ n•nh•h.•rd hi In.,


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


--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.

■


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.


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.


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


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


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..


-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


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

ecif

icati

on

s


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.


SECTION 7

CIVIL ENGINEERING

•


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


SECTION 8

LOGISTICS


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


SECTION 9

MANPOWER AND ORGANIZATION


THIS SECTION IS BASICALLY ADDRESSED TO PHASE III OPERATIONS. MANPOWER REQUIREMENTS FOR STAFFING THE SPO IS •

OUTLINED IN SECTION 3 - PROGRAM MANAGEMENT


SECTION 10

PERSONNEL TRAINING


CREW TRAINING AS IT PERTAINS TO ASTRONAUT REQUIREMENT FOR FLIGHT TEST DURING

PHASE II - SYSTEM ACQUISITION IS DISCUSSED IN SECTION 6 (ACQUISITION)


INDEX

SECTION 11

FINANCIAL Page


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


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.

In

Cr • -4

O

69-

stl 69.

0,

tT ra

'0 0,

O

57x3

600 R

DT

&E

(T

O B

E D

ET

ER

MIN

ED

DU

RIN

G P

HA

SE I

) I

I I

I I

57x3

306 -

MC

P

*Req

uire

d t

o fu

nd p

rese

nt p

re-p

has

e I

effo

rt t

hru

1st Q

t

Fig

ure

11-

1.

ins

O

0

O

ad

sd

O 01"

rd

OO

O Pik

0

110

0

0

aR

'0 tr)

O

In

tn

0

SS M- 5 0A 11-2 -EGRET

This document contains intoonaloon ollerimg the aill■ 0a01 aerense of the United Slates within the•Ineaning al the Espionage taws. Lilt IIT. U.S.C.. Section 793 and 794. the transmission of which. in any manner to on unauihorieed person is prohibited by law

Cn .... .-4 0) >,

0 C0 P 2 ei q

Con

ting

ency

- $

1. 0

t.) fit to O

a) Z

•

of

0 In 1-4

0 0 0 N O ‘1. I■1 •■■■1

0 0 N

O (11 0 'VI 0 0 0 0 0 t11 N O NON 0 0 0

N •-■ •-■ N -. Id

0

1

... O 0

Ts a) > o

0. 44) >.. 4.) .-4 ..4

511 k .,-. 0 ... 0)

N 'CI4 k ..., 04 al

a) ...; g

43 *--* 0

P. 0

U P. al

#.1' 0 o cz.

C.) j

>.7,10 10 0

U)

in .k ctl F4 N

0 0

'CI 0

-,-. co 4.1 g 0) C G k 4, k

e 7". a.

0 0 6 A 4.114

Ts V. u) g

>... .0 .13 4-, 0 >. 0 u " •0 tia 4°-', tf) 8 "

4) 4-1 VI 1.... 1 E a) V . a. 442 '1 E .2 C14 .0 0 0 a .....

co... (t to --, U 644 0 I

40z tn a ko fl, cl,

'...g.00 0 o 0 , a, 0 0 ...I , ly 0 WW1 ,-, 0 0 0 rd rd 0, 4) co E 5 4-'„ 4,, F

'" to }4. k ...., 0 In -' •la 41 04 , g u U 0 U) 4-4. ...t 0 —9 ›.

73.; [4 o 0 •Ifo

V E v, V.

r .1):titl A A

i'441 ?

0 L) >,..., '10 44

›‘ Id t' 1 u)

03 ..4 .0 0 th 0 • 0 0 0

(-) .-..

0 4) 2 t CO w

y .1) o .2 a) o 8., "0

4-) 0 0 • ...

'5 44 0 A . 0 -0 -...., c0

o ta

1

0 41 - 1 0


This document contains inlormotuon affecting the notionot avenge of the United States within the meaning of the Espionage Lows. Title CE, U.S.C.. Section 793 and 794, the trensmissuan of which in ony manner to on unouthorized person is prohibited by low

SECRET

0 0 0 0 In

c•-;

OR

BIT

ING

VE

HIC

LE

CO

NT

RA

CT

OR

0

SU

PP

OR

TIN

G S

TU

DIE

S &

TE

ST

S

0

AE

RO

SP

ACE

CO

RP

OR

AT

ION

tn

0

0

0

drk

a

H 0 H

MO

L P

has

e I

Fu

ndin

g E

stim

ate

(In

Mil

lio

ns)

SSM- 50A 11-4 SEeREF

This document contains information affecting the national detente at the United Stain within the meaning of the Espionage Lows. Title la, U.S.C., Section 793 and 794. the transmission of which in any manner to on unauthorised anion is prohibited by low


SECTION 12

REQUIREMENTS

. . NOT APPLICABLE AT THIS TIME

DATA PERTINENT TO THIS SECTION WILL BE GENERATED DURING PHASE I

. -

SSM- 50A


INDEX

SECTION 13

AUTHORIZATION

Page

FIELD LEVEL MANAGEMENT OF THE MOLS PROGRAM 13-1

CHARTER FOR THE DEPUTY COMMANDER, SPACE SYSTEMS DIVISION FOR MANNED SYSTEMS 13-2

MANNED SPACE PROGRAM 13-3

TWX FROM AFSC TO SSD - 10 MARCH 1964 13-5

AFSC LTR (MSF-.1), 8 MAY 1964, TO DCMS, SSD 13-8

IfeREF SSM-50A 13-i/ii

Th.* document contoms ,nlotenconon 014(1,9 the not.onot oeteme at the Umted States nah.n the meomog of the ftwonoge Ions

7,11. 18. U S C Socha. 793 end 794. the ”c^s..“.0. Ot ..h.(11 monnm to an aolaoho,qed pvtom .1 o,o ■• b,ed by


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

This document cantons •nsotmonon offering the -a•.annI deie^Se S•ntes •nc •nconing Of the Espionage 1o•.

T.tte ta. U S C Sector 793 and 194 the ',my..., of .n,•.h • man', to an uroolho,ted pe“on .t ntoh,h,,ed by low


-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-

Tho document cameo's mfottneo.on elteettng the not,onol ante,. co the Un.ted States ...oho, the mcon.ng of the hp•onoge Ions

Tole 18. U S C Sierran 793 and 791 the tocnton,s,ot• of ,. ,,h n^, mono., 10 on unnvibo,i,r1 pe,.cv• .% wbb.b.'"d by


SECRET c ma- IDENTIAL)


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


(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

--SEGRET-


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


SECRET COPY

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-


--SEGRET- COPY

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

Thq document conto:ns ,n10•mat.on cuect ng 'he nnt,onni deie^se n •ne .e0 S,ntes meot...10 01 the Esn•onnge

T.tte 18. U S C Sec,o^ 797 c-d '94 the t•ansrn ..-on 01 0^ r)h t,d b., H.


REPLY TO ATTN OF: MSF-1

SECRET -teerrrpreferrphtfty


United States Air Force Andrews Air Force Base

Washington 25, D. C.

COPY

8 May 1964

SUBJECT: Approval of USAF FY-1964 RDT&E Manned Orbiting Laboratory (MOL)

TO: SSD (DCMS) Air Force Unit Post Office Los Angeles, California

1. References:

a. MOL Preliminary Technical Development Plan (PTDP), dated April 1964.

b. D&F 64-11c-84 dated 13 April 1964, with attached Form 111.

c. Memorandum, DDR&E (Dr. Brown) to SecAF, same subject, dated 29 April 1964, copy attached. (Attachment #1)

d. Memorandum SAFRD (Dr. Flax) to Vice Chief of Staff, USAF, same subject, dated 4 May 1964, copy attached. (Attachment #2)

e. Letter AFRDC to AFSC, same subject, dated 6 May 1964, copy attached. (Attachment #3)

2. You are hereby directed to proceed with the pre-Phase I study program as outlined in the April 1964 PTDP, subject to the conditions listed below. PA and BA authorization is being forwarded under separate cover.

a. Contract negotiation for the following studies will be deferred pending specific authorization by this headquarters to proceed:

(1) APOLLO '

(2) GEMINI (One-Man)

(3) Pointing and tracking scope definition

(CONFIDENTIAL)

SSM- 50A 13-8 --SEGREf

This document canto..., ,nfotmotton offechng tee ...co ono, oe'ente o• Un•ted Stntet .•th.n gnu meon.ng of the Ftin•onoge

I■ sle 18. U S C Seet.on 797 ond 79.1 the Ire,• ■■•ti. a. a; •••••• ■■ a 1^, mon,- ta e- ne,,n- ,to^ t, b, 1,„


(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.

4EGRET- SSM-50A 13-9/10

if, document COnt0,1s ,n1011.1•01, 011e0 ng me ..ot•Cm01 oe, e"se a the U,,ed 51otes ...thin the mcomng of the Eso,onoge tons

Tole 18 U S C Seo.on 793 c^1 '94 m r. 0” •11 •n n,i ma^êt 90 711 1,1,1 by 1n.


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


SECTION 15

SECURITY


DATA PERTINENT TO THIS SECTION WILL BE GENERATED DURING PHASE I

SSM- 50A


INDEX

SECTION 17 Page


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

Th.e document con1001$ .010,0,01.00 ollechog the ootmool °most 01 the Untied Stoles *Am the oteonong of the eswonoge tows

Tale 18. U.S C . Section 793 (sod 794. the Itchfm•st•Oh 01 .eh,ch ,h any toonnot to on u.outhotqed peso" ,t otoh.b.led by low


SECRET

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

Th.% document conto.ns .nlotmot.on ollechno thy not•Onot Oetense or the United Stotts the meon,ng of the ho.onooe Ions

Tale 18. U S C . Sethon 793 and 794 the ooettn,..on of ...h.01 ,n Ony Mall" el to on unouthot•zed nets°, otnh b.ted by Ion


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


SECRET

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

--SfeREI- SSM-50A 17-3

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.


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


SECRET

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

NRO APPROVED FOR RELEASE 1JULY2015

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

docvmeo. 'fie•.o,onn, of ..e Unoed .he *enn,ng of the

Command

Experiments


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


SECRET

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

SSM-50A 18-2

1h., doo.orn,, .n1Of nrO.nn nfert1.ng ritif 1.1•,•,tit !OW., of 11, •••

1 S 711 ,nn ol mnr^, I

HF

TH

RU

VH

F,

LA

RG

EL

Y A

VA

ILA

BL

E

UH

F,

PU

LS

ED

, NO

N-M

ILIT

AR

Y F

RI E

NDL

Y VE

SS

EL

S v, ±"

-± a v, Zr, >.-

ix 1 a c4

U) o_ ;I = E •- . 3 Q v, w c, - o w w > - re' I- a 0 o x z v, 0

VI CD O w 1 0 U IL)

—I i.i.. = hd 1 Ce *CZ il. ti- LL. --CV LD Z ..

...a IL CO ■ a. 0 U) .1. w a -I 't I.:

LI 4( i,1 m :-.1j- 4" -cr.. •— I— C,.I i.". I IX 0

G ILI V) ili 0 z Iti U — a. ce = 1 ..<

•ct Zsi b U •-• a i-

-4

Ix

Ix

(.) I- 00

>

LI

u_ Ui

uJ

0 U

V U

*NI co

0

SSM-50A 18-3

Tale 9 0 $ C Seo.o, 993 Q. '91 .• • •, , DC


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

SECRET SSM -50A 18-4

Fig

ure

18-3. C

ov

er a

ge

Obta

ine

d w

ith S

imp

le N

on

-R

ota

ting R

ad

ar

An

tenna a

s S

ho

wn

in

Fig

ure

18

-2

.40-140 MILES

210 MILES

140 MILES ow

210 MILES

4

S ( c• '•■■ • •

CERT SSM-50A 18-5


IERET-

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.

SSM -50A 18 -6

N 44 0 0

00 U U Z X W

0 0 CE CO CO Z X

,-- cc rz o 0 ce

a LLI

CC U I I

I—

LU 3Z Z ).

_ice win < 0 0

OC p p

I I 17: > ce a.

AD

VA

NC

E DE

TE

CT

ION

- 1

MIN

., 2

50

MI.

CLA

SSIF

ICA

TIO

N -

F

I LM

S F

OR

0 ce

0

0

I - 0 Z ,,u,1 :L- i—

<2 -O W U

-1uj

vs u- ~ (11 4.7

0 ce 0U 4

w 0 a. U

TA

RG

ET

S,

SAT

UR

AT

ION

BY

-

Fig

ure

18

-4. O

ce

an S

urv

eil

lan

ce

-Conc

ept

W 4 ,./, I- I v, 0 5g ow w W ce WZ CL ..::( 0 us tr 4 LA, 1 a

w -Iccooce I-Lu ozo

t4 m o

1— IL 0 i— ti <2 tp 0 <2 tes 0 0 ce 0 c4 Z US I.— g Ow /''' = 7,-,wv)00 F. 0 U - t- 0 1-- tn 0 ce

1.1-14: 8 ujz 7; z cil 4 0 11- 0 .4 "I 0 ILI 0 ce =7 v) p-4 CI Z 4( Pc t3" rz: tu 0 W 0 ii. I U a. ce ui

E2 u I 0 i.: S? ca 1-- —3 Lt. I Z z a u.. z 0 a U L71 6 ra- 44 o 1 0

1__ u. ..t „, ..: g ,„/- 0- u_ „J W , ,-, 0 ...! -,.-• 0 _Luca %.1 400:-.

0 CC 0.. 4 F- 4 0

T.o. ,8 u 5 ( 5e, -c ,

--SEGRET- SSM- 50A 18-7


SECRET

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


Fig

ure

18-5

, O

cean

Sur

veil

lanc

e

SSM-50A 18-9

Tlus document contconi inlonwollon ollecwng the nerd•a ovente or It Untied 5101,$ the meaning of the figt.roge ta.t • TM. 18. U 5 C . Section 793 and 794. the uontm,uo• of wnnh .n ..y ,..■•■•,, to on unoutho..ted person .t ploh.boed by low

1/4 / /

// 1/ /1 / / / / / /

• •

U z

kJ • CU Z > < Ce OC ...a VI 0 /— 17.1 W Q. > Z Z

< gya //11 GC DC ° O Z ce

< Z uj w • s— 0

•

MA

N G

IVE

S...

0

•

CH

OIC

E OF

BE

ST

SE

NS

OR

•

SELE

CT

IVE

AC

TIO

N

•

OP

TIM

IZA

TIO

N

•

CO

NC

ENT

RA

TE

D

•

RE

LIA

BIL

ITY

•

FIL

TE

R N

OIS

E R

EJE

CT

ION

.

•

AC

CU

RA

CY

•

RA

PID

RES

PON

SE


-AGE-

SSM-50A 18-10 IEEE-

This document contains inloonaoon allecting the nahomcso amense at int United Stoles within the meaning 01 the Espionage tows. Title 111, U.S.C., Section 793 and /N. the trensrmstion of which in any manner to an un01,1110,1sed person is proh ■bated by low


SECRET


This document comma inlotenotion affecting the notional °C.C.S! Or the Untied Shan within the meaning a the Espionage tows

Title IS. U.S.C. Section 793 and 791. the Ponsoustion of which in any manner to an unathorired. person .% proh.biled by low


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.

SSM -5 OA 18-12 SEM-

Its document confo.nt mloirnohon ollect ■ no the nobonal detente a..ne Un.ted Stntet "Oho, one oteon,n9 01 the Elp.onoge to*.

Tide IS, u.s.c . Section 793 and 794 the oon■ rn.ss.on 01 .n ony rnanne■ to on unauthof.ted pe“on n ofoh.boed by lo.

TO

INS

PE

CT

20 PO

RT

S

CA

TA

LO

GU

E A

ND

CO

UN

T

•

SH

IPS

IN

PO

RT

•

SH

IPS

IN

LA

NE

S T

O T

HE

SE

M IN

0 a.

OP

TIC

AL

...

M

AN

GIV

ES

...

HI

RE

S H

AR

BO

RS

AN

D A

PP

RO

AC

HE

S,

Z

•

et O a. e- 4 4 la

0 Z W SU b. u Z O eg u ot ); 0 o- u >

vb

RA

DA

R,

TV

-IR

-LO

RES

HA

RB

OR

S. A

ND

AP

PR

OA

CH

ES

, O

PE

N L

AN

ES

, IC

E

CL

OS

UR

ES

, IF

F,

EL

INT

, B

EA

CO

NS

, A

CC

UR

AT

E D

AT

A

CL

AS

SIF

ICA

TIO

N,

AP

PR

OA

CH

ES


This document commits intotmor.on altering the not,onal °ciente of Ion Untied States will. the meaning of the Espionage Lows.

Title IS. U.S.C.. Stolen 793 and 794, the trcnunre,on at whtch in any manner to an unctuthowed person h prolubtted by law

ce INT

EG

RA

TIO

N

SECRET

-SEGRET-

g gc4141 (NA of 43 oi a: c; c; in. VI- 4441- 10). 03

43 0 4" I—'

I-- in ,wee N C) to to to

0 to go .-- ot '— c) c• I-- .

toU , c; c; ci c; c; c:'

to 40 AO 40 1.9- 41)- 41, 43 %CO

ce O

O

...)

.4t 111 W U 1— -4t

0 1-: .4 EL > W 0 1--

SSM -50A 18-14

This document contains information *fleeting the notional defense of the United Stoles within the meaning of the Espmnoge Title IB, U.S.C.. Section 793 and 794. the Iromm.,,.on of which in any manner to on onoutharired person is•prohibiled by be,

CI 4,

NR

L N

MC

NA

DC

NP

IC- A

PE

L

BU

WE

PS

NR

L

U G

AP

L I

NS

NR

L


SECRET

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

This document contains information affecting the nolional defense of the United States *Ohm one meaning of the Escuonage La«,

Tote 18. U S C Section 793 and 794. the tionsmist.on of which in any TOMMe1 to an unouthoiqed pemon •s pinh•hoed by In.


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

SSM -5 0A 18-16 -SEORET-

This document confomt mlotrn0000 ollecong the oc00000l deleo%* of the Unwed Stole, odh., toe meorong of the Etreonooe Lae.

Tole IS. U. S.0 . Section 793 and 791. the ttontrn.toon of 0,hith in one rnonne. to on unoetho..ted 1.0h.b.ed by too


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

IEEE- SSM-50A 18-17

This document contours snlormahon ottechng the notional defense of the Owed Stales *alias one enecon.ng of the Esp.onoge too..

Tole 18. U.S C . Section 793 and 79e. the Itonsmas.on of nhah as any manner to on unoothohted person is ystah.baed by tan

0 ix) z 0 0- v)

0 U

NR

L N

AD

C

.4t 0

U) ∎o

C%1 41)

Fig

ure

18

-11.

Co

mm

uni

cat

ion

s V

LF

, EL

F, H

F

GL

OBA

L C

OM

MU

NIC

AT

ION

S

AN

TE

NNA

IMP

ED

AN

CE

N U

4.1

tu

U

ce

U 0

a. 0 a. T

UN

ES

AD

JUS

TS

OP

ER

AT

ES

CO

NT

RO

LS

AT

TIT

UD

E

OP

TIM

IZE

S

IhNEMINIMMIIIM.Sy.■=1O0 144=11•1■IyalneMNIIIMO

0

a.

z


This document contains information affecting the notional defense of the United States within the meaning of the Espionage taw,. Title 19. U.S.0 . Section 793 and 794. the transmission of which in any manner to an unouthorised person is prohibited by law


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.

W

at1 O

NO

T U

NIQ

UEL

Y N

AV

Y, M

UC

H AF

AC

TIV

ITY

.

MA

INT

AIN

CO

NT

AC

T, D

EM

ON

STR

ATE

INT

ER

ES

T.

Fig

ure

18

-12.

SSM- 50A 18-20 -SECRET

This document contains information affecting the national defense at the Untied States within the meaning of the Espionage tows. Tide le, U.S.C.. Section 793 and 794, the Itcnsmission of which M nay roomer to on unauthorised person is prohibited by Ipne

SE

CU

RIT

Y -

SE

PA

RA

TE

AP

PR

OA

CH

ES

MA

N G

IVES

SE

LE

CT

IVIT

Y, N

OIS

E R

EJ E

CT

ION

, E

NH

AN

CE

D A

CC

UR

AC

Y,

RE

LIA

BIL

ITY

, C

OR

RE

LA

TIO

N

PA

SS A

GE

OV

ER

FO

RE

IGN

TE

RR

ITO

RY

7.)

z

z

NA

DC

, NM

C, N

RL

, NO

L(W

O)

CO

ST

INC

LU

DE

D

Fig

ure

18-

13.

Eli

nt

J CO O

O.

-SEM- SSM-50A 18-21

This document caldrons inlarrnation alt«ting the notional defense of the United Stain «ohm In, meaning of the Espionage tow, T111. IE. U.S.0 Sertion 793 and 791, the transmission al ohortt in any manner to an unclothed:eel poison is prohibited by low


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

in • C•4

40) 44

1-• 4,1

tr) .43

O

cs 4. A 4.1

A

O vt z0

EXPE

RIM

ENT

E2 ...i 0 —1 0

• rx ce z z z

Z 14 o w P P z ...1 CO ce CF3 E2 1- 0 ;A ix z 1-z w - o

0 z 0, us ci u o tn z ui >0 :W .55 0 > z ig o W

. 4 0›• W 1-* Z — 0 ix Z • _ i- 0 LU X 2 AC on J›* 113

•

ZS "5: u w

-I cg -I cg Lg et CL 0 0

Cg 0., CC 0 44 V 11. us .44 x

W -4 O0 >... Ce ,-; ...I > 0 u 4 ce 0 w a. z x

(

PRO

BLE

M FA

CTO

RS

-

O

Figure

18-14.

Bioastronau Uce

SECRET SSM-50A 18-23

This document COMeillt information alfectinp the national delentt of the United States within the meaning of the EsPionat). Low.. Title 18, U.S.C., Section 793 and 794, the hananission of which in nay manner to an unauthorized person is ptahtbaed by low


SECRET

18.7 GENERAL SCIENCE

The Navy has much capability in the area of General Science, and

consequently the Panel had many experiments to review. Those ultimately

selected are thought to have potential military value. Considered first were

experiments that are related to the MOL vehicle and deal with space and

plasma physics. For example, the proposal of the NRL to study plasma

surrounding the MOL vehicle by scatter of RF energy is included. Similarly

the proposal to study by the use of probe techniques the density and 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-

'Ms document contemn inforrnohon offechno the notional defense of the United Stoles ...ohm me meaning of the Esp,onoge to.. Title 18. U.S.0 Section 793 and 794, the iranon.won of which in any manner to on unouthoozed pet., pr0h,b.ted by le.

65 C

OS

T-T

OT

AL

MO

L V

EH

ICL

E)

MO

L O

RIE

NT

ED

- S

PA

CE

& P

LA

SMA

PH

YSI

CS

EL

EC

TR

ON

D&

T

FA

R U

V O

RT

HIC

ON

AIR

GL

OW

HO

RIZ

ON

PH

OT

OG

RA

PH

Y

SECRET

LC)

tR

flw 40,

Csl

tc,

-J U

44

In

O 40)

...I -I ce ce ce zz Z Z


This document contains info/moues, allectmg the nobespf defense of the United Slates ad hot ale meaning of Ike Espionage Low,. Title 18. U S C , Section 793 and 79e. the trans...won of which in any manner to an unauthorized pesson it prohibited by law

Fig

ure

18-1

5. G

ener

al S

c ien

ce

c — > — c

—

OC -ct

O —J

AIR

GL

OW

SP

EC

TR

OS

CO

PY

PH

OTO

GEO

LO

GY

EA

RT

H

PH

OT

O S

OL

AR

PL

AN

ET

S

CO

SM

IC R

AD

IAT

I ON

SECRET

l'‘. C■••

-J -1 -J CG Z IZ Z

tI) 1— 1— 0 0 Z Z

Fig

ure

18-

16. G

ener

a l. S

c ien

ce

41■1 •••••

SSM-50A 18-26 SECRET

This document contains informarion affecting the notional defense of the United Slates within the meaning of the Espionage low.. Tills 18, U.S.0 Section 793 and 7.4, he transmission of which in any manner to on unouthoriyed person is prohibited by low


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


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.


SECRET INDEX (Cont'd)

SECTION 20


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


-SEM-

SECTION 20


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


SECRET

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


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.


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


(weight, power, space) which otherwise would be necessary in an automatic

link establishment procedure when using narrow-beams.


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.


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.


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.


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


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,



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.


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.


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..


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.



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.


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


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.


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


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



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


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


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


-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.


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


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.


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.,


20.13 VAPOR VAPOR COMPRESSION DISTILLATION WATER PURIFICATION SYSTEM - EXPERIMENT S-13.

20.13.1 Objective.

Verify and evaluate operation of the system.


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.


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»



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.


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


-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.


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


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.


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.



The tests are needed to provide basic data for the design and develop-

ment of a high resolution radar system.


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.


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.


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



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.


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»


-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.


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.


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*


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.


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

Documents

1111111111111111 - National Reconnaissance Office · 1111111111111111" MICROFILMED BY TIM APRIL 1964 Status as of 30 JUNE 1964 r;i:,":',,j1 C.] 3‘..-ae-A-994 • SPECIAL HANDLING