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EXEMPTED FROM DECLASSIFICATION IAW E.O. 12958

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•

air force

spaes systoms

d•ollopn•

Program

AIR FORCE BALLISTIC MISSILE DIVISION, HE QUARTERS,

AIR RESEARCH AND DE VELOPMENT COMMAND

WDZR-180
AIR FORCE SPACE SYSTEMS

DEVELOPMENT PROGRAM

OVOO'C "C! 000

4/FSti

t Title: SPADE '031

ION 

elY3A Z1 IV :S-VA

030VciDNAJOG

20 October 1959

AIR FORCE BALLISTIC MISSILE DIVISION

HEADQUARTERS

AIR RESEARCH AND DEVELOPMENT COMMAND

This 

•

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FOREWORD

There exists an urgent need to define and initiate a coordinated

Air Force Space Systems Program. The following pages outline in

broad terms a space program based on established Air. Force General

Operational Requirements plus other requirements which appear to be

necessary to complete and integrate the over- pr gram. This

planning guide, which we call SPADE for "Sp e D velopment", has

the following objectives:

To delineate Air Force space requirements;

To define the systems under development or being

considered to meet these requirements; and

3. To promote the recognition and advancement of the

technology needed to achieve the systems.

This initial report, which is very preliminary, is designed to serve

as the framework for continuing study. It is to be modified periodically

as the need arises.

This document is intended as a tool to assist in coordinating and

ordering the Air Force space program definition and development,

and is for the use of using commands in defining operational requirements, and centers and laboratories in analyzing development requirements. With the assistance of interested commands and agencies, the

study ultimately should define and provide an. analysis of each of the

required systems in sufficient detail to show the inter-relationship

of the various technical requirements. The results of this analysis

will indicate critical areas in which technological advancements are

required to permit timely development of systems to accomplish the

space-age missions.

OSMOND J. RITLAND

Major General, USAF

Commander

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WDZR - 180

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TABLE OF CONTENTS

SECTION 

I. INTRODUCTION

PAGE

I-1

Objectives I-1

Evolution of a Weapons System I-2

C. Purpose of the SPADE Plan I-3

IL MILITARY SPACE SYSTEMS REQUIREMENTS 11-1

A. Offense Missions 11-4

Strategic Missile 11-4

Bombardment Satellite 11-6

Tactical Weapon System 11-7

Deception and Jamming 11-7

B. Defense Missions 11-8

Missile Attack Alarm 11-8

Ballistic Missile Defense 11-9

3. Satellite Defense II-10

C. Surveillance Missions II-12

1. Visual and/or IR Satellite

Z. Ferret 

Mapping 

Weapon Test Surveillance

Communications Mission II-14

Supporting Missions II-15

Environmental Observing and Forecasting . . . II-16

Space Navigation Aid II-17

Logistic Support of Space Operations 11-17

Rescue II-18

5. Satellite Tracking and Cataloguing II-19

III. SYSTEMS: ACTIVE AND PLANNED III-1

A. Offense Systems III-1

1. THOR III-1

Z. ATLAS III-1

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TABLE OF CONTENTS

SECTION PAGE

TITAN III-2

MINUTEMAN III-2

5. ALBM III-3

B. Defense Systems III-3

MIDAS III- 3

SAINT I/1-3

C. Surveillance Systems 111-4

1. SAMOS III-4

D. Communications Systems 111-4

STEER III-4

SAC POLAR 111-5

TACKLE/DECREE III-5

National Survival Communications System (FLAG) 111-6

5. COURIER 111-6

E. Support 111-7

TIROS 111-7

TRANSIT III-7

3. SPACE TRACK III-7

IV. SYSTEMS UNDER STUDY AND PROVISIONAL SYSTEMS IV-1

A. Offense Systems IV-1

Advanced Strategic Missile IV-1

Bombardment Satellite IV-1

Tactical Weapon System IV-1

Deception and Jamming IV-2

B. Defense Systems IV-2

Advanced Attack Alarm IV-2

Ballistic Missile Defense IV-2

C. SurveillanCe Systems IV-3

1. High Resolution System ' IV-3

2, Weapon Test Surveillance IV-4

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TABLE OF CONTENTS

SECTION PAGE

Communications Systems • • IV-4

1. Global Communications Satellite IV-4

Support IV-4

Advanced Navigation IV-4

Re-supply IV-4

Rescue IV-4

Transportation-Logistics IV-5

5. Space Environmental Observing and Forecasting

System IV- 5

V. SPACE STUDIES V-1

Strategic Systems V-1

Defense Systems V-3

Reconnaissance Systems V-4

Supporting Studies V-4

VI. TEST SUPPORT SYSTEMS VI-1

Dyna-Soar VI-1

WS-609A VI-1

Outer-Space Weapons. Test Vehicle VI-2

Re-entry Test Vehicle VI-2

Hypersonic Lifting Re-entry VI-2

High-Altitude Sounding Rockets VI-3

VII. ANALYSIS OF THE PROGRAM AND ITS SYSTEMS . . VII- 1

Space Program Schedule, and System Priorities • . . VII-1

Operational Characteristics and System Specifications VII-3

VIII. SUBSYSTEM CORRELATION AND DEVELOPMENT . . . . VIII-1

Operational Concept and System Characteristics . . . VIII-2

State -of-the -Art , VIII-2

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TABLE OF CONTENTS

SECTION PAGE

A Recommended Program 

Future Analysis VIII-3

IX. CONCLUSIONS IX-1

APPENDIX A DEFINITIONS OF TERMS A-1

APPENDIX B REFERENCES B -1

APPENDIX C BOOSTER DEVELOPMENT REQUIREMENTS C-1

APPENDIX D REPRESENTATIVE RESEARCH AND

DEVELOPMENT AREAS D-1

Development Programs D-1

Research Projects D-18

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I. Introduction
AN AIR FORCE SPACE SYSTEMS DEVELOPMENT PROGRAM

I. INTRODUCTION

The competition among nations in introducing new military weapon

systems has become very critical with the development of the nuclear

warhead and thereafter the long-range ballistic missile as a carrier

for this warhead. Today, as the ballistic missile systems are becoming

operational, our nation faces new and intense competition in the exploitation

of weapons systems utilizing space vehicles and satellites. Our greatest

threat is from an opposing nation which recognizes the military value of

space operations, is capable of extreme control and acceleration of

development effort, and will probably not, in actuality, conform to any

international agreements for "peaceful use only" of space. With this in

mind, our nation must lose no time in defining and initiating a coordinated

military space systems program.

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B. Evolution of a Weapons System

System operational requirements normally are initiated by the

using command or by a senior plans and requirements Air Staff agency

on the basis of an :analysis of a mission, and broad studies of potential

systems capabilities. The relative priorities of the operational requirements are established by consideration of the national strategy or concept

of operation, the state-of-the-art in the particular field, and the anticipated

systems costs for development, maintenance and operation.

The operational requirements are converted to system development

requirements through operational concept studies and preliminary design

analysis. This. effort involves an; analysis and study of similar existing and

planned systems and a study of the pertinent state-of-the-art. The results

are normally preliminary development or design specifications.

The preliminary design specifications are converted into a system

design by detailed design studies involving extensive selectivity studies and

tests of major components for the system. If the system is unique in that

it is a considerable extension of operational techniques and technical

capabilities, a feasibility demonstration may be required preceding the

design studies.

The system design is converted to a production design by further

study, and production and tests of development prototypes. Subsequent to,

final design the system is produced and appropriate operational suitability

and reliability teats are conducted. Modifications are made as necessary

and the system is put into operational use.

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This sequence of events for a major weapon system usually covers a

period of from 5-10 years. Most weapon systems involve a major

extension of the state-of-the-art for development of one or more of the

major components. This is particularly true in military space systems

development. U the systems currently under development and anticipated

can be defined and analyzed in sufficient detail to show the interrelationships of the various technical requirements, it should be

possible to foresee some of the critical technological advancements

required to permit timely development of the systems.

C. Purpose of the SPADE Plan 

The purpose of the SPADE Plan is to guide space system planning

by assembling and discussing space system requirements, analyzing the

systems under development or being considered to meet the requirements,

and correlating the major component requirements in principal areas to

permit relatively economical and timely development. Timely identification and promotion of the state-of-the-art improvement in critics.).

areas is a major long-range goal of this plan.

Section II, which follows, contains a listing and descriptions of

Air Force space systems requirements. These requirements, for the

most part, are based on established General. Operational Requirements

issued by Headquarters USAF. An effort has been made to indicate a

general priority for some requirements.

Systems which may fill certain of these requirements are discussed in Sections III and IV. In Section III are included systems which

are in operation, in development, or in the advanced planning stage.

These systems have been analyzed in some detail and can be defined

reasonably well. Section IV describes systems which are under study

or which are being considered but are in a provisional category pending

study and analysis. Characteristics and design details for the latter

systems are either very tentative or unknown.

Section V lists long-range systems studies designed, to investigate

concepts and areas from which future systems designs may be drawn.

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These studies play a key part in the evolution of a weapon.system, .icir

their results suggest new requirements and point the way toward systems

which may some day fulfill advanced requirements.

Section VI contains descriptions of major test support systems

or programs which are required or may be directly applicable to the

space weapon research and development program.

Section. VII contains a discussion of systems analysis and sub -

system correlation. Included are a consolidated schedule of all of the

space systems programs and a summary of system specifications or

characteristics for these systems which have progressed to the specification

stage. These charts, which are very preliminary at this time, serve to

illustrate the usefulness of the SPADE Plan and the effort to be associated

with the Plan. As additional space systems are analyzed and the schedule

and characteristics are defined more clearly, the data in the charts will

become more apparent.

Section VIII describes an analysis of Air. Force Space Booster

requirements. The correlation between individual system booster requirements and .a proposed development program for this major subsystem

area is explained. The intent to analyze other areas of major component.

technological development and state-of-the-art advancement is stated:.

• Certain conclusions are drawn in Section IX:

Appendix "A" contains selected definitions, and Appendix "B"

contains a number of references applicable to the system discussed in the

SPADE Plan. The complete booster analysis paper is included as. Appendix

"C!', and a list of representative development and research areas which

are or could support military space systems development is contained

in Appendix "D".

WDZIt. -180

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II. Military Space Systems Requirements
WDZR-180

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II. MILITARY SPACE SYSTEMS REQUIREMENTS

The following section surveys the various military operations associated

with aerospace as an operating medium. It expresses these operations as

Military Space System Requirements. These requirements, together with

an indication of the status of programs to satisfy them, are summarized

in Table II-1 and described in some detail in the following pages. Although

an attempt is made to .examine the entire range of possible requirements,

it is well for the reader to keep in mind the systems of clearly-recognized,

early military interest, to-wit:

Strategic communications

Reconnaissance

Ballistic missiles

Missile and satellite defense

These areas are of early, definite interest, because it is now evident

that powerful, even decisive, military advantages are to be gained therein.

We are, of course, continuing to analyze other areas of space weapon

possibilities for systems of considerable potential.

Of the currently-recognized space system requirements, both communications and reconnaissance offer clear, concrete military advantages.

In each of these areas, systems can be developed now which will contribute

powerfully to our national military posture.

It has not yet been possible to focus quite so clearly upon the basic

area of strategic offensive-defensive forces, due to the depth of the

un-plumbed technology involved. The strategic potential of the ICBM,

which traverses space for 90 per cent of its trajectory, is understood

very well. However, the full value of space as an operating medium

within which to blunt or frustrate an enemy ICBM attack is not yet

completely understood.

Potentially, though, it is possible to recognize the overwhelming

military advantage accruing to the nation which first couples a useful

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ICBM defense with its decisive offensive Strength. That nation will, if

it desires to use it, possess the capability to shape a stable world order.

In the more likely possibility that both the opposing nations achieve

approximate defensive parity, then a tremendous need for further offensive

improvements can be anticipated. Thus, in the classic military pattern,

the alternative move and counter-move of developing military capabilities

may be expected.

Consider, for example, the possibilities generated by the development

of an orbiting defensive system which intercepts and destroys ballistic

missiles during the boost or powered-flight phase. Such an achievement

immediately initiates an effort to provide powerful satellite interceptor

systems, to attack the defenses; orbiting bombardment systems, which

can be launched innocuously from the ground; or advanced missiles which

can evade or similarly frustrate the defenders during powered flight.

Thus evolves the ever-changing spectrum of military requirements and

defense expenditures.

The pages which follow discuss individually the military space system

requirements which presently can be foreseen. Some of the requirements

may appear Buck Rogerish to those not in frequent contact with space

system activity. This is not the case. Many of these systems are

feasible within the 1960-65 period, and others which now appear quite

extreme can be available in the 1965-75 era if selected and emphasized

development effort is initiated .at a reasonably early date. In this

connection, it should be remembered that the complexity and cost of

current weapon systems have restricted the U. S. to a few selected

systems. The military leaders now know the number and kind of weapons

to be provided in the foreseeable future for defense of the U. S. As

time progresses, costly incremental improvement of current systems

could be accomplished. However, it appears to be almost mandatory

that we take a quantum jump into space, and develop selected active

defense as well as deterrent space weapon systems.

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A. Offense Missions .

The projection of our national ICBM deterrent force capabilities

into the realm of space should be accomplished by a logical transition

from its current configuration into improved ICBM weapon system

capabilities coupled possibly with a low altitude orbiting bombardment

system. A companion satellite reconnaissance and intelligence system

will also be necessary to support our national defense and counter

offense efforts. Extension of our initial low altitude system: to a

manned satellite might be foreseen during the 1965-1975 period.

1. Strategic Missile 

GOB, 180 establishes the requirement for an advanced or

improved ICBM weapon system whose initial range and payload will

provide the means to increase our operational flexibility and expand

our counter-offensive capabilities.

Technical evaluation of the current ICBM weapon systems

and the state-of-the-art of missile and associated technology indicate

it is possible to improve these systems to the degree where a 9, 000

nautical mile, greater than 5-megaton payload capability could be

realized at an early date. Study should be continued in this area, and

a restatement of R. and D product improvement and AEC development

should be obtained and evaluated.

In discussing advanced ICBM operational systems, consideration must be given to the effectiveness of a large number of

relatively low yield missiles with adequate range, great accuracy,

low vulnerability, and logistic support simplicity, versus a smaller

nitmber. of high yield missiles that have "sulaquate range. and yield but

are inherently more expensive due to logistic and support problems.

Since "time" and "cost" appear to be two of our more critical commodities,

the early availability, increased reliability, and cost effectiveness of

the lower yield weapons may be our best near -term objective. The

long-term goal could continue to be the high yield warhead or comparable

WDZR-180

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kill capability, with.the objective of achieving breakthroughs in the

state-of-the-art that would provide the higher yield in a light warhead

with the associated accuracy, logistic simplicity, and low vulnerability.

Specific requirements for the advanced/improved ICBM

missile state a range of 8, 500 miles, with a payload capability for

nuclear . warheads in the 20-50 megaton range and CEP of one nautical

mile. This capability will permit the using command to locate its

launch sites anywhere in the ZI USA, and provides strike capabilities

for coverage of USSR (and its Asiatic Communist-dominated countries)

industrial and metropolitan target areas. A counter-offense capability

against enemy ICBM launch installations located as far south as the.

Malayan Penninsula may also be realized. The capability represents

an advance in the ground-based U. S. ICBM deterrent force, supplementing the strategic manned bomber force. However, the need to

increase the deterrent threat and provide improved operational techniques,

particularly in the counter defense and penetration areas, through the

medium of air-launched and satellite-launched orbiting vehicles,

establishes the additional requirement for development of a strategic

bombardment satellite.

Air-launched and submarine-launched ballistic missiles

provide certain operational advantages over both the ground-launched

missile and the cruise-type stand-off weapon. In the first instance,

they offer extreme launch-site dispersion, mobility, and flexibility.

In the second instance, the stand-off weapon acquires the performance

to overcome enemy defenses.

(Reference: THOR, Section III-A-1

ATLAS, Section III-A-2

TITAN, Section LU-A-3

MINUTEMAN, Section III-A-4

ALBM, Section III-A-5

Advanced Strategic Missile, Section IV-A-1)

(See sections indicated for system descriptions)

WDZR - 180

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2. Bombardment Satellite 

The feasibility and practicality of a bombardment satellite

must be carefully studied. The moat obvious concept for a bombardment satellite is a nuclear warhead in orbit about the Earth so that

the plane of its orbit passes over or near all potential targets. Thus,

a polar orbit would bring all areas of the world under orbit within a

twelve -hour period. - The warhead-carrying satellite could .thus be

launched at leisure in orbit around the Earth, with the capability of

being triggered out of orbit when one so desires. The selection of

orbits for a bombardment satellite must be carefully considered so

that all potential targets come under coverage of the satellite force

and that the destruction is such as to optimize the desired target

concentration and minimize the vulnerability of the satellite to a

satellite defense system. For use of a satellite as a bombardment

vehicle, the warhead must descend essentially intact through the

Earth's atmosphere to the target. Since the warhead descends on a

ballistic trajectory to the target when the orbital velocity is reduced,

this point of reduced velocity must be carefully predetermined in order

to provide the required range accuracy. Detailed control of the velocity

of ejection from orbit will be required to achieve acceptable accuracies.

In addition, some control in azimuth will be required since only a rare

coincidence would place an intended target in the orbital plane of the

satellite. To achieve azimuth control, a component of velocity must

be provided normal to the plane of the orbit.

The development of a strategic bombardment satellite

is an established requirement (GOR 174). The research and development, and subsequent operational employment in space of an armed

nuclear satellite, by the U. S. must consider the political and world-wide

ramifications in the event of an unforeseen incident which may cause

impact on friendly. or enemy territory. Therefore, absolute control

must exist in all satellites carrying conventional and nuclear armament,

and specific sea areas must be designated for impact and recovery of

WDZR-180

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erratic and malfunctioning satellites.. Positive means of cataloguing

and identifying U. S. satellites must also exist for control of this

system.

General development parameters for the strategic

bombardment satellite are as follows: The mission will be to supplement the national strategic deterrent force. It must have the characteristics for providing continuous alert, low vulnerability, long life

(reliability) and low cost. Control and cataloguing functions, should

be within the capabilities of current or proposed military systems,

and/or modifications or additions to existing equipment. System and

subsystem developments should permit injection and ejection of multiple

counter defense and penetration aid devices. Outside skin should be

non-reflective radar absorbent type. Simplicity, protection against

neutralization, and positive warhead arming and disarming control

features are other development objectives. (Reference: Bombardment

Satellite, Section IV-A-2. )

Tactical Weapon System 

A vigorous study of the application of large ballistic

missiles to tactical military operation is required to establish the

feasibility and potential availability of systems capable of performing

missions of the tactical air command, when it is no longer feasible to

use conventional aircraft. Operational objectives such as the attack

of mobile military targets, battlefield reconnaissance, and the delivery

of massive destruction against concentrated field forces, should be

evaluated for solution by the use of ballistic missiles or space vehicles.

The need for this type of weapon, or the utility of ballistic missiles

for this application, will be determined by further study. (Reference:

Tactical Weapon System, Section IV-A-3. )

Deception and Jamming 

In studies which have been conducted to define satellite

defense systems, consideration was given to the possibility that the

WDZR-180

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enemy might use decoys and janiming. Therefore, it appears that there

is a requirement for a system capable of this type of action for use with

U. S. satellites. In addition, consideration. should be given to the possibility of jamming enemy communications from a satellite as an offensive

measure. (Reference: Deception and Jamming, Section IV-A-4.)

B. Defense Missions 

It is axiomatic that enemy capability to deliver decisive military

force against us through any operating medium requires our immediate

attention toward means of denying him this advantage. Space is such

an operating medium, and the ballistic missile has become an instrument

of decisive military force. Development of a missile defense system

thus becomes our initial space defensive concern. Our ability to

effectively employ such. a defense will, in turn, call upon counteringenuity by the enemy, leading through more versatile missiles to

offensive satellite schemes, with an eventual probability of maimed

offensive systems. Our defensive development timetable must keep

up with the enemy pace and should, of course, be designed to get out

in front. By overtaking the enemy here, so as to couple our offensive

might with an effective defense, the U. S. can again establish a.favorable

balance of international power, making possible the achievement of a

stable peace. The discussions that follow concern these defensive

requirements.

1. Missile Attack,Alarm 

A requirement for a system capable of surveillance for

early warning of ballistic missile attack was established by GOR. BO.

The infrared reconnaissance subsystem (Alert System),

which is to provide instantaneous alarm of attack by ICBM's, is required

on a most urgent basis with an initial capability at the very earliest

date. The operational objective is to detect the launching of ICBM's,

immediately alert the active missile defense system to such launchings,

then track the ICBM's to positively determine that the attack is aimed

This tiocwarest CONIMINI Interresdiee Mediae the notlettel defense et Na United Stews within the mewing et the Espionage laws, This

19, U.S.C.. Sallee 793 and 794, the tronsmissiee or revelotiee of which In goy mama' is an veentiterised penes is prohibited by law.
at the U. S. or its possessions. Long-range plans envision the incorporation of the infrared detection and tracking capability into a manned

space defense vehicle system. (Reference: MIDAS, Section III-B-1,

and Advanced Attack Alarm, Section IV-B-1.)

2. Ballistic Missile Defense 

The Soviet Union has, or will have shortly, an ICBM

capability that is a threat to our nation. Satellites launched by the

Russians indicate they have rocket engines and guidance systems

which are sufficiently developed to allow them to direct an ICBM

attack against the U. S. There is some question as to the actual

number of Russian ICBM's that can be launched immediately; however,

they must be assumed to have a production capability at least equal

to our own. During 1960 the Russians may be expected to achieve the

capability of launching a decisive ICBM attack.

A requirement for a ballistic missile defense system

was established by GOR 156.

The objective of a ballistic missile or an anti-missile

defense system is to prevent the detonation of the nose cone warhead

in. the intended target area. The three phases of an ICBM trajectory

(acceleration, coasting, and deceleration) define three general classes

of anti-missile defense schemes. These are commonly referred to

as the "during boost", "mid-course", and "re-entry" approaches.

Regardless of the approach selected, an anti-missile

system must provide for the detection and tracking of the nose cone

vehicle until it can be diverted or destroyed by interceptor weapons.

The maximum flight time is of the order of thirty-five minutes so

that an effective defensive system must have a very quick reaction

time.

Analysis of the three types of anti-missiles indicates that

the ICBM is most vulnerable during the boost phase of its trajectory

when detection and tracking of the nose cone vehicle are relatively

simple since the attached booster is optically visible for hundreds of

This lioceseet contehu infermertias effecting the entiowel defense of the United Sates within the enenting of the Espionage Lows. Thee

itection 793 and 714, the trenunissioo or neveintioo of which In ony at Goner to on vestethosined gess* Is onshibiled * law.
WDZR - 180

11-10

miles. During this period infrared seeker missiles with non-nuclear

warheads could divert the warhead by destroying booster guidance

and/or thrust. This approach cannot be pursued initially due to our

present inability to operate from satellite bases with the required

degree of reliability and economy of effort.

It appears that early anti-missile systems, if mandatory,

will have to be developed around ground-based interceptors which.

destroy the warhead during the mid-course or re-entry portions of

its trajectory. Considerable study will be required before adoption

of a ground-based system. Powerful radar equipment will be required

to illuminate the ICBM-warhead for detection and tracking. Methods

must be found to discriminate between this warhead and the swarms

of decoys which are expected. Large interceptor missiles equipped

with nuclear warheads will probably be required to insure destruction

of the very rugged ICBM warhead. This, in turn, will place severe

altitude restrictions on the interceptor to prevent thermal or blast

damage to friendly territory. Such restrictions make the mid-course

attack more attractive than the re-entry approach.

Another prime requirement of an anti-missile defense

system is a warning element to alert our strategic offensive forces

as well as the civil and military defense agencies. For maximum

warning, surveillance satellites over enemy launch sites are required.

Passive IR sensors will be used to detect ICBM boosters as they rise

above the atmosphere. Interim warning systems, however, will use

ground-based radar or airborne IR. equipment deployed as closely as.

possible to the potential missile launching areas.

3. Satellite Defense 

The objective of a satellite defense system is to catalogue

and inspect unidentified satellites and to disable those orbiting satellites

found undesirable by the U. S. The system should have peacetime as

well as wartime potentialities. This indicates a kill mechanism which

is more surreptitious (and less disruptive to radio communications, etc. )

This &moons contains Itiformeatioo offottio4 the Wien& dolmas of the Wiled Stoles wind. the ootooloo of tho Isisishollo Laws. niki

19, U.S.C.. Section M and 794, M. troottoluloa or mole** of which la soy moose to on intootirattood mom is otsfilliffad W law.
than nuclear destruction of the satellite. GOR 170 establishes the

requirement for a satellite defense system.

The ability to catalogue and disable enemy satellites

becomes urgently required at such time as Russia could, through

satellites, significantly threaten our national security. Present

Russian satellites threaten only our prestige and complacency. Nearimmediate Russian capabilities include using satellites for reconnaissance, surveillance, and counter-measures (electronic and saturation)

against our ICBM early-warning and defensive systems. This latter

Russian capability indicates an urgent requirement for a cataloguing

capability. By 1963-1965, satellites might be used to track (infrared)

our missiles so as to actively facilitate the Russian ICBM defense

system. We should counter these with an active ability to disable

enemy satellites. This ability would also be applicable against Soviet

bombardment satellites, which might exist by 1965 if our missile

defenses made the Russians employ such weapons, and against.Russian

satellite-launched anti-ICBM missiles possible by. 1965-1970.

The anti-satellite system will include elements which

locate, identify, inspect, and neutralize enemy satellites. Initial

interceptors will probably be unmanned ground-launched systems,

with follow-on manned identification and neutralizing forces stationed

in orbit, as .the art permits. Threatening satellites may be in orbits

varying from 100 to several thousand miles. Sizes may vary from 5

to 50 feet, and weights from 100 to 25,000 pounds. Large numbers

of decoys, combined with numerous "spoofing" opportunities, will

make target identification and discrimination one of the severest

problems facing an effective, practiCable system. For good political

and technical reasons, killing with nuclear weapons may be unwise.

Careful inspection and kill assessment require the proximity feature

of a rendezvous type vehicle as an alternative to nuclear destruction

of the hostile satellite. Initial defensive force requirements will tend

to be reduced by systems permitting several orbital passes by the

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WDZR - 180

11-12

--C-OfnpfatriAt

•

hostile satellite. Ground control systems must include or tie in with

"space track" or similar satellite acquisition, tracking and cataloguing

systems.

The problem of distinguishing satellite threats from decoys

arises, of course, when the threats materialize. As indicated above,

1963-1965 could bring a grave threat in the form of satellite components

of an effective Russian ICBM defense. The initial U. S. satellite

defense system must cope with this problem. By 1965-1970, the

increasing Russian capability (with recoverable booster) to economically

infest space with scientific probes, multi-ton satellites, jammers,

debris, bombs, ICBM detectors and interceptors, and multitudes of

decoys will require an advanced interceptor/inspection system to cope

with the problem. (Reference: SAINT, Section III-B-2. )

C. Surveillance Missions 

Advanced surveillance systems are required to provide aerial

world-wide reconnaissance, to provide strategic intelligence data, and

to support international inspection systems. The systems devised will

be companions to the advanced offensive and defensive space systems

being considered and consequently must be compatible with these

systems.

GOR 80 establishes a requirement for Reconnaissance Satellite

Weapon Systems to provide the necessary reconnaissance capability.

The satellites will be launched from stations within the U. S. into Earth

orbits and will be monitored initially from ground stations in the

Western Hemisphere.. They will be employed in numbers required

to acquire or confiim data concerning actions, locations, capabilities,

and vulnerability of manned and unmanned strike forces. Separate

or combined configurations of the photographic, electronic, infrared

or other sensors will be employed to provide the desired coverage.

Each satellite will require the capability of in-flight processing of

data collected and transmission to ground stations or to other satellites

This document aoteles isterloottee elfectIne the netlewoi Wallow of the United Steles Wain lb. ...mite of the belenowt lows, Title

141, U.S.C.. Bodies 793 01111 794, the tressmissiee or revelation of which In soy onweer to ow Imootherlool pease Is onthIbboi by low.
electronically and/or by physical transfer techniques (including ire-entry

and recovery).. Man will undoubtedly have a place in this system,

ultimately, to provide on-the-spot decisions and equipment control

and repair.

The Reconnaissance Satellite subsystems are:

Visual and/or IR. Satellite 

The Visual and/or IR Reconnaissance Subsystem is to

provide source material for the production of intelligence information,

target materials, air navigation and topographic maps, and weather

data primarily in the form of cloud cover. This operation involves

aerial photography, on-board processing of film, and return of data

to ground stations. -Development will involve progression from lesser

to greater resolution as the state-of-the-art in satellite reconnaissance

improves. Initial general coverage with 100 foot resolution and spot

coverage with 20-foot resolution with twelve months life will provide

some capability. In future systems, general coverage with 10-foot

resolution and spot coverage with 1-foot resolution with a three to

five year life is desired. (References: SAMOS, Section III-C-1,

and High Resolution. System, Section IV-C-1. )

Ferrer

The Electronic Reconnaissance (Ferret) Subsystem is

to intercept electromagnetic emissions from potential enemies, to

store the information until a time suitable for retransmission, then

to transfer the intercepted information in a secure maneuver to a

central intelligence station. Intercept coverage in the band of •

frequencies between 30 MCS and 40 KMC's is required. A direction.

finding capability to an accuracy of five miles is desired but its

incorporation should not delay the availability of the initial version

of the Ferret subsystem. It may be desirable to incorporate the

Ferret Subsystem with the Visual Reconnaissance subsystem.

(Reference: SAMOS, Section III-C-1. )

•

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Mapping 

The Mapping and Charting Subsystem is to provide cartographic agencies with photographic and radar mapping service of the

land mass areas of the world, including those areas which are not

presently accessible whether for political or other reasons. The end

product of this subsystem must result in maps and charts (or substitutes)

of geodetic accuracy. Photography produced by this subsystem must

be of high quality with sufficient data recorded on the negative to

facilitate reduction to usable form by cartographic agencies. Highresolution radar should provide data not available by photographic

means. The required quality of the data and the quantity of information

involved would appear to govern the necessity of a means of recovering

the film itself in this subsystem. (Reference: SAMOS, Section III-C-1.)

Weapon Test Surveillance 

Possible international agreements on disarmament create

a need for surveillance of space to detect nuclear explosions. Even

in the absence of such agreements there is an intelligence requirement

for such data. (Reference: Weapons Test Surveillance, Section IV-C-2.)

D. Communications Mission 

The communications satellite provides a relay station for

long-distance radio communications. Initial applications are ground/

ground and ground/air;" later applications will require links between

the various elements of complex military space forces. GOR 178

describes the requirement for a communications relay satellite system

for ground/ground and ground/air communication.

Satellite communications relay for military operations control

promises relative invulnerability from certain critical enemy threats

against other communications means. A particularly pressing need,

that for over-the-pole communication with SAC bomber forces, can

be achieved using 5, 600-mile polar satellites. An extremely hard

80

II-14

Mb document CINdflilla kaiMOOffill. OWNS* the national defense lie United bates within the meaning of the Espiennee Lows, Title

IS. U.S.C., Seale, 793 end 794, the trenenisstee or revelatios al which In any etaanor to en eneetherined pima Is prohibited by law.
world-wide (exclusive of polar regions) system can be achieved using

22, 700-nautical mile "synchronous" satellites. The first space-to-

.

space communications applications could well accompany missilewarning (and later, missile-tracking) satellite systems. Each major

weapon system advance after that will require increased space

communication capabilities.

Initial communications satellites must include sensitive,

jam-resistant receivers and transmitters as well as precision attitude

control for antenna positioning. Urgent developments include longlife power sources, such as big arrays of solar cells, and large

payloads to permit high volumes of data transmission. Military

space communications will have to devote great emphasis to light,

long-lived, reliable and secure systems. The communications

advantages of space long line-of-sight ranges and freedom of atmospheric and ionospheric attenuation between suitably positioned space

vehicles, must be fully exploited. As payloads and secondary power

sources permit, satellite-borne jamming equipment will offer advantages

in space-era ECM.

(Reference: STEER, Section III-D-1

TACKLE/DECREE, Section III-D-2

SAC Polar Satellite, Section III-D-3

FLAG, Section Ill-D-4

COURIER, Section III-D-5

Global Communication Satellite, Section

IV-D-1)

E. Supporting Missions 

There are numerous categories of space activity which we must

master to acquire the primary mission capabilities discussed before.

Some of these "supporting" space missions will be initially employed

in support of non-space operations. In general, though, these early

WDZ -180

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MPIP-CONFIDENTIAL

accomplishments will provide the know-how required later for vital

support of operational apace systems. The following paragraphs discuss

several of these supporting systems which will ultimately provide

important elements of the technology permitting military operations

in space.

I. Environmental Observing and Forecasting 

As military operations are extended beyond the Earth's

atmosphere the need will grow for an integrated system to coordinate

the observing and forecasting of environmental conditions which the

space missions will encounter. GOR. 176 establishes a requirement

for such a system to extend and supplement the present weather observing

and forecasting system.

The primary function of the system is that of furnishing

environment reporting and forecasting support to space vehicles operating

above 200, 000 feet. A secondary function is observation of weather in

support of a Weather Observing and Forecasting System. This system

would operate much the same as the existing weather system insofar as

processing and analyzing the environmental data and distributing forecasts and information to interested commands.

The environmental data would be procured from special

meteorological satellites or from xnulti-purpose satellites and other

space craft. Development of space environment observation and

reporting procedures and equipment must be coordinated with the

development of other space systems, in particular the reconnaissance

satellites, in order that the environmental observations may be procured

from such satellites and from other space craft as an associated function

of such vehicle operations where practicable. Development of this

system should parallel the development of the family of space weapons

to provide the timely incorporation of environmental reporting components

and procedures into the design of each system where feasible. (Reference:

TIROS, Section III-E-1.)

80

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,

2 Space Navigation Aid 

Navigation aids placed in orbit promise certain aids to

position determination on or near the Earth's surface. Ultimately,

"beacons" in terrestrial and cislunar space will facilitate the positioning

or navigating of military satellites and space vehicles. This requirement is not specifically called out in an established GOR, since the

need can be expected to arise primarily as an outgrowth of specific

mission-system requirements.

The basic time requisite is to acquire sufficient experience,

through early experimental efforts, in order to meet requirements

which will be defined as future military space systems, and should

receive careful design consideration. Defensive systems involving

large numbers of pitrolling satellites might well utilize positional

reference satellites to maintain necessary control of far-flung forces.

Later operations involving maneuverable defensive patrols, possibly

extending to cislunar ranges, may call on further navigational assistance,

perhaps from "fixed" 24-hour or libration-point satellites.

Various doppler and hyperbolic schemes may find applications. Objectives will be to supplement stellar references with

favorably located "beacons" nearer the operational arena. It is most

likely that navigation schemes will depend upon requirements of the

missions of the over-all weapon systems. (Reference: TRANSIT,

Section III-E-3, and Advanced Navigation, Section IV-E-1. )

3. Logistic Support of Space Operations. (recoverable

boosters, maintenance and re-supply, space transportation)

The deployment and use of integrated offensive and

defensive space systems, ultimately requiring scores and possibly

hundreds of cooperating, functioning satellites, will pose challenging

logistic problems. To operate effectively in space, we must solve

these problems. We must economically get these large numbers of

satellites into orbit and then replace (or augment) them as they wear

This doctened coatains inforatatisme effecting tie nodded dolonso of the United Steles within do wttenine of die Espionedt laws, Title

U.S.C.„ iodise 797 and 794. the transasissiee or moieties of which in any monad le an weattheilsed person is prohibited by law.
out. Ultimately, we must be able to repair or re-supply the basic

satellite vehicles. Finally, when man begins functioning in space, we

will have problems in personnel transportation. Existing GOR's

(80, 170, 174) which may be met by orbital systems involving large

numbers of satellites establish the urgency of space logistic considerations.

• Large scale systems first become feasible and required

with the ICBM tracking and detection component of the missile defense

system. Later, orbital anti-satellite patrols and offensive systems

will be in operation. Still later, manned satellite inspection systems

and other manned systems will require full-scale logistic support.

Recovirable boosters offer great economies in the deployment and replenishment of many satellite military systems. These

vehicles must be available eventually in the million-pound and greater

thrust class; they must be maneuverable enough (and manned, if

necessary) to assure recovery essentially intact for re-use.

With more complex systems aloft, economies may eventually

become feasible if malfunctioning satellites are repaired instead of

replaced. Re-fueling of powered satellites which must periodically

reposition themselves or must indulge in maneuvers is another such

application. Requirements for rendezvous are similar to those raised

by the satellite inspection (defensive systems) requirements.

Man can obviously participate very profitably in these

logistic functions, and it may be here (in a non-combat environment)

that he first fulfills a military role in space. If so, this will bring

on requirements for personnel transportation into and out of space,

and for considerations of manned space station assembly and operation.

(Reference: Re-supply, Section IV-E-2, and Transport Logistics,

Section IV-E-4. )

4. Rescue

A requirement exists for a satellite system capable of

locating persons in distress on the Earth's surface. Reception of

WD -180

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it, U.S.C., SotMoo 793 and 794. Ih. tsonswissisio or wirolalloo of which in soy wanner Man voossfitswizod porno is osohibitod by low.
distress signals 'and re-transmission with location data to a ground station

can be envisioned as an early system capability. (Reference: Rescue,

Section IV-E-3.)

5. Satellite Tracking and Cataloguing 

The objective of the satellite tracking and cataloguing system

is to detect, track, and compute orbital data for all satellite a, both

cooperating and non-cooperating. Specifically, a requirement for this

system exists in support of the satellite defense mission. In addition,

data provided by this system would be useful for intelligence purposes.

An operational space track system should have a capability

of detecting dark (non-radiating) satellites passing over the continental

U. S. at altitudes to 1,000 nautical miles. An increase of altitude

detection capability to as much as 25,000 nautical miles is a desirable

objective. The system should be capable of tracking uncooperative

satellites with accuracy sufficient to provide orbital information needed

by a satellite inspection system.

In. addition to acquisition and tracking radars and other

radio detection devices, the system must have adequate communications

facilities for data transmission to a control center. The control center

facilities would include computation, maintenance of a space situation

display (showing locations of all satellites), and provision for threat

alarm.

Detection equipment for dark satellites at altitudes to 1, 000

nautical miles could.be available in the 1961-1962 period. Considerable

improvement in the state-of-the-art will be necessary for a significant

increase of this altitude capability. (Reference: Space Track System,

Section III-E-4. )

This decumbent cattalos informetioa bin/odes the metiomei defense .f the United States within the weenie, of the Eseionome Lows, Title

111, U.S.C., Section 1.3 and 714, the tromweissiee or oevelotiest of whirl in ono mama to es vensItherited memo is prohibited by tow.

•
III. Systems: Active and Planned
III. SYSTEMS: ACTIVE AND PLANNED

In this section are described systems which are in operation, in

development, or planned.

A. Offense Systems

THOR

THOMRSM-75) is a single-stage liquid-fueled IRBM, mounted

in soft surface launch complexes, which is now completing its development period.

It can be launched within fifteen minutes of fire order.

Initial THOR squadrons are now operational under the RAF in Great

Britain.

Mission Strategic bombardment

Length 64 feet 10 inches

Diameter 8 feet

Weight 110, 000 pounds

Propulsion Single engine, 150, 000 pounds

thrust

Guidance Inertial, 2 n. mi. CEP

Re-entry vehicle Copper heat-sink

Warhead 1600 pounds

Operational range 300 to 1500 n. mi. .

ATLAS

ATLAS (SM-65) is a stage-and-a-half liquid-fueled ICBM

now approaching opekational status. It can be launched within fifteen

minutes of fire order. Initial squadrons will be mounted in soft surface

launch complexes; later squadrons will be hard-based in underground

silos. The ATLAS will be stationed within the continental United. States.

Mission Strategic bombardment

Length 82 feet 6 inches

Diameter 10 feet

Weight 266, 100 pounds

Propulsion Booster engine: two chambers,

total 300, 000 pounds thrust

Sustainer: one 60, 000 pound

chamber

Guidance Radio guidance, 2 n. mi. CEP

(inertial guidance later) "

Copper heat-sink (ablative later)

WDZR- 180

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Re-entry vehicle
WDZR- 180

III-2

Warhead 1600 pounds

Operational Range 2000 to 5500 rt. mi. (7000 later)

TITAN 

TITAN ISM-68) is a two-stage liquid-fueled ICBM now undergoing flight tests. It will be launched within fifteen minutes of fire order.

Squadrons will be deployed in underground silos capable of withstanding

100 .psi overpressure. Operational capability is scheduled for mid-1961.

Mission. Strategic bombardment

Length 97 feet

Diameter 10 feet

Weight 221, 000 pounds

Propulsion First stage: two chambers, total

300, 000 pounds thrust. Second

stage: one chamber, 80, 000 pounds

altitude thrust

Guidance Radio (inertial later)

Re-entry vehicle Ablative, 4100 pounds

Operational range Over 5500 n. mi.

MINUTEMAN

MINUTEMAN (SM-80) is a three-stage solid-fueled ICBM

now under development. It will be substantially smaller than ATLAS or

TITAN. It can be launched in seconds after receiving fire order. Squadrons

will be dispersed principally in hard underground installations, with about

25 percent of the force scheduled for mobile (railroad) deployment to

further confound enemy counter-action. Operational capability is scheduled

for early 1963.

Mission Quick-reaction strategic

bombardment

Length • 56 feet

Diameter 5-1/2 feet

Weight 65, 400 pounds

Propulsion First stage: 166, 000 pounds thrust

Second stage: 47, 000 pounds thrust

Third stage: 15, 500 pounds thrust

Guidance Inertial (1 n. mi. CEP)

Re-entry Vehicle Ablative 550 to 790 pounds

Maximum Range 5500 to 6500 miles

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WDZ R - 180

111-3

5. ALBM

WS 138 A is now under development. It will provide an airlaunched ballistic missile for use in strategic bombardment.

Mission

Length

Weight

Propulsion

Range

Strategic bombardment

About 50 feet

About 5.0, 000 pounds

Two-stage solid propellant

Approximately 1000 miles

B. Defense Systems 

MIDAS

MIDAS is a planned satellite system which will provide, via

infra-red detection of the missiles' boost flight, instantaneous earlywarning of hostile ICBM attack. This technique . supplements BMEWS with

a different technology for greater assurance of success, as well as extending the available warning margin to approximately 25 minutes. It will

become operational in 1961.

Mi s sion

Payload

Booster

Satellite Weight

Orbit

Missile attack alarm

Infra-red missile detection and

instantaneous signalling

Atlas -Agena

2500 pounds

2000 n. mi. , circular, nearpolar

SAINT

SAINT • is a planned program, now being considered by Headquarters USAF, for the development of a satellite defense system. The

operational system, WHITE SAINT, would be an unmanned, ground-launched

system to intercept, inspect, and optionally negate satellites passing over

the United States at. up to 1000 miles orbital altitude. It would be operational

by early 1964. GREEN. SAINT would be an earlier (1962-1964) feasibility

demonstration of the ground-launched co-orbital interception technique.

SILVER SAINT is an investigation of a light-weight, air-launched co-planar

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interceptor while BLUE SAINT is a study of a later manned satellite interceptor and inspector. The following table refers to the initial operational

system, WHITE SAINT:

Mission

Payload

Booster

Satellite Weight

Orbit

Intercept, inspect, and

optionally negate unwanted

satellites

Detection, communications,

maneuvering and negating.

capabilities

Atlas-Centaur (Thor-Hydra

for GREEN SAINT)

3500 pounds (1400 pounds.

GREEN SAINT)

100-1000 miles, maneuverable

(300 mile - GREEN SAINT)

Surveillance System 

1. • SAMOS

SAMOS is a satellite system, now approaching the flight test

phase, which will provide operational military reconnaissance of the Soviet

land mass. Types of coverage will include photographic, both for intelligence

and for mapping, and electromagnetic ferret. The system will be operational

in 1961.

Mission Military reconnaissance

Payload Sensing, storage, and command

readout (alternative recoverable

system)

Booster Atlas -Agena

Satellite Weight 2800 pounds

Orbit 260 n.rai., near-polar circular

. Communication. Sy. 

1. STEER

STEER is an .R and D program intended to demonstrate the

feasibility of a polar satellite active communications relay for groundto-air use. The development system will not include the orbit-keeping

subsystem required for a sustained, operational system. The flight test

program is scheduled for 1960-1961.

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WDZR- 180

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Mission

Payload

R and D for SAC Polar groundair communications

Active, instantaneous cornmuiiicalions repeater

(WADC system)

Booster Atlas-Agena. las in SAMOS)

Satellite Weight 400 pounds

Orbital Altitude 5600 n. mi.

SAC POLAR

The SAC POLAR satellite is a planned operational follow-on

to STEER designed to provide secure combat-useful communications relay

from ground control points to airborne SAC units in the polar regions. As

such, it will provide one means of circumventing enemy and natural obstructions in maintaining positive control of the bomber fleet. The system will

include eight satellites in polar orbits, with the necessary station-keeping

capability to correct and maintain the orbital position. Operational date

is early 1963.

Mission SAC polar ground-air communications

Payload Active, instantaneous communications repeater (WADC system)

Booster Atlas -Agena (as in SAMOS)

Satellite Weight 400 pounds (minimum)

Orbital 5600 n. mi., polar

TACKLE/DECREE 

TACKLE and DECREE are Army-managed development programs intended to demonstrate the boost, injection, and control of a

communications payload in a synchronous 24-hour orbit, and to integrate

the payload and satellite with the launch system. Neither program is

designed to satisfy Air Force operational needs; the Army Signal. Corps

is the communications agency involved. TACKLE will employ ATLAS-AGENA

vehicles, launched from Vandenberg AFB starting 1961, with preliminary

and test versions of the DECREE payload. DECREE will use the NASA

ATLAS-CENTAUR vehicle, launched from AFMTC starting in 1962.
Mission Develop synchronous communications satellite

Payload Active, instantaneous repeater

(Army Signal Corps. system)

Booster Atlas-Agena (TACKLE)-AtlasCentaur (DECREE)

Satellite Weight 400 pounds (TACKLE)

1300 pounds (DECREE)

Orbit 5600-10,000 mile elliptical

polar (TACKLE)

22,400 mile equatorial (DECREE)

National Survival Communications System (FLAG) 

FLAG is a planned operational system, now under consideration

by Hq USAF, designed to provide secure combat-useful communications

relay between ground control points. It is primarily to ensure the control

of our SAC retaliatory forces under conditions of enemy attack, sabotage,

or nuclear blackout. The system will employ three large satellites in

synchronous orbits providing redundant coverage of the North American

continent and adequate coverage of the non-polar free world. The ground

system will, employ fixed (non-tracking) hard antennas. Operational date•

is late 1963.

Mission • SAC non-polar ground-ground

hard facility communications

Payload Multi-channel, jam-resistant

active, instantaneous

communications repeater

(WADC system)

Booster LargelSATURN class)

Satellite Weight 3-4000 pounds

Orbit 22,400 n. mi. equatorial

(dog-leg injection)

5. COURIER

COURIER is an Army system providing an active, delayed

communications repeater for certain of their military needs. The Air

Force is scheduled to provide booster support in 1960 and 1961.

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WDZR- 180

III-7

Mission Army communications

Payload Active, delayed and direct

repeater

Boosters. Thor-Able Star (1960) and

Atlas-Agena (1961)

Satellite Weight 500 pounds

Orbit Circular, 500 and 1200 n. mi.

E. Support

TIROS

TIROS is a NASA "one-of-a-kind" experimental satellite for

meteorological data gathering. The Army Signal Corps is providing the

satellite while the Air Force will provide and launch the booster.

Mission NASA meteorolOgical experiment

Payload Army Signal Corps

Booster Thor-Able

Satellite Weight 270 pounds

Orbit 380 n. mi. circular

TRANSIT

TRANSIT is a Navy experimental system for navigational support

of the Polaris submarines. The Air Force will provide the required booster.

Mission Navy navigation

Payload Doppler system

Boosters THOR-ABLE STAR

Satellite Weight 215-270 pounds

Orbit 400 n. mi. circular

3. SPACE TRACK System

An interim National Space Surveillance Control Center has

been established and is now operating at L. G. Hanscomb Field at Bedford,

Massachusetts, under Project. SPACE TRACK, Cambridge Research.Center.

The interim system receives tracking and observation data from various

sources, and maintains a catalog of the space population. By mid-1960,

the capacity of the system could be 50 objects. Specifications for the

accuracy of prediction under present plans are as follows: period -

O. 5 seconds; inclinations-0. 1 degrees; time of ascending node - 1.0 second,

at epoch.

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Inputs to the system will be from radars such as that at

Trinidad, Millstone, and Canadian Millstone. The ARPA east-west

fence should be providing useful data by early 1960. Ultimately, a combination of one or more fences, together with appropriately located tracking

radars, will be required.

Output information will be provided to military operational

commands such as NORAD and SAC, for use in assessing the threat of

attack. In addition, it will be furnished directly to the SAINT satellite

intercept/inspection system and other operational systems. The data

will also be transmitted to intelligence agencies.

Finally, there is considerable scientific value in the data

collected for universities, industry, and government laboratories.

WDZR- 180

III-8

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-IV. Systems Under Study and

Provisional Systems
WDZR- 180

IV-1

IV. SYSTEMS UNDER STUDY AND PROVISIONAL SYSTEMS

This section discusses systems which have not been established as

feasible but which are under study or may be considered for future study

toward fulfilling a system requirement.

A. Offensive: System

1. Advanced Strategic Missile

Studies for advanced strategic weapon systems are now

underway. There are several directions in which advancing technology

may turn out to promise real operational advantages over MINUTEMAN

and its contemporaries. It appears that study-type effort will suffice "

for several years. Areas under technological and operational investigation include:

Increases in gross payload, perhaps to 100, 000 pounds

Provision of highway mobility

Improvement of accuracy

Hardening of ground and flight systems

(v) Command control after launch for recall or attack changes

2. Bombardment Satellite

Various current studies indicate the technological feasibility

of a bombardment satellite. The question of its ultimate operational

usefulness remains to be established, and merits continuing attention.

This is particularly advisable in light of the disadvantages of prior

Soviet recognition of the direct or psychological utility of this weapon.

3. Tactical Weapon Systems

An Air Force study is desirable in this area.

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WDZR- 180

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4. Deception and Jamming 

Physical deception, simulation, and jamming are properly

considered as adjuncts to almost any military space system under study.

However, the area of specific systems intended primarily to frustrate

enemy tracking, defensive or communications systems merits separate

study starting right now.

B. Defensive Systems 

Advanced Attack Alarm

The MIDAS program includes studies of possible follow-on

infra-red systems incorporating missile tracking and trajectory prediction.

Ballistic Missile Defense

Preliminary studies have been made of various ways to

defend against attacks from intercontinental ballistic missiles. The

defense of localized critical target areas is presently under development

in the NIKE ZEUS program sponsored by the Army. The main deficiencies

of this system appear to be its very high cost for defending a very limited

number of targets, and its inability to selectively attack incoming warheads

when accompanied by a large number of easily provided decoys. Although

intensive efforts are underway to improve the target discrimination capabiIities.of warning and tracking equipment, this discrimination function is

thought to be limited to the period when the re-entry bodies are within the

Earth's atmosphere. Air Force studies have concentrated on an area type

of defense which involves attacking the ballistic missile during the period

when it is being propelled into its ballistic trajectory or during the midcourse of this flight when it is out of the Earth's atmosphere. In the

first case, the use of decoys is not believed to be feasible, and in the

second case, there is some indication that the mid-course environment

and time available might be utilized to provide a discrimination between

warheads and decoys.

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WDZR-180

IV-3

A number of surveillance satellites are under consideration

for a system:to attack ballistic missiles during the boost period. An

infrared detection system similar to MIDAS would be used to detect the

launching of a ballistic missile. Satellite-borne interceptor rockets

would be launched to destroy the ballistic missile before its propulsion

period was completed. An operational concept and rough sizing of satellite

and interceptor vehicles has been made for this weapon system, but many

technical problems require extensive research and development and actual

space experiments before the true feasibility of this program can be

definitelrestablished.

The alternate system for destroying an intercontinental

ballistic missile attack is to attack the ICBM's during the mid-course

of the ballistic trajectory. This system is entirely dependent upon the

availability of equipment capable of discriminating between war-heads

and decays traveling at very high velocities in a spherical volume of

approximately 100 miles in diameter. Although the maximum range

of 50 miles and the outer space environment are thought to be significant

aids in this problem, the solution to this discrimination problem remains

to be demonstrated in theory and practical application. Approximately

two years of intensive study and research and development experiments

will be required before the feasibility and detailed development plan for

an AICBM system can be precisely defined.

C. Surveillance System 

1. High Resolution System 

SAMOS follow-ons to achieve greater resolution, greater

data rates, and more sophisticated selectivity are receiving continuing

study, both within the SAMOS program and elsewhere.

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Z. Weapon Test Surveillance 

This system consists of earth and sun satellites equipped with

instruments to detect nuclear explosions at high altitude. In addition,

certain ground instrumentation systems are also used. The requirement

for this system originates from the 1959 Geneva Nuclear Disarmament

Conference.

Communications Systems

1. Global Communication Satellite 

This system is an operational follow-on of the FLAG system,

(National-Survival Communications). Its operational date is estimated to

be 1966. Studies to determine the capabilities possible in that time period

should be initiated in 1961 or later.

Support 

Advanced Navigation

The earliest version of this system should be used as a

navigation aid for persons on the Earth's surface, and might be an outgrowth of the TRANSIT 1 B Program. Eventually, systems of this type

might be used as a navigation aid for space vehicles.

Re-Supply 

Re-supply is a requirement associated with large-scale

space operations. Serious system considerations can safely be deferred

until 1961 or later, although in the meanwhile this ultimate application

should serve to guide DYNA-SOAR and other applicable testing activities.

3. Rescue.

A relatively simple satellite with receiver for distress signals

and provision for repeating these, together with the location data, would be

possible at an early date. Studies to define such.a system might be initiated

in 1959-60.

WDZR- 180

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Tran.sEortation-Logistics

Studies to define a system meeting the transportation-logistics

mission requirement might be initiated in 1962.

Space Environment Observing and Forecasting System 

The primary purpose of the Space Environmental Observing and

Forecasting. System is to provide the USAF with an integrated system for

observing, processing, and forecasting meteorological, geophysical, and

astrophysical phenomena affecting military operations conducted at altitudes

above 200,000 feet. A secondary purpose is to observe, from a satellite

vehicle, meteorological and environmental conditions below 200, 000 feet

in support of the "Weather Observing and Forecasting System", GOR 11.

A development plan prepared in response to.GOR 176 proposes to make full use of existing hardware developed under the DISCOVERER,

SAMOS, and MIDAS programs. These include the AGENA vehicle, auxiliary

power supply, guidance and control, ground to space communications, tracking and acquisition stations, and ground data handling facilities. Use will

be made of both the THOR-AGENA combination and the ATLAS-AGENA.

WDZR- 180

IV-5

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V. Space Studies
V. SPACE STUDIES

Areas presently under study to investigate directions of future military

requirements in the space area are listed below:

A. Strategic. Systems.

Within this area the following studies have been pursued during

the past year or have recently been approved.

Recoverable Booster Study (SR 89774) 

This is a study to examine the various means of recovering.

the first stage booster of a space system. The trade-offs between parachute

type of recovery and winged vehicle will be examined, for example, and the

optimum conditions for the use of various recovery systems will be stipulated.

Hypersonic Boost Glide Bombardment-Reconnaissance Studies 

(SR 126)

Purpose of this study is to examine the Military potential of

boosting a winged vehicle into a low altitude orbit so that the vehicle is

maneuverable by means of aerodynamic forces. The potential of using this

concept for bombardment and reconnaissance missions is being explored.

Intercontinental Glide Missile (SR 79500) 

This is a study to examine the potential of using a lifting type

of re-entry warhead which would extend the range and perhaps increase the

accuracy of intercontinental missiles. Preliminary calculations indicate

that for a given booster the range can be doubled over that of a ballistic

missile.

Strategic Orbital System (SR 181) 

The objective of this study is to examine all the potential

military uses of the Earth orbital area. It will take into account all the

present systems such as SAMOS and integrate these into a proposed military

booster for this regime of space.

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Strategic Lunar System (SR 192) 

This is a conceptual study to examine the future military

potential of operating upon the surface of the moon and the area around the

moon and in cislunar space. The type of systems and their performance

parameters are expected to result from this study.

Advanced Ballistic Missile Weapon System (SR 199)

Purpose of this study is to examine the potential and feasibility

of developing a very large ballistic missile. The payloads under investigation will vary from 20 to 100, 000 pounds, and the range required is 8, 500

nautical miles.

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Low Altitude Systems Study (No SR Number) 

This is an in-house, study being conducted at WADC. Purpose

is to examine the feasibility of using a satelloid for military missions. A

satelloid is a low altitude orbital vehicle which must have a small amount

of power applied almost continuously in order to keep it in orbit.

WDZR-180

•

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ileirafeft,

10. Strategic Interplanetary System (SR 182)

This is a broad conceptual type of study to examine the military

potential of operating in the interplanetary area. It is assumed that if the

Air Force is able to operate in the lunar area, it will not be a big step to

start operations in the interplanetary area. This study may determine the

best type of propulsion and guidance systems to use.

B. Defense Systems

Advanced Defense Concepts (SR 49758) 

This study will examine the entire defense problems of the

future when the Earth-orbiting vehicles may be a threat to Ws nation. It

will examine the means of detecting, neutralizing, and verifying the kill of

such vehicles.

Boost-Track Ballistic Missile Defense System (No SR Number) 

Purpose of this study is to examine the means of tracking a

ballistic missile during its boost phase. Such tracking is to be accomplished

by means of an Earth-orbiting satellite. The system would also have the

capability of intercepting and destroying a missile which it detects.

Satellite Inspector System (SR 79998)

This SR has not been started. However, it is proposed to

examine the means of inspecting enemy satellites. It also will examine the

various means of neutralizing enemy satellites, and the various means of

neutralizing a satellite if it is determined upon inspection to be of a hostile

nature.

Satellite Defense Weapon. System (SR 79999)

This is a new study that has not started to date. The objective

is to determine the design characteristics of an air-launched satellite

interceptor weapon system, including both the requirements of the launching aircraft and the space-borne components of the intercepting payload.

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C. Reconnaissance Systems 

Global Surveillance Systems (SR 178)

The objective of this study is to determine the feasibility of

a manned orbital surveillance system. It can be considered a follow-on

to the SAMOS project.

Lunar Observatory (SR 183) 

Purpose of this study is to examine the potential of using a

base on the moon for reconnaissance of the Earth and cislunar space. The.

study is to determine a sound and logical approach to establish and operate

such a base on the moon.

D. Supporting Studies

Retrieval. Conceits (SR 49759) 

The objective of this study is to examine the various means

of retrieving space vehicles. It will also determine when certain types of

systems such as parachute receivery should be used.

Advanced Design Trainer. (SR 49756) 

This is a study to examine various means of training pilots

to operate maneuverable space vehicles.

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VI. Test Support Systems
VI. TEST SUPPORT SYSTEMS

There are a number of key research and development support systems

which are required to test new designs or techniques which may become part

of a new system design or which may be required in applied research programs

designed to advance the space technology. Some of these systems or programs

are described below.

DYNA-SOAR

The objective of the WS-464L (DYNA-SOAR) research program is •

to develop and demonstrate a piloted winged vehicle capable of carrying man

and materials through a sub-orbital, hypersonic boost glide flight regime.

The gliders will weigh approximately 9, 000 pounds and will achieve up to

50 nautical mile orbits. The boosters will be two-stage• variations of either

the ATLAS-CENTAUR or the TITAN missiles.

The planned schedule contemplates initial drop tests in 1961, piloted

ground launches in early 1963, and global flight late in 1963. The global

flight will consist of eastward launch from Cape Canaveral, a circumnavigation of the Earth, and finally a piloted landing at Edwards Air Force

Base in. California. During the various flights a variety of equipment and

techniques will be tested, including environmental system, advanced radar,

communications and intelligence systems.

WS-60.9A 

The WS-609A system is a modified version of the NASA "SCOUT"

four-stage solid propellant vehicle, which is designed to serve as an

inexpensive test bed for launching payloads of 100 pounds to altitudes of

4, 000 miles and 1, 000 pounds to altitudes of 1, 000 miles. The system

serves as a test bed for component and subsystem tests and special research

tests. The initial system will be ready for limited use, concurrent with

vehicle development testing, in mid-1960.

WDZR-180

VI=I

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Re-entry Test Vehicle 

An advanced re-entry test vehicle program is being considered.

Objectives of the advanced RTV program would be to provide a hypersonic

re-entry test environment for the testing of advanced low-cost ablating

materials for ICBM nose cone, the development of low-temperature ablation

materials for lifting type re-entry vehicle heat protection, and for providing

a test environment for the development of heat protection of re-entry vehicles

operating at re-entry velocities up to 30, 000 ft/sec. This re-entry test

vehicle program is desired to provide for the development of suitable heat

protection materials for uses in the various space missions that involve

re -entry.

Hypersonic Lifting Re-entry 

A prOgram of study, 'research, and demonstration of hirperionic

lifting ke .-entry vehicles in a range of designs involving Moderately. low..

ratios of lift-to.-drag is being considered. Studies have been completed by

a number of agencies. A rocket vehicle test program could be instituted

to obtain actual test data on scale models of the desired vehicles under

hypersonic re-entry conditions similar to the applications anticipated.

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WDZR-180
Early phases of this program can be performed relatively easily with

ballistic trajectories utilizing the instrumentation facilities available in the

Atlantic Missile Range. Later tests should involve reentry from a low

altitude orbit and should include test and evaluation of terminal control,

guidance, and communication schemes * as well as obtaining aerodynamic

data and vehicle design evaluations.

F. High-Altitude Sounding Rockets 

JAVELIN-JOURNEYMAN 

These are solid propellant high altitude research vehicles.

JAVELIN was developed for sounding rocket support of the original ARGUS

high-altitude nuclear test. JOURNEYMAN is now under development for

instrumentation support ofijlIllruclear tests. JAVELIN has a 750-mile

altitude capability with about 100-pounds payload. JOURNEYMAN has a

I, 700-mile capability with a 100-pound payload, The fourth stage • of the

rocket is spin stabilized; however, the instrumentation head is de-spun

after fourth-stage separation. The first three stages are aerodynamically

stabilized. The concept is to provide relatively inexpensive, readily movable

sounding rocket support.

JAGUAR

This is an air-launched sounding rocket development presently

undergoing development at AFSWC. The aircraft used is a B-57 which

utilizes vertical launch. This system is an outgrowth of the original NACA

effort which was taken over by the Air Force. Basic advantages for such

sounding rocket systenis are that it provides flexibility and relatively lowcost research and development effort. Launchings in polar regions are con-

.

templated at present. The JAGUAR has a 500-mile altitude capability within

the order of 50 to 100 pounds. The potential of a B1-58 carrier with a better

sounding rocket capability is under study.

The JOURNEYMAN and JAGUAR programs, except for motor

fabrication, are in-house efforts and are launched by Air Force crews.

-SECRET

WDZR-180

VI-3

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VII. Analysis of the Program and

Its Systems
VII. ANALYSIS OF THE PROGRAM AND ITS SYSTEMS

The evolution of a weapon system was outlined, in general terms in

Section I, above. Sections II through VI contain statements of operational

requirements, descriptions. of systems that might fulfill the requirements

and system studies and test support programs that have a bearing on

the selection, design and development of the systems. It is of interest

to summarize the space program schedule and the space systems characteristics, and to discuss the problem of program analysis and system

de sign.

A. Space Program Schedule, and System Priorities 

Table VII-1 contains a schedule of the space system programs.

This schedule includes those systems which were discusiied in Sections

III and IV and which are under development or study, or might be considered, for fulfilling a requirement. The table indicates the study

phase and the active programming phase, and approximate first launch.

and operational dates, where a rough estimate or, in some cases, pure

speculation was possible.

The operational requirements have been stated. Systems to

fulfill the requirements have been described and the schedule and

status of the systems have been summarized. In two instances

(THOR and ATLAS) the systems are operational. A /ow are in the

advanced design stage. Others have been through operational concept

studies and preliminary design analysis, but the majority of the

advanced systems are in the early study phase and have yet to reach

the preliminary design analysis stage.

There are two good reasons for this situation. First, to

date, no one has established a military space program with sufficient

clarity in scope and priority to permit scheduling and funding of the

detailed system analysis and design effort on advanced oystems.

Secondly, the advanced technology required for the understanding and

development of such systems, and the magnitude of expenditures to

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be anticipated on advanced systems argue against the initiation of

extensive development effort on a number of systems until a priority is

established. This situation is not likely to change in the near future

insofar as the advanced systems are concerned, for we are feeling our

way in the new science of astronautics.

With this in mind, a priority must be established among those

near-term systems (1960-70) and they must be analyzed thoroughly.

Development plans must be prepared and development initiated. At

this time, those systems which should receive the most active support

appear to be, in order of priority, the following:

• Ballistic Missile Defense System -

Intensive study, measurements and component

development on a systems basis, directed toward

selection and development of complete system.

Missile Attack Alarm -

Completion of MIDAS development and an immediate,

parallel effort to develop and advanced attack

alarm system to be part of the Ballistic Missile

Defense System and to alert the deterrent forces

and civil defense agencies.

StlxveiHance -

Completion of SAMOS and an immediate parallel

effort on an advanced surveillance system.

Communications - .

Completion of SAC-Polar Satellite, including the.

advanced version, and on parallel basis, initiation.

of development on FLAG (National Survival Communications Satellite).

WDZR- 180

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Satellite Defense -

Completion of development of ground-launched

intercept and inspection system and parallel

effort on extending capability of SPACE TRACK

ground-based satellite tracking and cataloguing

system to skin-track and catalogue all noncooperative satellites passing over U.S.

Manned Space System -

Completion of DINA-SOAR Research Program;

and intense study directed toward development

of a manned multi-purpose space vehicle for

both defense and offense applications.

Two systems not included in the above priority list are the Outer

Space Weapon Test Surveillance System and the Outer Space Weipons

Test System, both of which hold a priority to be determined nationally.

The above outlined development effort must be accompanied by

an extensive advanced systems study program which utilizes industry

capabilities and talent to a maximum.. The ARDC Study Requirements

program, which includes the studies listed in Section V, above, can

produce and guide these studies if the SR program is more carefully

directed and coordinated with space system development.

Associated with the systems development and advanced system

study must be an effort to correlate subsystem and major component

development of the many systems wherever possible, and to initiate

the necessary advanced research and development in critical areas,

which require a decided advance in technology. Such correlation

requires an analysis of the systems involved to determine the operational concept and. design ular importance is the

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develOpment and test of lifting re-entry vehicles and recoverable boosters.

B. Operational Characteristics and System Specifications.

Table VII-2 is a summary of systan specifications or characteristics for some of the listed space systems. In some cases these

specificatiOns . are reasonably firm, in others they are very crude

estimates. Both this table and Table VII-1 are intended to .be based

on data Obtained from established weapon system programs from design

studies and system concept studies. In its present form . the data is

somewhat preliminary but will suffice to show what is being attempted

in the long range plan.

The analysis of a system in sufficient detail to provide

operational characteristics and preliminary design specifications is

usually accomplished in development plan studies and in design studies

made subsequent to development plan approval. It is intended that the

effort associated with the SPADE Plan will promote analysis of the

selected space systems on an accelerated and coordinated basis. in

accordance with the priority accepted and established. This will

permit an expansion of the table and refinement of the data now in the .

table.

In the section which follows, we will discuss the use of this

data and the space program schedule in analyzing future. Air Force

space booster requirements.

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VIII. Subsystem Correlation and

Development
VIII.SUBSYS TEM. CORRELATION AND DEVELOPMENT

SectiOn VII discussed space program analysis and the necessity for

an orderly program of systems development accompanied by advanced

systems studies. The need to correlate major component requirements

and promote technological advancement in critical component areas was

emphasized.

Timely development of the required space systems is a strong reason

for a coordinated technological advancement program. A more urgent

reason is saving of dollars. The cost of space system development and

production is the real governing factor in the kind and numbers of space

weapons which-the U.S. may put into operation. To get the most for our

•dollar, we must not only establish priorities but also must take steps to

minimize the tremendous expenditures per system. -

One big step is the correlation of requirements and coordination of

major component development wherever possible. Appendix "D" presents

some representative areas of technical development and basic research

which could contribute to future weapon systems. The list is not comprehensive in its present form nor does it indicate priorities or areas

of greatest potential payoff. It is intended as a starting•point for correlation of research and development efforts with apace weapon system requirements.

All the technical disciplines listed in Appendix "D" must be considered

in detail for sound planning of their place in new weapon systems. These

areas include communication, radar, computers, tracking, guidance,

power supplies, rocket engines, booster vehicles, controls, reentry,

materials, propellants, low-thrust propulsion, and others. An eventual

objective of the SPADE plan is to relate these technical areas to weapon

system requirements.

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An example of the technique proposed is the analysis of Air Force

space booster development requirements which is included as Appendix "C".

This analysis includes a proposed development program for this major

subsystem. A brief look at the approach to this ten year (1960-1970)

booster requirements analysis is of interest.

A space booster is any particular combination of propulsion vehicle

stages which will place a specified payload on a particular flight path.

As such it includes all integral vehicle subsystems (e.g., propulsion,

guidance and control, internal power, and associated tracking/communications equipment).•

Operational Concept and System Characteristics

The degree to which a future booster can be defined is dependent

on the degree that the payload and flight path can be defined. The first

operational techniques for space are only now being demonstrated. From

these and from experience with ballistic missiles, reasonably-accurate

estimates of concepts and characteristics can be made for some nearterm systems. These data, which were obtained.from individual program

design and development plans, are assembled in Table VII-2. Further

extrapolation by extension to systems in the advanced study area is

necessary for extension through the 1966-70 period. Correlation with

the required time period may be made by reference to the Space Program

schedule in Table VII- 1.

State-of-the-Art

Once an estimate of booster requirements by system is assembled,

it is necessary then to look at the present and projected booster capability.

Booster vehicles available now or in the immediate future are tabulated

in Table C-1 of Appendix "C". These boosters are based primarily upon

the use of ballistic missile hardware with slight modification and the addition of appropriate upper stages.

gn7:1.:7rn:Z710,1

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IMPIr-CONflDOITIAL

It then becomes necessary to look . carefully at the future possibilities in space vehicles, including the research programs in progress,

the advanced studies and state-of-the-art improvement programs in

propulsion, guidance, and other pertinent areas.

A Recommended Program

When the future booster requirements are assembled and the

forecast of technology is known, the proposed program may, be configured.

A compromise is necessary because selection of a limited number of

discrete booster systems, with associated research requirements, is

dictated by the high cost of their development and production. This

compromise does not penalize the individual systems, because the

selection is coordinated and timely and appropriate adjustments may be

made in system planning.

The resulting proposed Air Force booster. program and associated

research program are outlined and discussed in Appendix "C". One very

critical need in this area is the development of an economical booster

which could make certain very expensive space weapon programs feasible

as well as reduce the overall cost of the space program. Approaches

include the design Of a recoverable booster and/or major design improvements in non-recoverable boosters.

Future Analysis

It is intended that, with the cooperation and participation of

interested laboratories and agencies, and through cooperation with

industry, all of the major space component areas will be thoroughly

analyzed. This analysis should uncover critical areas, and selected .component research and development programs may be initiated to support

systems development.

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IX. Conclusions
IX. CONCLUSIONS

The following conclusions are based on the SPADE Plan and the

study and effort associated with its preparation.

The SPADE Plan can serve as an official planning guide in the

Air For ce.Space System Development Program, to assist the decision

process and in coordinating and ordering development effort. The

initial report is preliminary, but will serve as the framework for

continuing study. It will assist using commands in defining operational

requirements, and centers and laboratories in analyzing development

requirements and in prosecuting the development program. Through

the cooperation and participation of interested commands and agencies,

detailed analysis of each of the required systems may be accomplished,

and the report may be refined and extended.

A definite requirement exists for an official statement of system

requirements and a development priority among systems. The r equizemeats outlined in. Section II and the priority stated in Section. VII may

suffice as a starting point for this action.

WDZR-180

IX el

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Appendix A - Definition. of Terms
APPENDIX A

DEFINITIONS OF TERMS

The following selected definitions axe pertinent to an understanding

of the SPADE document:

Booster -

The vehicle system designed to transport the payload into

space, place it on the proper orbits or trajectories, and

control its flight path, attitude and environment thereafter

as required by the mission of the payload. includes propulsion, guidance and control and associated telemetry,

vehicle structural units, and primary auxiliary power sources,

as well as the necessary ground environment incidental to

launch and guidance.

Major cOmponent -

A combination of units or parts that together may be

functionally independent of, or an independent- entity within

a complete operating subsystem, but providing a selfcontained function necessary for proper subsystem and/or

system operation.

Mission -

A specific assignment, service or duty to be accomplished

by a person, organization, office, detachment or the like,

with the object of contributing functionally to an overall

objective.

Payload -

The functional package including sensors, instrumentation

and supporting bracketry which must be placed and maintained in the appropriate space environment in order to perform

the primary mission of the space flight.

WDZR-180

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CONFIDENTIA1

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Plan -

The detailed approach or methodology to be employed in

attaining specified program objectives, includes summarisation of physical characteristics, the operational concepts

involved and the resources needed for successful accorn -

plishment of the objective.

or:

The design, method, or scheme for accomplishing a mission

or reaching an objective.

Space system -

An integrated relationship of all subdivisions of an operating

complex including checkout/servicing equipment, together

with associated personnel; all aligned to establish proper

functional continuity towards the successful performance of

a defined task or tasks.

Subsystem -

A single module, or a combination of modules, plus independent components_ that contribute to modular functions, all interconnected and interrelated within a system and performing a

specific system function.

System integration -

The process of insuring that all elements of the entire system

will properly perform their functions, are mutually compatible

and are available in a timely manner.

Weapon system -;"

Equipment skills, and techniques, the composite of which

forms an instrument of combat. The complete -weapon system

includes all related. equipment, material, services. and

personnel required solely for the operation of the air vehicle,

or other major element of the system, so that the instrument

of combat becomes a self-sufficient unit of striking power in

its. intended operational environment.

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Appendix B. - References
APPENDIX B

REFERENCES

A selected list of references applicable to the systems discussed in

the SPADE plan are included below. This list is not intended to be inclusive,

but does list development plans and other documents of principal interest.

Offense 

THOR (WS-315A)

ATLAS (WS-107A-1)

TITAN (WS-107A-2)

MINUTEMAN (WS-133A)

Defense

MIDAS

(Missile Attack Alarm)

SAINT

(Satellite Interceptor)

Surveillance 

SAMOS

Development Plan

GOR 50

Development Plan

GOR 104

Development Plan

GOR 104

Development Plan

GOR 171

Development Plan

Development Plan

GOR 170

SR 187

Development Plan

GOR 8Q

August 1959

November 1959

(In process)

August 1959

August 1959

30 January 1959

10 August 1959

30 January 1959

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Communications

COURIER

STEER )

(Polar Satellite) )

SAC POLAR Satellite)

)

TACKLE/DECREE )

(24-hour• Comm. )

Satellite) )

FLAG

(National. Survival)

Support 

TIROS

(Weather Observation)

TRANSIT

(Navigation)

Test Systems 

WS-609A

Development Plan November 19 59

AREA Order 17-59 (In process)

Development Plan December 1958

(New plans in

process)

Development Plan 27 July 1959

Development Plan 30 June 19 59

GOR 176

Development Plan (In process)

Development Plan 18 May 19 59

System Directive 609A 5 February 19 59

DYNA-SOAR

OSWT

Development Plan

GOR 92

SR 126

SR 181

Development Plan

25 November 1957

1 September 1959

WDZR -180

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•

Appendix C - Booster Development

Requirements
APPENDIX C

AIR FORCE MILITARY BOOSTER DEVELOPMENT PROGRAM

A. INTRODUCTION .. - A-space booster: is the, Ar..eliitle: syistern designed. to transport the' payload into

space, place it on.the proper orbits or trajectories, and control its flight

path, attitude and environment thereafter as required by the mission of the

payload. It includes propulsion, guidance and control and associated telemetry, vehicle structural units, and.primary auxiliary power sources,. as well

as the necessary, ground environment incidental to launch and guidance.

The objectives of this analysis are to:

Establish general. criteria as a basis for planning a:military.

booster development program.

Review military booster needs.

(iii) Define the booster development program which will most economically fill military needs.

B. BASIC CRITERIA

Space, systems are by their very nature complex and expensive.. As

will be seen later,. military system needs are rapidly being defined and

expanded. Extrapolation of present-day costa indicates that, under. present

concepts, this nation cannot afford to. develop all the systems which will be

needed. In some cases where high launch rates are required.to make.a

system effective, the cost of one system alone may be prohibitive. The

: • . United States Must maintain a balanced effective defense posture against

. . attack. Therefore,. criteria for planning space system and booster devel-

, . .

.opment should be based on an over-riding need for reductiOn in cost.

. . . . . . Methods for reducing costs in terms of dollars per pound of payload.

are currently under investigation. This analysis is based on the fact that

. . • :

the major costs presently involved'in the operation of ballistic missiles

and space vehiCle systems are hardware manufacturing costs and those

associated with- launch operatiOna.. A long range objective should be to

evolve booster designs which make maximum use of economical materials

WDZR-180

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and eolvrAtruction techniques. Checkout and count-down operations must

be simplified to eliminate complex support equipment and facilities as well

as. reduce the operational manpower needed.

Reduction in development costs can be accomplished by developing

boosters, subsystems, and stages• which are usable for a variety of

missions with a minimum of modification. The possibility of combining

payloads to perform more than one type of mission is also attractive. New

booster and subsystem developments should be carefully planned to insure

grOwth •potential and direct applicability to later requirements insofar as

they can be defined. This would enable a minimum of new booster. stage,

and subsystem development programs.

Reduction in production costs could be achieved in three ways. The

ability to use major portions of the same booster for different payload and

trajectory requirements results in greater gross production with a commensurate reduction in cost per limit. Possible recovery and re-use of

major portions of the booster vehicle could result in substantial savings.

The savings actually obtained in stage recovery depend on the balance

between the coat of recovery and the cost of a new stage. They will be a

function•of the number of different missions the same stage will be used

for since this will determine the number of launches over which the cost of

a recovery system can be amortized. They will also depend on the ability

of the recovered stage to be used again with a minimum of inspection, repair, and checkout.

Rlduction in the cost of launch operations could best be obtained by

reducing the ground facility and support equipment requirements. Decrease

in subsystems complexity would, in addition, tend to simplify checkout and

count-down operations. This would reduce technical manhour requirements

as well as provide more efficient launch-facility utilization.

The ever increasing need for greater performance and versatility of

booster systems appears in conflict with the above discussion. Analysis

of staged weapon systems indicates that overall performance, and versaplauntik rik WDZR-180

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11111-CONRDENTIAt

tility of booster vehicles are most sensitive to the design and performance

characteristics of the last stage. Since the final stage is also the smallest,

it is easier to handle, and involves smaller weights of hardware. 'In order

to make-maximum use of the larger stages, a greater variety of last stage

designs appear to be needed. The need for maximum performance on the

more stringent missions dictates that emphasis should be on the use of

highest-energy pr'opellants in the last, stage. This does not necessarily

obviate the continued need for versatile work-horse stages with more moderate-performance propellants which are logistically easier to handle.

A final consideration is based upon the fact that, at present and for

the next few years, our major space booster capabilities rely on existing

ballistic missile hardware. Space was not considered a practical reality

when ballistic missile development was initiated. The state of our tech-

, nology and the nature of the threat also made cost a secondary objective.

As a result, present space vehicles using ballistic missile stages are

expensive items at any production rate. Present booster vehicles with highenergy upper stages appear sufficient for immediate needs but order-ofmagnitude increases in. capability are required in the near future. Development of new high-energy upper stages for use with ballistic missile stages

should be conducted with their possible applicability to later, more optimum,

space boosters in mind.

In summary, general criteria for planning ,a booster development program

for space vehicles must be based on an overriding need for reduction in cost

per pound of payload. These, criteria are:

Stages and booster* shotdd be sized and developed to accommodate

a maximum number of mission/payload requirements with a minimum of

modification.

New stages developed should include a reasonable growth potential and be adaptable for use with larger follow-on booster vehicle developments.. "Dead-ends' development should be avoided.

(iii) Large stage development should be based on maximum simplification of design,. fabrication techniques, and launch operations. Ruggedness

WDZR-180

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and simplicity at the expense of over-all stage performance will be acceptable U significant economies result.

Maximum performance and sophistication should be planned for

the development of final booster stages.

The broadest approach to long lead-time development should

apply to final stage subsystem development.

C. MILITARY BOOSTER. NEEDS

The degree to which a future space booster can be definpd is dependent

on the' that the payload and flight path involved can be defined. Intensive study and analysis Is being performed to establish the various military

potentialities of space. However, demonstration of operational techniques

for initial military space systems is just starting. Not enough is now known

about true space environments and a well-planned and conducted program

of space exploration is needed before many presently indicated military

possibilities can be confirmed and weapon systems defined in detail.

The extent to which missions and payloads can be defined is a function

of how far analysis extends into the future. This means that booster needs

for the near future can be quite definitive. However, exact definition of

booster needs ten years hence is impossible and, in fact, unnecessary.

Table 1 lists presently available and immediate future space booster

vehicles based on ballistic missile stages. Approximate mission payload

capabilities are also indicated. Maximum immediate. capabilities range: from

abolit.6,000 pounds in a 300 nautical mile orbit to about 400 pounds in 24-hour

orbit. The first need is to achieve maximum practical use from the existing'

ICBM stages. With no major structural modification it appears that appro-

.

priate upper stages using high-energy propellants can provide capabilities

up to about 8,000 pounds in a 300 nautical mile orbit and about 1,600 pounds

'in 24-hour orbit. The most attractive vehicles of this type are illustrated

in Figure 1. This will be sufficient to accommodate systems presently

approved for development and many follow-on requirements. However,

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WDZR-180

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performance requirements have been defined for the 1963-64 time period

which need substantially greater mission/payload capabilities. Some of

the major systems which have been defined and their present status are

as follows:

(1) FLAG - National survival SAC communication system. This

requires up to 4,000 pounds in a 19,400 nautical mile equatorial orbit. A

development plan has been submitted.

WHITE SAINT - Unmanned satellite inspection and/or negation

system. This requires about 3,500 pounds in orbits tip to 2,000 nautical

miles. A development plan has been submitted.

DYNA-SOAR I - Hypersonic glide vehicle. This requires a 7,500-

10,000 pound payload launched into a 50 nautical mile apogee glide path.

This program is awaiting final approval.

(iv) Advanced Ballistic Missile (GOR 180). This requires payloads of

up to 20,000 pounds delivered over an 8,500 nautical mile range. Detailed

system studies are being performed.

Booster stage :requirements are firm :for niost..of theit systems. ..The

exact booster configuration which will be developed to accommodate thezp,

however, wi11 be determined by the first system or systems approved for

development and their relative priorities. It appears that a first stage of

about 800,000 pounds thrust and a second stage of about 200,000 pounds

thrust with appropriate third stages can best provide the desired performance.

For instance, addition of a 30,000 pound thrust stage using high-energy propellants will more than satisfy requirements for the FLAG. system.

For the 1964-66 time period, requirements are less clear and more

subject to revision. Military mission/payload requirements which can

be described range from realistic approximations to pure guess. In addition,

there are distinct possibilities of now undefined requirements due to rapidly

advancing technologies, the results of studies now being performed, and the

possibilities of combining some payload requirements. Some of the highThis Onwasit midgets informed'. oftetIng the isotkowl Mosso et Me Wiwi Labs wale Mw 11.1110111110 11/ Mr 7:sphaNfo Laws. lift

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payload system needs which appear more clearly defined are as follows:

Advanced FLAG - 24 hour military communications satellite.

BLUE SAINT - Manned satellite inspection and/or negation system.

DYNA-SOAR II- Manned orbital boost-glide bombardment/reconnaissance system.

Advanced Ballistic Missile (SR 199)

AICBM - Satellite-borne ICBM negation system.

In addition, studies are underway and possible systems have been investigated to varying degrees for advanced reconnaissance satellites, satellite

bombardment systems,' advanced missile detection, tracking, and negation

systems, and even 'manned space stations or lunar bases.

By the time a decision can be made (around 1964-66) to initiate stage

development for the 1967-70 time period, much more will be known about

space and the military potential of operating therein. Possibilities demonstrated by then for nuclear or other new propulsive means may change the

current outlook for chemical propulsion. The possibility of assembly- inspace techniques or orbit rendezvous and refueling techniques may make

larger payloads more practical through the use of several smaller boosters

instead of one giant booster. A recent study performed under ARPA Order

93-59 and based on extrapolations of present day experience indicates that

orbit-refueling, using "tanker" vehicles and chemical propulsion, might be

more economical than the use of single very large chemical systems or even

advanced nuclear systems. The only safe statement which- can be made today concerning booster requirements for the 1967-70 time period is that

missions will be more stringent, flight paths will be more complex, and

payload weight requirethents will be much larger. Not all new systems

under study now will be developed. Some may be combined, at least as

far as basic payload configuration is concerned.

D. RECOMMENDED PROGRAM

There are two basic approaches to filling future space booster needs.

One is to base plans on extrapolations of present-day technology and the
assumption of propulsion, secondary power, guidance, and control, and

structural subsystems similar to those in existence. This is the conservative approach. Unfortunately, this approach results in booster

vehicles, stages, and -subsystems whose cost appears to prohibit development of the numbers and kinds of systems which appear to be needed.

There is need for an economic breakthrough in the development of

large chemical booster stages. Present analyses indicate that the

following characteristics are required.

Simplicity

This requirement dictates a minimum system complexity and

number of operating components. Design simplicity indicates a prefer

ence for pressurized feed systems, the use of a minimum number of

propulsion units, elimination of mechanicS1 vector control, if possible,

and a minimum of components requiring close tolerance manufacturing

or exotic materials.

Ruggedness

Stages should be designed for rough handling and possible stage

recovery and re-use.

Reliability

Design, fabrication and operational procedures should be directed

toward maximum probability of mission success.

Simple Pre-launch Checkout

There is need for drastic improvement in checkout. procedures

and reduction of associated launch equipment needs.

Means for accomplishing the above objectives have bedn investigated.

Preliminary results indicate the feasibility of a completely new approach

to meeting stage requirements for large military boosters. Two new

stage design concepts have been evolved. One, designated "Phoenik"„

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applies to high-thrust stage requirements. The other, designated "Aurora",

applies to altitude stages using high-energy propellants. Further analysis

of both concepts is continuing and initial developments to prove weapon

system potential are proposed. They will be outlined in greater detail in the

following discussion of the over-all recommended booster development

. program.

Requirements for the 1962-63 time period must rely on the conventional

approach to high-thrust stage development. An over-all program must be

planned commensurate with the criteria outlined in Section B, using conventional chemical stage design. This is in the full realization that at some

later date, currently thought to be three to six years hence, major decisions

will be needed based on progress made with the Phoenix concept.

Figure 2 illustrates, by a cross-hatched band, how payload needs are

expected to increase using a 300 nautical mile orbit capability for comparison.

The width of the band is indicative of the degree of uncertainty existing conearning these needs. The diagrammatic vehicles shown are only examples of

booster vehicles possible with the propulsion systems proposed for development. This is in recognition of the fact that stage size is largely determined

by the propulsion system. Actual vehicles developed will depend on the

individual military weapon systems approved for development.

The specific program recommended in the high-thrust booster area is

delineated in Figure 3. Propulsion and propellant tankage requirements

have an overriding effect on booster size and thrust requirements so it

is outlined in that context. The need to insure success in attaining advanced

capabilities in space dictate propulsion backup approaches due to the somewhat unpredictable nature of advanced rocket propulsion development

programs. The need for economy and the rapidity of technological advances

dictates close monitorship of the over-all program and the ability to make

rapid technical and program decisions. Some of the major decisions we

presently foresee are indicated by numbered boxes in Figure 3.

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There are two possible approaches to achieving an 800,000 pound thrust

first stage for the 1962-63 time period. One is to take advantage of the

ballistic missile program and the uprating of the basic LA. 87 engine to

200,000 pounds thrust using storable propellants. The other is to use the

LR. 109 basic engine currently rated at 300,000 to 400,000 pounds of thrust.

This engine does not have the extensive development testing already achieved

with the LR 87. However, it does have growth potential to over S00,000

pounds thrust and is simpler, using fewer engines in cluster to provide the'

thrust needed in vehicles for this period and for follow-on vehicle stages.

It is recommended for primary development toward. an 800,000pound

thrust booster stage. The LR 87 is recommended as a primary conventional

development toward an altitude engine for, the required second stage and as

a backup development toward the first stage requirement. As is indicated

in Figure 3, two major decisions should be possible about one year after

initiation of the program. First, it should be possible to decide on a single

approach to meeting 800,000 pounds thrust stage requirements. Second,

detailed technical and cost analyses performed in the meantime should

indicate whether the LR. 87 altitude engine should be paired to fill later

400,000 pound thrust second stage requirements or whether an altitude

version of the LR. 109 engine would be more desirable.

The F-1 (one million pound thrust) engine development, currently under

NASA sponsorship should be oriented toward filling conventional first-stage

requirements for military boosters of the 1964-66 time period and beyond.

It should be recognized, however, that the thrust developed by this engine

is more than three times that of other engines in existence. The classical

problems involved with the scaling up of rocket engines (combustion instability,

heat transfer, vibration, injector design) may offer complications yet undeteri.

mined. Well over a year of aggressive development and test are n-;eded

before systems development planning can be- based on a firm engine development schedule.

The basic LR 109 engine in a cluster of three or four can provide the

needed stage propulsion. It is considered the best backup to producing

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1,500,000 pounds of thrust with conventional engines. As is indicated

in Figure 3, a decision should be possible within two years as to which

propulsion system should be selected for stage-oriented development.

The. Saturn booster, currently a responsibility of the NASA, is a

more costly endless desirable approach to filling high-thrust booster

requirements in the 1962-63 time period. It is a dead-end development

as far as follow-on requirements are concerned. However its performance capabilities are expected to be roughly comparable to those of boosters

using the 800,000 pound thrust stage described above. It is therefore con-

..

sidered a backup propram for filling first-stage requirements in the 1962-63

time period..

Since booster stages for the 1962-63 time period and beyond will be

specifically intended for space weapon systems, the primary design

considerations will be economy and reliability. Maximum economy of

operation involves recovery and reuse of first stages and, possibly, second

stages. The most promising approach to acceptable reliability is through

simplicity and standardized well-developed components. Together these

requirements dictate development of a new type of first stage which exists

today only as a design concept which has been given the name Phoenix.

At, present the most attractive Phoenix configuration is based upon the

use of a pressure-fed propulsion system using liquid oxygen and liquid

hydrogen, an =cooled ablating plug nozzle and segmented combustion

chambers. Rugged tanks would be designed specifically to facilitate

stage recovery and re-use. High-energy propellant performance and

continuous optimum expansion characteristics would offset the use of

lower chamber pressures. Combustion chamber development in single

segment size would permit flexible engine sizing by choice of number of

segments. If this particular design continues to be attractive after further

investigation, the Phoenix program could start quickly by initiating sybsystem development without commitment to a stage size. Subsystem work

would include a chamber-segment test program, tank pressurization techiossomool amlohn IsfonoeSos offoolhop lho aolloost &Sow of Sr WW1 Slam 14114o lbw foosolos of Ns boiloorso foofflo Ulm IS, U.S.C., Sulfas 713 owil 794. No toomosloolso wooled.. .hied la awl wart is so oftooO ►oolo•d fame Is pooklblloi by low.
nique investigation, plug nozzle flow analysis and experimentation, and •

ablating material tests. A corollary stage recovery and reuse program

to include analysis and demonstration phases would be essential. The

TITAN first stage is an attractive stage for development of recovery and

reuse techniques.

Figure 3 indicates that aggressive practical investigation of the

Phoenix concept should be initiated now. At such time that successful

development of high-thrust stages has been proven feasible under this

concept, a major decision must be made as is indicated in the figure.

The goals of the Phoenix program are such that their achievement could

result in a phasing out of the conventional approach to high thrust stage

development. Figure 4 illustrates the present concept of what a Phoenix

booster vehicle would look like. For illustrative purposes only, consecutive 800,000 pound and three-million pound thrust stage development.

were presumed.

Another approach to simplification of high thrust stages which should

be considered is through the use of solid propellants. The present

MINUTEMAN, POLARIS, and PERSHING programs will provide a family

of stages with thrusts ranging up to over 100,000 pounds. Use of these

motors will very likely be found in specific weapon system programs.

However, --the potential of solid propellants for very high thrust applications

cannot be determined until the results of the present high-impulse stateof-the-art program are known and detailed systems cost analyses have bean

completed involving production, handling, performance, and operational

parameters. The state-of-the-art investigation should be continued until

the potentialities of very large solid propellant motors can be determined.

Emphasis in upper stage development should be on the use of high-energy

propellants. While technological improvement in other subsystem areas

such as guidance, secondary power, stabilization and control should be rapid

also, propulsion development is still expected to be the controlling factor for

stage sizing and availability. As is shown in Figure 3, first developments

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are designed for use with ballistic missile stages. The NONIADAPressurized

fluorine/hydrazine) and.CENTAUR (pump-fed ozygen/hydrogen) programs are

currently being actively prosecuted. Another concept which has been.evolved

-as a result of systems cost analyses, designated "Aurora", is exemplified by

a pressure-fed upper stage system using an uncooledablative bell nozzle. The

initial stage in development Of the Aurora concept is the 15,000 pound thrust

HYDRA shown in /gime 5. It is now ready for development to prove-out the

concept. Once the concept is proven, it should be applied to subsequent

Aurora stages which could be developed in the 30-60 and 100-150,000 pound

thrust ranges. These would provide stages applicable for use with high thrust

stages which would evolve from either the conventional approach to the Phoenix

approach to development.

The demand for maximum performance and versatility in the last stage

indicates that present types of propulsion systems, both pressure-fed and pup:ogled should be judiciously developed. In the 100-150,000 pound thrust range, pump

fed systems would be explored with emphasis on the liquid oxygen-liquid hydrogen propellant combination. Techniques for restart and thrust modulation

should le established and sufficient work using all attractive propellant combinations be pursued to determine conclusively their relative merits for

system applications as they arise.

The liquid fluorine/liquid hydrogen combination offers the greatest performance potential in chemical propellants. No aggressive program now exists for

determining whether this performance is practical of achievement. A program

should be pursued at a modefate level to determine the answer to this question and

establish the feasibility of pump-fed systems using fluorine. The experimental

pump program would also be applicable to stages using fluorine with hydrazine.

No decision times are indicated in Figure 5 as they were for Figure 3. This

is because the upper stage program should be broad in scope, under continuous

close surveillance, and frequent technical and management decisions will probably

be required. Not discussed here in detail, but also required to enable successful

accomplishment of military missions by the booster vehicle are broad programs

for th e development of low thrust vernier maneuvering, and attitude control

propulsion systems.

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Appendix D - Representative Research

and Development Areas
APPENDIX D

REPRESENTATIVE RESEARCH AND DEVELOPMENT AREAS

This section mentions representative development and research areas

which are or could support military space systems development. The

lists are organized by technical disciplines and should be considered as

preliminary information. No effort has been made to indicate a priority

or associate the subjects with specific systems development programs.

The list is included merely to suggest areas of interest and to stimulate

further study and suggestions.

A. Development Programs 

The prOgrams represented by the items on the list shouldmbe con-

, timed or initiated at an early date in order to meet system requirements.

1. Communications and Radar 

a. Transmitters 

High Powet 

High-power transmitters and duplexing techniques

permitting simultaneous transmission of command .and reception of

telemetry data, or a single direction antenna, are required. High-power

solid-state devices should be developed for high efficiency transmitter

amplifiers.

Airborne

High efficiency, light-4eight, phase-stable,

airborne transmitters with power output of 100 watts or greater are

required for long range telemetry and accurate guidance systems.

b. Telemetry and Command 

(1) Automatic 

Develop automatic telemetry demodulation and

recording equipment for digital information; FM telemetry demodulation

equipment for extremely noisy signals.

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Secure Telemetry Transmission

Secure transmission is defined as transmissions

which cannot be decoded, even though complete engineering information

is available to an enemy interceptor. One example is the use of

psuedorandom noise techniques for encoding digital information.

Digital Telemetry and Encoding 

Digital telethetry provides a capability for

automatic ground data demodulation, recording, and processing.

Techniques should be developed for digitizing as wide a variety of

data as feasible.

Digital Telemetry Transmission 

Digital transmission systems must be developed

which provide maximum information rates for given transmitted power

level and for given bandwidth of radio signals.

Secure Commands 

Secure command transmission systems should

be developed.

c. Receivers 

(•) Low Noise 

Low noise, light-weight, efficient amplifieis

are required to provide long range communications with a minimum

weight of communications, equipment in the vehicle. Maser•and

parametric amplifier technology should be applied.

(2) Solid-State 

Solid-state receivers providing excellent noise

figures are urgently needed. These receivers must have minimum

power drain so that continuous operation within a satellite is feasible

for periods of a year or more.

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Phase-Lock 

Development of improved phase-locked receivers

with narrow bandwidths are required in order to receive very weak

signals in the presence of noise.

Correlation 

Advanced data correlation techniques should be

developed for improved communications, radar detection, and security

against jamming. •

d. Antennas 

(1) Large Size 

Economical large antennas must be developed.

Large antennas are needed for earth satellites to provide wide

communications bandwidth with.reasonable transmitter power.

Such antennas are obviously badly needed for lunar probes, and

interplanetary probes as well.

(Z) Back Lobe Control 

In ground installations the primary beam of the

antenna is pointed at a source with a low noise temperature and the

back and side lobes are directed to receiving radiation from a source with

high noise temperature such as the Earth. Therefore ,it is necessary

to develop antennas which eliminate the back and side lobes as much as

possible, in order to take advantage of the low-noise receiver characteristics.

Electronic Scanners 

Electronically scanned antennas will relieve the

problem of accurately and rapidly positioning very large ground-based

antennas.

Position-Seekers 

Light-weight, directional, position- seeking antennas

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are required for use in space vehicles. It is necessary that vehicle antennas

be .directional in order to have high gain. Because of the directional properties of the antennas, it is necessary that they` e self-orienting.

e. Radar Systems

Improvements 

Improved radar performance through.the development

of modifications for existing radars. (e. g. , FPS-16) are required.

Ground-Based 

Ground-based radars capable of detecting space vehicles

of 1 square meter at ranges to 30,000 miles (24-hour satellite range), and

of accurately tracking ihem, are needed as sensors for SAINT-type program.

(3) Satellite-Borne 

Satellite-borne radars for detection and tracking of

other • satellites at ranges from 30 miles (for SAINT) and greater require

major state-of-the-art advances.

2. Computers and Control 

a. Control 

(1) Simplified Guidance and Control 

Methods of avoiding the use of a stable platform in

boosters to obtain simplified guidance and control should be investigated.

One possible approach consists of using improved wide-angle body-mounted

gyros instead of a.platform.

(Z) Pneumatic and Hot Gas Servos

Present methods of thrust vector control generally

require power servos to accomplish the thrust vectoring Pneumatic servos,

particularly those employing hot gas, show promise of. increasing system

reliability and producing simplification. The development of a hot gas servo

system capable of operating directly from gas obtained from missile fuel

combustion is desirable.

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13) Miniature Inertial Platform for Attitude' Reference

Such a platform v411, be useful for a number of attitude

control and orbit correction.applications. In particular it will be useful for

such reorientation.taslcs as are beyond.the capability of autopilot systems

and in which.a.full inertial guidance system is not required, or in which

radio guidance is used.

(4) Hot Gas Sources 

Development' of an efficient chemical energy source

of hot, high pressure gas, for use in attitude control and orbit-keeping of

satellites using jet reaction is needed. Present systems using cornpresseE

inert gas .fora this lun.ction are unduly heavy and of limited •life. The system for

must be stable, reliable, controllable and instantaneously restartable.many

times.

Operational. Flight Safety

A general purpose inertial operational flight safety unit

would.be applicable •to a variety of missions, and will probably be necessary

for some.

Orbit Control 

The development and demonstration of orbit-keeping

subsystems for space satellites must proceed as rapidly as possible. This

equipment is a vital functional part of any operational system which utilizes

a large number • of earth satellites whose positions must be maintained

precisely. A.most common application of the requirement for orbit-keeping

is in systems where a large number of satellites are used to provide complete ,

coverage over the surface of the Earth, or a portion of it, for purposes of

reconnaissance, surveillance, or communication. An accurate system of

position-keeping of the orbit of each satellite will reduce to a minimum the

number of satellites necessary to make the over-all system successful.

Orbit-keeping equipment is scheduled to be .developed in.Project TACKLE

or Project DECREE of the Communication Satellite Program, and can be

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expected to be useful in the . satellite AICBM. program, the Satellite Interceptor

ProfiTam, the. Reconnaissance . Satellite Program, . the navigation satellite

program, Program MIDAS, outer-space weapon. testing surveillance systems,

weather • surveillance systems, and•similar satellites. Because of the widesprees:Luis. anticipated.for this type of equipment, and the...lack of present

experience in its design and system integration, thistechnology should be

developed:at a. research level at the earliest possible.moment.

. d. Computers

The following developments in Ihe computer area are

applicable.to missile and space programs, and should. e supported:

Thin-film memory computer

Thin-film circuit techniques

Minimum power and weight computers

Minimum, powei circuits

Connectors for compact memories

Phase-logic computing systems. (information-carried

in phase of sine wave)

(vii) . .11igh-speed elements and microprogramming

techniques (minimum number of components) •

(viii). Efficient digitisation of data.

3. Guidance and Tracking

a. Inertial. Guidance

(1) Lightwei:ht System

A lightweight inertial guidance system is required

for •.injection.guidance applications to be used in many of the military space

mission.programs. Such a unit might also be used with a.modestly

manueverable re-entry nose cone or lifting vehicle to reduce aerodynamic

or. MECO error-induced dispersions. It could also be used.during lifting

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re-entry to control the impact point or .for changing, target. The CENTAUR

program has such a guidance system development project associated with.it,

and this should be continued, but the development of a.second such system,

of somewhat different performance and capability, should.be started in 1960.

Some study evaluation of subminiature techniques in. desirable as a companion

to microelectronic computer developments.

. b. Radio' Guidance 

11) Modulation 

. IL-- There is a requirement for more-simple and-more

reliable modulation and demodulation techniques in order to obtain more

accurate guidance. Modulation and demodulation.equipmentis. used in

systems which resolve angular ambiguities while operating at signal-tonoise ratios. which are less than unity.

Phase Stability,

There is a requirement for techniques and equipment

with greater phase stability in interferometer systems. The ability to

accurately measure angles and angle rates depends o•phase stability of the

equipment.

Very StableOscillitors 

It is possible to simplify guidance equipment by utilizing

very stable oscillators in the vehicles. The use of a very stable oscillator

enables' Doppler measurements to be.made from one .way transmission.

(4). Secure Communications Techniques 

Secure communications techniques must be developed

for incorporation into radio guidance systems. Such techniques are essential

if radio guidance is to have a place military guidance applications. The

problems involved are quite.difficult, and a great deal of development work

is required to resolve them.

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Wide Base Systems

Development of an operational wide base radio guidance

system is required if radio guidance accuracy is to be improved by a large

factor,

Frequency Conversion 

There is a requirement for a small, reliable,

lightweight device for performing frequency multiplication and division.

c. Terminal Guidance 

The use of terminal guidance enables a vehicle to hit a target

when the location of the impact point is not accurately known at the time of

launch. Development of accurate terminal guidance systems may help make

AICBM and tactical ICBM and IRBM systems possible. The following types of

terminal guidance systems should be developed:

Map matching systems

Infrared seeking systems

Radio frequency seeking systems

Other types of terminal guidance • systems

d. Tracking

Automatic Steering 

Techniques are needed which will accurately steer

ground station antennas to the correct azimuth and elevation for a passing

satellite, based on the transmission of a few parameters from a central

computing center. Such equipment must be economical and simple to be

widely used in a number of ground tracking stations. Further, such a computer at each station will reduce the work load on the central computing

facility such as the SPAN Center.

Range Instrumentation

• As guidance systems become more and more accurate,

radio tracking systems to measure guidance system performance must be

developed with improved high accuracy.

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WDZR-180
Automatic Search 

Equipment for automatic search acquisition and tracking

of satellites under conditions of low transmitter power, high angular tracking

rates, short transmissions from satellites, or combinations of all three, is

required.

Ballistic Camera

An Improved ballistic camera capable of tracking from

launch through engine cutoff is required for adequate ICBM flight test evaluation. With the current camera, the flashing light carried by the vehicle is

obscured by the light from the rocket engine. A camera shutter, synchronised

with the flaming light, and with a very short exposure time, is required.

4. Power

Intensive effort should be directed toward development of ultralightweight high efficiency electrical power conversion and generation systems

for use in space vehicles. Efficient power sources of lifetimes from a month

to several years will be needed. Solar cells, fuel cells, and thermal energy

converters should be considered..

Solar Cell Auxiliary Power Systems

Solar radiation affords an excellent means for providing

power aboard satellites which must remain in orbit for long periods of time.

There exists an urgent need for reduction in the size, weight, and cost of

silicon solar-cell arrays. Novel schemes for orienting solar energy concentrators or large arrays toward the sun must be developed in order to satisfy

the increased power requirements of satellites without making excessively

large booster vehicles necessary.

Electrochemical Batteries 

Batteries are used in all missiles and as energy storage

devices aboard satellites. It is necessary to continue development and

evaluation of various types of batteries to achieve improvements in specific

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weight, cycle. of life, internal impedance, usable.teraperature range, shelf

life, and packaging. New test techniques to predict performance are needed.

Fuel Cells

Certain types of fuel cells show promise of yielding much

lower specific weight in applications where electrochemical batteries are

now used. A regenerative.fuel cell, system should. be developed capable of

gravity-free operation for one year. Maximum output power should be

200 watts after at least 2000 charge-discharge cycle"s. Nonregenerative

fuel cell systems should be developed for one-houro one-month lifetimes.

Rotary Energy Converters 

For large but short duration hydraulic and electric loads,

turbine driven. umps and electric generators .give a. system of low specific

weight. Continued development of hot gas and solid.fuel turbine. drives, and

novel.types• of brushless generators, and variable speed-constant frequency

generators, it required.

e. Static Converters 

Development should be continued on solid-state static

inverters and voltage changers in the 1. KW range and above, to yield maximum

possible• efficiency. Methods of improved radio noise. suppression in circuits

which.use switching devices should also be developed.

5. Propulsion and Vehicles 

a. Chemical Booster Systems 

(.1) Conversion of Present Systems.

Convert present ICBM engines. (e. g. , ATLAS) to

LOX-NH4

 combination for higher payloads and longer range capabilities

(interim Big Bang applications).

(2) High Altitude Performance 

Develop high altitude performance capabilities for the

present• ATLAS and. TITAN booster engines. This includes high expansion

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ratio nozzles and altitude start and restart capability so that these engines

can be used in upper stages-for very large boosters.

400,000 Pound Booster

• Develop a. LOX.RP booster engine of the.500K thrust

levet class (such as the Rocketdyne E-2) for use in second generation.ICBM's

of the Big Mang type, and also in boosters-for various Air Force space

missions.

Reliability

Develop reliability features in. booster 'engines suitable

for. rnanned.missioni. (Man-engine integration. )

b. High.Energy Chemical Systems

Small Engine,

Develop small 02 -H2, pressure-fed engine. with. uncooled

thrust chamber (i. e. , Hydra) for, general upper stage use. (SAINT, . Communications Satellite, etc. ).

Fluorine 

Develop small fluorine stage (in combination with N2H4

or possibly H2) fora upper stage ballistic missile application& reguiring•high

energy propellants and more compact envelope than the • 02-H2 stage.

(3) Medium Engine 

Develop medium sized•0 2 -H2 pump-fed engine for use

as upper stage..engines of super. booster systems. Basic engine size should

be 150K to 200K thrust level.

e. Storable Propellant Systems

(1) Ballistic Missile • Applications 

Develop small storable propellant engines for use in

ICBM systems with greater mobility. These could be N204-N2H4, pressurefed engines with..uncooled thrust chambers. Thrust range would be 10,000

pounds to 30, 000 pounds and greater, depending on stage applications.

WDZR- 180

-CONFIDENTM-D- 1 1

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Space. Vehicle Applications

Develop a. family of. small storable rocket engines for

various space application—manned and. unmanned missions. These engines

should have restart, maneuvering, and throttling capabilities. They can le

. . monopropellant or- bipropellant storable systems. Thrust range . would be

anywhere .from 50 to 5000 pounds.

Attitude Control System

Develop a.monopropellant or.bipropellant propulsion

system.for a lightweight, long-life,. quick-response attitude.control system.

. d. Movable Nozzles 

A large effort is currently, underway to develop nozzles

movable about One axis for the . MINUTEMAN system. This effort should be

continued, and in addition, nozzles capable of two degrees of freedom should

be .investigated as a product improvement which may yield a more reliable

and lighter-weight system.

e. Vehicles 

(1) . High-Energy Second.Stage

The development of an optimum size. second stage

rocket usingaliquid-hydrogen liquid-oxygenpropulsion should be initiated.

This development would provide a vehicle stage for use in delivering very

large ballistic or orbital payloads in conjunction with the existing•ballistic

missile. boosters. The proposed missile stage utilizes the same propellants

as the ATLAS-CENTAUR stage which is under development-by NASA. However, it is felt that a. stage of greater simplicity and smaller size will

provide nearly the same payload.and .be more adaptable for operational use

and space research applications. This objective can be accomplished.with

a pressure-.fed. stage which is approximately 50 per cent as large as

CENTAUR.

- WDZR-180

11111MCCORDENTtAt D-12

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(2) Recoverable Boosters

The design development amlydemonstration•of recovery

systems for large rocket boosters should.be initiated as. soon as possible.

Large Payloads require very large rocket proPelled.boo.sterato be developed

and fabricated. in. substantial numbexs. The high expense of this. sine of

booster can. be. expected to become a major. lb:lifting-factor. in the magnitude

of splice raission.effortif.a new booster is required.for.each.launching. .

The development of systems for the recovery of the very large first stage

boosters can be expected to substantially reduce the cost of the. use of very

large vehicles, since..it is readily recognised that the cost of the actual

liquid-propellant. used in eachmisaile.firing is an extremely small portion

of the whole cost. It is possible that the recovery of boosters could.be

accomplished through. the use of drag, rocket propulsion energy, airbreathing engines,, parachutes, or controllable. lift. In general, the

technology necessary for the design evaluation-of each of the above techniques

is: fairly wellin.hand, with.the exception. of the lapt technique involving the

use of controlled hypeisonic: lift. Further research- and experiment in tir_s

area. of technolOgy will be required. When this. technical information.is

available the.integrated design of a recoverable booster system• could be

intensively studied.. This should. then be. followed`. a development and

flight demonstration program.

Ground Support 

. Design studies and conceptions should be. developed for

launchers and. support systems for use with very large chemical rocket.

boosters. Safety and handling problems.aisociated with the. high energy

propellants that are expected to be used in.the, future systems, shOuld also

be.coneidered.

Large Boosters 

Programs, such as SATURN and TITAN C, for: the development of large boosters should continue in anticipation of large payload

requirements.

WDZR-180

--SECREF--

D-13

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6. Sensors

a. Attitude Sensors 

. Geocentric and Attitude Rate 

Of very vital need at the present time are devices• used

to sense. the local vertical and attitude. deviation. Accurate reconnaissance,

target acquisition, and orbit correction all depend on extremely stable attitude

control of satellite vehicles. Instruments currently available are cumbersome

devices. involving rotating parts and extensive logic circuitry. Equipment

using electronic, optical or infrared techniques for. horizon sensing should

be developed. Of. major. importance are accuracy and noise level, which

should be measured for currently available hardware in the proper. environment.

Heliocentric .

Heliocentric sensors should be developed in order to

orient devices which depend .upon.. solar radiation such as solar energy cells.

These sensors may also be useful. for navigation purposes. • Sensors should

be. developed at infrared and optical frequencies.. Radio frequencies should

also be investigated.

. Low-Drift Attitude. Sensors

An.order-of-magnitude reduction in the drift rate of

gyroscopes is heeded to enable attitude control. during long duration missions,

by conventional all-ineitial means. This could possibly be achieved.by basing

the development of a. gyro on cryogenic, electrostatic, or molecular -effects.

Other principles such as the effect of body rates on standing waves or

vibrating strings should.be considered. A further mechanization of a

drift-free attitude sensor. might consist of using well-known vacuum

measurement techniques to determine the.relative number of molecular

free. space. particles which are. intercepted. by two orthogonal surfaces. In

this. mann er, the. vehicle attitude relative to.its velocity vector. can. be

determined.

WDZR -180

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WDZR-180

D-15

11111P1111r **I toNFIDENTat_

Ver Low Rates

One of the more promising methods for. determination

of very • lOw attitude rater is the stellar:: drift Meter. This device should.be

evaluated, bathes a.rate and as an attitude measuring device. In this regard,

the lechniques. of map reading or map matching may prove applicable.

Detection. of dark satellites by means of relative/notion requirea•techniques

similar to those. used in.measuring stellar drift: . Measurement of lateral

ground. velocity, is necessary for certain lunar missions.

• Electromagnetic • Attitude Measurement 

The possibility of determining space. vehicle attitude

.from vehicle electromagnetic radiation patterns has been.proposed•in several

forms. These should. e evaluated.for possible use for attitude monitoring.

b. Position-Sensors

.(1) . Detection 

Devices are required to detect satellites or. re-entry

vehicles at long ranges, and. under a variety of environmental conditions,

for satellite interception, warning, and anti-ICBM programs. Radar,. radio,

. infrared, and .optical techniques should.be considered. Methods of extracting

guidance and. control signals.from such sensing devices need to be developed.

High Resolution

The use of space vehicles to determine the position of

ground installationeduring reconnaissance or. early warning .missions requires

some form of extremely high resolution sensing, and very accurate control of

vehicle. body rates. The high resolution.photography techniques should be

. investigated, either: separately or combined with.attitude.senaing.

• Weather Reconnaissance 

Weather satellites• will require simple, lightweight,

low-resolution sensors and data transmitters for cloud.cover reconnaissance.

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Acceleration Sensors 

The development of accurate acceleration . sensors is .

required to enable the development of more accurate inertial guidance and

navigation. systems. For such systems.position.cornputations are based upon

attitude. measurements and acceleration measurements.

Other

Developments are needed in every type of instrumentation

to make devices useful in space applications.

7. Components, Packaging, and Environmental Test

a. Components

.(1) High. Frequency Transistors

There is a need for- high frequency transistor. which

can operate above. 1000 "megacycles/second.output, from low power. levels

to. power levels of the order of many watts.

(i) Digital Control System Components 

The use of digital computers for missile control as well

as guidance. has many advantages. However, complete integration requires

a..number of digital-analog devices not currently at the required.state of

development. A transducer which. can measure engine angle and provide a

. direct digital signal is desirable. In addition, a hydraulic or pneumatic

valve which accepts a digitally, coded signal would simplify the over-all.

system. Both of these components require development to meet missile

system requirements.

(3) Bearings for Space Environments 

Of particular importance in meeting the space environment is the vacuum bearing problem. At the present time, inadequate information. is available. regarding the effects of vacuum on bearing surfaces or

how to overcome the problems due to lack of lubrication, vacuum soak, and

. surface. sputtering. Life tests on specially designed.bearings should.be

performed in simulated space. environments.

WDZR -180

D-16

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WDZR-180

D-17

(4) Command Controlled Miniature Integrating

Accelerometer

A miniature integrating accelerometer unit capable

of accepting "start"; "reset", and "velocity to be gained" commands is

necessary for missions having vehicle stages which do not demand full

inertial guidance capability and for which direct radio control of cutoff

is inconvenient. Such commands could be generated from the ground or

from the previous stage.

b. Packaging 

(1) Lightweight Control System 

Ultra-lightweight minimum size equipment for

guidance and control of space vehicles should be developed. It should

have the capabilities of being programmed throughout the vehicle

trajectory. It should also have automatic course correction capabilities

for use of an astro-navigation device.

• Electronic Equipment Microminiaturization 

Studies should be conducted to apply microminiaturization to electronic assemblies. This should include the employment

of techniques of thin films, single crystals and molecular structures .to

complete systems of electronic circuitry. • This would permit • the inclusion

of high performance control. and data systems in.missile and satellite

payloads.

Application of Tunnel Diodes 

Intergranule Corrosion Control in Aluminum 

and Magnesium Alloys 

Deposition of Thin Films for Plasma Jet Techniques 

High Performance Rocket Nozzles Requiring less

Rhenium 

Ultrasonic Welding. Techniques 

(8) Methods of Production of Ultra-pure Metals

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c. Environmental Test

. II) Flight Tests 

The effect of rocket launch and space environment on

the reliability and performance of specific. missile components should be

evaluated at every opportunity in.order to decrease the failures of these

components when subsequently used in system development flight tests. This

type. of test is suggested as a.part of the advanced THOR-ABLE series, but

should also be done as "Piggy-Back" tea s on ICBM flight tests• and new stage

development .flight tests.

(2) Space Environmental; Laboratory

In.order. to shorten the development time of hardware

items for space application, facilities for limited simulation of zero gravity,

radiation.pressure, meteorite impact, ionization levels, etc.. as found in

space, would be. desirable.

8. Biology

Design, development, and demonstration of various equipment

and conceptions necessary to integrate.men into the space missions structure

is required. It is suggested that present investigations now underway be

extended and additional studies be instituted in the area.of mannedenvironmental subsystems, data.displays, control system inputs, and

mission integration. Special consideration should be given to the .function

that a man would perform in a. missile system and the effect that the

availability of man's capabilities might have on the basic design of the

missile system. One promising consideration is the very wide range of

equipment performance redundancy that can be.provided by a man because

of the tremendous adaptability of his mental processes.

B. Research Projects 

I. Communications 

a. Improvements in. Channel Capacity

WDZR - 180

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illiteoffifeaw

11). Coding

The capacity of a communication channel to transmit

information is affected.by received.signal power, system bandwidth, and

noise level. It is necessary to increase the capacity of communication

channels in actual systems to more.nearly approach the.theoretical lirni:.

Coding is one method.of increasing the capacity of a channel • At thepresent

. time coding techniques which enable a. system to approach the theoretical

limit of capability are very complex and unreliable. • It is required that

. these optimum coding-techniques be simplified and made more reliable.

(2) Narrow Banding.

kesearch.is required.in order: to . extend the state-of-

.

the-art in narrow banding techniques. • While still permitting the narrow

band.width.techniques required.for low signal to noise, methods. must be

devised for obtaining fast acquisition. as required.in guidance, tracking,

and communications.

(3) Detection in Noise

• Techniques • are required for. increasing information

. rates used. .for. communications and telemetry above those•presently possible.

Present techniques for resolving signals in the presence of noise,. limits our

information to rates which are less than desired.

(4) Noise

Research.is required to obtain.other new techniques

for improving signal-to-noise. ratio.

b. Propagation 

(1) Ionosphere

There are many propagation phenomena characteristic

of the ionosphere and its tenuous outer extension which are only very

imperfectly known at the present time. Work in this field 'should be pursued

vigorously. This is of special importance.to guidance systems and cornmunication systems.

WDZR-180

MIR CONFIDEMt

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WDZR-180

D-20

.(2) . Troposphere

Continuing research work is required on the propagation

phenomena.of the troposphere. This region. is currently responsible for some

of our worst precision radio guidance problems.

Solid and Exotic Propellants

Further research work Is required in connection with

the. effects of the.loading of solid.propellants with.metals such as aluminum

and lithium on.radio propagation through the missile flame. • For example,

it would prove embarrassing to discover that a radio guidance system

developed for a specific. solid propellant vehicle could not be used.because of

excessive. flame attenuation. The same type . of problem arises, potentially

at least, in.connection with exotic.liquid fuels.

Radio Scintillations

New radio scintillatibn data.from radio astronomical

as well as satellite signals. should be subjected to statistical studies, using

improved methods o£ statistical inference. Complementary theoretical studies

of e. m. propagation by fluctuating media should be carried•out. The over-all

objective is to gain improved.information.about the size, shape, orientation,

motions and stability of ionospheric irregularities which cause amplitude

andphase scintillations in radio waves.; and thereby introduce a.natural

limit to tracking accuracy.

• (5) Plasma

The transmission.of high powered signals through

weakly ionised plasma is a nonlinear problem which has characteristics

quite different from that of weak signals. Strong low .frequency signals can

modify a plastna..suCh.as the. missile exhaust so as to reduce blackout and

.phase. shifting. Applications to the powered, as well as re-entry, phase of

flight should be investigated. Electromagnetic propagation experiments and

actual, equipment evaluations.. can be planned as Piggy-Back experiments on

existing rocket.firings, as-part of a re-entry test vehicle program, and.by

special rocket firings as required but available. in:.other programs.

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(6) . V. L. F.

Very low frequency radar cross sections should be

evaluated to. estimate .feasibility of missile detection in the. powered phase

from magnetically conjugate . points on the surface . of the-earth. The detailed

propagation. of V. L. F. through nonisotropic plasma its well as V. L. F.. noise

background in.the upper atmosphere is under investigation and will continue.

Since this noise.background is directly related.to the. Van Allen.Belt high

speed electrons, considerable. activity on satellite radiation.bialt measurements- should comprise part of this progtam. V. L. F. propagation theory

is also extended to frequencies which are. less than the gyro frequencies of

the protons.

c. Secure Communications

Secure communications techniques require extensive

research.work, aathere are a number: of basic-problems outstanding, of

which. the. most difficult is probably the. synchronisation problem.

2. Computers and Control 

a. Control

(1) Thrust Vector:Control by Gas Injection 

•

• Methods of thurst vector control which require no

heavily loaded moving paits are:desirable. One suchmethod, which as yet

has not beenfullyinvestigated, employs gas injection normal to the. thrust

cone. walls- to cause controlled separation with a.rasultant controlled change

in. thrust vector direction: A development of a.thrust vectoring system is

necessary before. the. Method can .be evaluated.

(2). Adaptive Control •

A definite need exists for control systems for ballistic

missiles. which 'are .truly self -adapting . to changes. in. missile system charac-

.

teristics and-flight environment. Recent advances in the.fleld of adaptive

control theory have promise; however, a.need.exists for a .concentrated

effort to determine adaptive control techniques directly applicable.to ballistic

missile. control. In addition, • such. techniques may be . required for. control

during a. controlled re-entry.

WDZR -180

D-21

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WDZR-180

D-22

19) Torque•Producing Devices 

Development of torque producing. devices for changing

the .vehic.le•attitude Is currently centered around reaction wheels and low

thrust jets using stored gas, monopropellants, or bipropellant.fuels. Larger

torqueranges and Improvements in. dynamic performance are required. Other

approaches such as solar sails or. magnetic controls should be investigated.

For low altitude vehicles, aerodynamic force may prove.usable. The investigation.of control techniques must. of course be. closely allied with physical

measurement''• in the space. environment.

Nonlinear. Control Systems 

On-Off (maximum effort) control systems are presently

used for. roll control. during powered.flight and-for attitude control of space

vehicles. Howevera, such.nonlinear methods have not been, successfully

applied .to pitch or: yaw control of large. ballistic missiles 'during powered

flight. • It would.be highly desirable to investigate methods of control similar

to the maximum effort type for the powered.. flight application. Such methods

hold promise-of simplification, increased reliability, reduced weight.

Missile•Dynaznics 

The dytuunic : behavio• of ballistic missiles during

powered flight is still not completely understood. A need exists for additional

. study of the. dynaniics of liquid propelled ballistic:missiles where the .fuel

sloshing.frequencies and body bending frequencies are close together.

(6) . Sloshing in Free Fall 

Requirements for coast period during the powered flight

phase introduce problems associated talth.thebehavior of liquid in the fuel

tanks during.free.fall. The dynamic effects of liquidluel motion during .free

fall must be. determinedin order that attitude control systems for the coast

period can be designed.

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WDZR - 180

D-23

b. Computers,

(1) Computer Simplification 

The current state-of-the-art requires vast computer

facilities. for performing relatively simple guidance function in launch,

midcourse and terminal phases. It is required.that studies be made to deter-

. mine simple forms of guidance equations for special purpose missions where

low information rates are required.

3. Guidance and Tracking

a. Guidance 

Sensors 

New and more accurate sensors are required, for

. determining position and attitude. Studies should .be. made to determine

more accurate techniques for obtaining data utilizing . radio, radar, optical,

infrared, and inertialtechniques and. combinations thesctechniques.

Terminal Guidance . Techniques 

Accurate methods are required for. terminal guidance

in order to accomplish missions with a high.degree of accuracy without

placing "extremelysevere requirements upon launch. guidance, midcourse

guidance, and propulsion.

Midcourse Guidance •Techniques 

Accurate midcourse guidance techniques are required

An order to accomplish missions requiring a high degree of accuracy without

placing. an undue burden upon propulsion, launch guidance, and terminal

guidance. Studies are required to evaluate the relative advantages of control

from the vehicle with control from. the ground.

• Noainertial Attitude•Sensors

Radio Attitude Sensing Systems , and other •noninertial

Methods should be studied.

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413-24

(5) Radio Guidance 

Research work is required for highly accurate, wide- .

base radio guidance systems.

1.6) , Secure Guidance 

Extensive research work is required in secure communications and anti-jamming .techniques. for effective military radio guidance

systems.

Doppler-Inertial Guidance• Systems

Careful. study of the. relative.merits of various possible

combinations of Doppler and.inertial equipment is needed. Among the important criteria are accuracy,. reliability, flexibility and cost.

• New devices such as cesium-beam and gas-cell frequency

references are promising, but considerable.theoretical study, exploratory

laboratory study, and. engineering development are needed.. Some •components

requiring special study are crystal oscillators, spectral lamps, and interaction

cells.

Improvements. of methods and equipment by which the

stability of frequency references can be measured are needed.

An investigation. is needed of errors caused by variations

of the time .of transmission of radio waves. through.missile flames of various

types.

System Simplification

It is required that studies. be made to reduce the complexity and weight•of guidance systems. In this regard.the studies should

evaluate the-use • f simple .radio and inertial combinations.

(9) CEP Improvement Research

There is a.need foi a strong research program to

investigate the over-all problem of CEP reduction. In the immediate sense,

such programs exist. in the various. ICBM weapon. systems, but there . currently

exists no long-range program.of this nature.

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b. Tracking 

. Fast Acquisition 

Research is required to obtain new methods for fast

acquisition of targets. With present techniques the acquisition time is

inversely proportional to the square of the communications bandwidth. Therefore, as t*e bandwidth is made narrower . to improve the• signal-to-noise ratio,

the acquisition time increases considerably.

Computer Accuracy

For the purpose of precise determination of orbits it is

required that studies be made to obtain more accurate computation programs,

especially with regard to integration.

Location of Ground Stations 

Accurate tracking of satellites is contingent upon an

accurate knowledge of the location of the ground stations which perform the

tracking. Studies are required to determine methods of measuring the

position of ground stations more accurately through.tracking of satellites.

. Data Reduction

. Studies are required to determine the optimum

smoothing of .data in order to obtain the. best estimate of measured quantities.

(5) Secure Tracking 

Research.is required to devise techniques for secure

tracking systems which are capable•of operating in the presence of counter-

. measures.

C. Flight Mechanics

(1) Trajectories

Studies are required to determine methods of trajectory

• selection for maximum performance. Optimum computation techniques must

be devised for selecting pitch programs which consider the constraints of the

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WDZR- 180
propulsion system and of vehicle heating. Computational techniques must

also be devised to obtain optimum steering in yaw which complies with the

range safety and the propulsion system requirements.

(2) Satellite Orbits 

The basic properties of satellite orbits must be studied

in order to determine precise trajectories. The effects of the various

perturbing forces must be known more accurately. Detailed results must

be determined for special satellites which require precise orbits.

d. Physics 

Re-entry Physics 

The optical, infrared, and radio character of the

re-entry wake should be established. Its passive appearance (how it looks

over. the entire frequency range) should be studied. In addition, radio propagation (including the V. L. F. range) aspects should be analysed. In

particular, 'radar cross sections of the wake for various aspect angles

should be. estimated.

Geophysics 

Determination of geodetic and gravimetric information to greater accuracy for high accuracy systems.

Research on upper atmospheric wind and densitir

fluctuation to be continued for higher accuracy systems.

(c) Geophysical environment parameters should be

determined to far better accuracy than now known. For instance, the

radiation levels should be known in all portions of space surrounding the

Earth, the energy and type of radiation should be known, the effects of solar

activity on this radiation may be very important.

(3) Geodetic Requirements 

Refined studies of the effects of geopotential fluctuations

on long-range trajectories should be carried out.

WDZR-180

D-26

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e. • Propagation 

The propagation research mentioned as being necessary

for communications in paragraph . VII B lb is equally applicable to both

guidance and tracking.

4. Power

Research.on systems for conversion of solar, heat, or nuclear

energy to usable electric power must be stepped.up in order to meet the

increased electronic requirements of satellites. The following laboratory

projects should be initiated.

Photovoltaic Converters 

Continue research on semiconductors to improve efficiency

and lower cost of solar cells. Invifstigate novel methods of obtaining p-n

junctions in large area devices and.fabricate units with multiple junctions.

Study photoluminescence as'a possible method of energy storage.

Thermionic Conversion 

Thermionic diodes have been.used su.ccessfullylor conversion of heat to electric power. Possible efficiencies are higher than those

..for thermoelectric or photovoltaic. conversion. Considerable research is

needed to arrive at practical thermal and mechanical designs. The possibility

of using grid. structures or split anodes• for direct conversion to chopped.d-c

or a-c voltages should definitely be pursued.

•c. Exotic . Heat Engines 

More advanced heat engines which • can provide rotornotive

as well as electric.power will be required for certain. satellite operations.

Research on items such as mercury vapor pumps and partial admission

turbine4, should. be intensified.

d. Thermoelectric Conversion 

Research on materials which exhibit large. thermoelectric

effects should continue in . support of the design.of thermal conversion

.systems.

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Basic research.must be performed now to ensure that

sufficient power can be made available aboard space vehicles so that ionic

propulsion or intense electromagnetic countermeasure techniques can be

implemented.

5. Propulsion and Vehicles 

a. Thrust Chamber 

Injector Development 

Continue basic investigations of combustion. stability

with storable and nonstorable propellants.

Nozzle Configurations

Investigate analysis and design of nonconventional

nozzles.. This should include experimental investigations, if analytical

studies show promise. The systems to be considered shotild include both

the Spike or Plug Nozzle and Unconventional Bell Nozzle (with large

expansion angles).

(3) Uncooled Thrust Chambers

Develop uncooled thrust chambers for use in high

energy and storable liquid propellant engines; and perform research on novel

schemes of designing uncooled thrust chambers. These should include

investigation of the heat-sink method of absorbing the heat for the rocket

engine nozzle.

b. Turbopump Systems 

Cavitation Performance

Investigate cavitation performance of pumping systems

in various propellants. Develop scaling laws to predict cavitation performance in various propellants from water tests.

Design Concepts 

Analytical studies should be directed towards unconventional, new design concepts for turbopumps.

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(3) Hydrogen Fuel 

Analytical and experimental studies should be made of

pumps suitable for large chemical or nuclear propulsion systems using

hydrogen fuel. Studies should include investigation of optimum turbopump

design (centrifugal, mixed-flow axial or hybrid) from the standpoint of

performance, weight, and development timer and cost.

Integration of Components Into Systems

Development efforts to permit system simplicity and

improved reliability through elimination of components, etc. , of present

propulsion systems.

Propellant Research

Investigate storable propellants, high energy propellant

additives. This should include calculation for performance of new systems

and consider capability of propellants with present and future systems.

e. Solid Propellant Research 

Metal Additives 

Investigate combustion of metal additives such as

aluminum, magnesium, berylium, and lithium in the propellant grain.

Studies should include theoretical and experimental investigations.

Solid Propellants

Study solid-liquid hybrid systems—investigate improving

the performance and thrust control of present day solid propellant systems by

the addition of a liquid oxidizer.

f. Liquid Propellant Research 

(1) Investigate catalytic phenomena relating to monopropellant

systems.

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Investigate the kinetics of dissociation and recombination

of free radicals in rocket nozzles. High energy systems, solid propellant

systems, and nuclear monopropellant systems should be investigated.

Investigate the physical and chemical properties of the

many liquid propellants of interest for advanced, high energy systems.

g. Aero-Thermodynarnic•Research 

Heat Transfer

Heat transfer investigations related to rocket propulsion

systems. These include studies necessary to derive basic information on

particle phenomena in nozzle flow and ablation phenomena in =cooled thrust

chambers.

Radiation Properties 

Study the radiation properties of rocket • engine exhaust

gases in order to determine their effects on infrared and. other similar trackers.

This is of great importance in SAINT and AICBM missions.

(3) Fluid Mechanics Studies 

Perform ro.agnetogasdynsunics-theoretical studies

relating to the containment and shaping of the flow of high temperature gases.

These studies should also consider selected thermoelectric energy conversion

devices and the containment of the high temperature nuclear plasma gases, and

the study of high temperature fluid dynamics problems associated with the

advanced nuclear rocket systems.

h. Advanced Propulsion Devices

Investigate low-thrust ion, plasma; and solar cell

devices for velocity and attitude control and orbit keeping in space.

• Design Evaluation• Studies 

Perform design evaluation studies of large solid propellant engines to assess feasibility and practicability of this type system for

various Air Force booster missions.

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Mr-coNFIDE-mtSupport. Studies 

Support studies should be initiated or continued to

indicate the areas of application and feasibility of various advanced propulsion

systems. They include:

Electric Propulsion Systems

Plasma Propulsion Systemd

Solar Propulsion Systems

Other Exotic Systems

Low Thrust Systems 

Low thrust chemical propulsion systems for satellite

applications are also apromising area for research.

i. Pressurization Systems 

Develop a lightweight pressurization system for space

vehicle applications. These should have long storage capability and be

operable under zero-g conditions.

. Nuclear Demonstration System 

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k. Decoys

There is a strong requirement on aerodynamics to create

a decoy vehicle which will duplicate the radar cross section, the re-entry

trajectory, and the same ionized wake as the nose cone. Such a decoy

needs to be developed.

1. Communications 

Aerodynamic shape choice can greatly affect the problem

of terminal trajectory communication through the ionised shock and boundary

layers. Techniques and hardware to ease this problem must be developed.

Aerodynamics

The studies and tunnel tests of re-entry shapes should

continue, especially in the newer fields of maneuverable re-entry.

Magnetohydrodynamics 

The application of this field to flow problems about the

re-entry body requires both analysis and hardware development. Its

potentialities are very great.

6. Sensors 

A study should be made of exotic, or improved gyroscopic

devices and accelerometers. Provisions should be made to exploit any

breakthrough in concept, materials, etc. In addition, promising work

currently underway should be continued.

7. Structure

a. Weight Reduction

An intensive investigation should be initiated into weight

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saving design techniques. For the foreseeable future, payloads will be

weight-limited and a critical examination of standard electronic and

mechanical equipment designs should prove extremely valuable. Particular

attention should be paid to mechanical joints, webs, and fillets, and to the

interface between electrical and mechanical portions of the payload.

( i) Pressure Vessel Design Criteria Development 

Determine material selection and design criteria

for high efficiency pressure vessels, including the effects of multi-axial

stress fields, stress gradients and discontinuities on the effective strength

of high strength materials for pressure vessel. applications.

Development of Design. Criteria for. Elastic 

Instability of Thin Shell Structures 

Determine the buckling strengths and characteristics

of certain stiffened. and =stiffened conical and cylindrical shells; including

the effects of combined loads and internal pressures.

Vibrational. Characteristics of Solid Propellant 

Rocket Engines 

Determine the structural dynamic interactions of

solid propellant case, including the modes and frequencies, effective

masses, and damping..

High Velocity Impact and Penetration Phenomena 

Investigate high velocity impact and penetration

characteristics of small pellets impacting on varioup structures.

Structural Characteristics of Composite Structures 

Determine the strength, stiffness, and instability

characteristics of layered. and composite shell structures under various

loading conditions.

(6) Structural Capabilities of High Strength Alleys 

Metallurgical investigation of solute distributions in

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high strength alloys, and determination of their relation to the motion of

dislocations in the alloy should be performed, in order to understand and

exploit the structural capabilities of nominally high strength materials.

Thermal Stresses in Rocket Nozzle Shapes

Measure stresses in the two-dimensional thermal.

stress field of rocket nozzle structures and correlate with theory.

Shock

Shock Gauge . Development 

Continue the development of shock gauges for

measuring ground shock characteristics.

Ground Shock Characteristics 

Physical measurement of ground shock characteristics in various soil . conditions for nuclear or high explosive blasts

should be performed as a part of hard base site evaluation studies.

Wave Propagation in Non-Linear, NonHomogeneous, or Layered Media 

Experimentally investigate wave propagation

characteristics of non-linear, non-homogeneous, or layered media,

perhaps including soils, and correlations with theory.

Response of Structures to Excitations by

Wave Propagation is Continuous Media 

Measure the response of structures contained

within. or attached to continuous media when excited by waves propagated

within the media, and determine the resulting changes in wave propagation

characteristics.

(e) Development of Advanced Shock Isolation 

Systems

Develop methods for shock isolation and

protection employing advanced concepts and techniques, perhaps including

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(a) Experimental-Investigation of Sloshing 

Continue and extend present studies in fluidsloshing characteristics to understand fluid slosh coupling with flexible

tanks, and sloshing control.

8. • Components, Packaging and Environmental Test

Space Environment Data 

Space vehicles, either earth-orbiting or probe type, must

fly thiough distrubances arising . from a variety of physical phenomena.

Among those which are most obvious are solar radiation pressure, gravity

gradient effect, and magnetic torques. At the inception of the ballistic

missile program, extensive work was conducted to evaluate• the wind pro-

.

file so that missile designers would have a design criteria. A similar

effort is now needed to evaluate the physical phenomena whiCh will influence space vehicle design criteria (one of the more important being the.

effect of these disturbances on attitude control).

Hyper-Environment Investigations 

The effect on the surfacing and thin films of materials

as a, result of nuclear, radiation, ultra-high temperature and combinations

of these under vacuum, should be examined.

This should include examination of the electrical, as

well as physical, properties of the materials resulting from high intensity

exposure rather than the long duration exposure to these environments.

c. Valves

Development of valves for space vehicle applications

requires basic research. These components must have long life storage

capabilities in space, minimum response time, minimum electrical power

consumption, and be capable of operation under zero-g conditions.

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9. Materials 

a. Crystals 

A fundamental study should be conducted on the properties

of crystals and methods of growing large ultra-pure single•crystals of

organic and inorganic materials under discovering properties useful in

electronic' equipment design. This is essential for progress inmicrominiaturisation.

b.• Surface Chemistry 

33asic studies of surface chemistry of organic and

inorganic material, should be conducted with particular investigation of

the electrical properties of their surfaces.

Shielding 

Lightweight shielding material for protection against

nuclear radiation is needed for microminiaturised electronic equipment.

Thermochromii

Thermochromic coatings are needed for controlling

temperature of space vehicles.

"Whiskers"

The properties of fibers and "whiskers" of organic and

inorganic materials should be explored in a search for super strength,

high heat-resistant flexible materials, leading to reduced weight and high

performance of devices in which these could be applied.

Propulsion Applications

Investigate the compatibility of materials with various liquid

propellants.

Investigate ablation properties of various materials when used •

in rocket engine nozale.

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9. Materials 

Crystals 

A ftuidamental study should be conducted on the properties

of crystals and methods of growing large ultra-pure single crystals of

organic and inorganic materials under discovering properties useful in

electronic'equipment design. This is essential for progress in microminiaturisation.

Surface Chemistry 

Basic studies of surface cheznistry of organic and

inorganic materials should be conducted with particular investigation of

the electrical properties of their surfaces.

C. Shielding 

Lightweight shielding material for protection against

nuclear radiation is .needed for microminiaturised electronic equipment.

Thermochromic

Thermochroznic coatings are needed for controlling

temperature of space vehicles.

"Whiskers"

The properties of fibers and "whiskers" of organic and

inorganic materials should be explored in a seaich for super strength,

high heat-resistant flexible materials, leading to reduced weight and high

performance of devices in which these could be applied.

f. Propulsion Applications

Investigate the compatibility of materials with various liquid

propellants.

Investigate ablation properties of various materials when used

in rocket engine nozzle.

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9. Materials 

Crystals 

A fundamental study should be conducted on the properties

of crystals and methods of growing large ultra-pure single . crystals of

organic and inorganic materials under discovering properties useful in

electronic equipment desIgn. This is essential for progress in microminiaturisation..

Surface Chemistry 

Basic studies of surface chemistry of organic and

inorganic materials should be conducted with particular investigation of

the electrical properties of their surfaces.

4. Shielding 

Lightweight shielding material for protection against

nuclear radiation is needed for rnicrominiaturized electronic equipment.

Thermochrcnnic. 

Thermochromic coatings are needed for controlling

temperature of space vehicles.

"Whiskers" 

The properties of fibers and "whiskers" of organic and

inorganic materials should be explored in a search for super strength,

high heat-resistant flexible materials, leading to reduced weight and high

performance of devices in which these could be applied.

f. Propulsion Applications

Investigate the compatibility of materials with various liquid

propellants.

Investigate ablation properties of various materials when used

in rocket engine nozae.

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Investigate the methods of coating materials with refractories.

This information will be directly applicable to problems

associated with the development of uncooled thrust chambers.

Investigate material properties at cryogenic (hydrogen) temperatures and also at the very high temperatures associated with

high energy chemical systems and nuclear systems.

(v) Investigate nuclear radiation effects on rocket engine components

and propellants.

Materials for Cryogenic Applications

Conduct mechanical strength and ductility investigations

at temperatures below 100°K to provide information for low-temperature

applications.

b. Material Surface Property Requirements for Space 

Environment

Investigate emissivity and absorbtivity throughout the

spectral region as a function of surface conditions; stability of such

surface characteristics in the space environment.

i. Physical Properties of Materials for High Temperature 

Applications 

Determine refractory, ablative, sublimative, insulation

and strength properties of advanced alloys and non-metallic" to meet the

strength, thermal shock, and erosion requirements of manned re-entry,

propulsion, and other extreme temperature applications.

J. Kinetics of Solid State Transformations

Determine the kinetics of crystal structure transformations in superconductors, semiconductors, intermetallics, and metals

to provide increased capabilities of materials in specific present applications and develop improved materials for future applications.

WDZR-180

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Radiation Effects in Solids 

Investigate the effect of high energy particle radiation

on the useful life of serniconductors and solar cells, as well as development of improved radiation detectors and nuclear auxiliary power

supplies.

1. Physical Properties of Materials in Space Environment 

DeterMine the effects of space environment, includinE

high vacuum and radiation, on strength and other physical properties of

structural materials in an attempt to determine their most effective use

in the space environment.

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