•

LMSD-414889

JANUARY 1919

Not LOGGED

t

EXCLUDED FROM

DECLASSIFICATION W E.0.1295$

••n

• DISCOVERER

SENTRY

MIDAS

SATELLITE DEVELOPMENT PROGRAMS

CONTRACT AF 04 (647)•97

!An si:t

no

j0;

wItIGRADED Ar 

32 YEAR 'ALS; 

.1; • DECLASSIFIED. 

COO

5200.10

a syllabus prepared by

LOCKHEED AIRCRAFT CORPORATION

MISSILES AND SPACE DIVISION

SUNNYVALE, CALIFORNIA WbS 9 - 1 0 8 9 •
LMSD-414889 NOT LOGGED

COPY WAN? 

conE.NTIAL

This syllabus summarises the basic concepts and the current state-of-development of the DISCOVERER, SENTRY, and MIDAS programs as presented in a

joint Air Force - Lockheed briefing to the National Aeronautics and Space Administration on 20 Jaimary 1959.

The Lockheed Missiles and Space Division is responsible for the management of

these related -- but distinctly separate -- satellite development programs in its

roll as the Systems Contractor.

' LOCKHEED AIRCRAFT CORPORATION

Missiles and Space Division

Sunnyvale, California

January 1959

• This sksvotost contains leferesenee effeefhto the settees' defense of the Ualtesi States within

Sbo meemblip of the Espl000r Lows, nti. IS, U. S. C. See. M owl 714. Ks fromunissien or

the toveloffee of ifs seeteefs is soy wow to es unauthorised person is prohibited by low.
LMSD-414889

SECTION I - INTRODUCTION

SYSTEMS EVOLUTION

Initiation of the development phase of the programs presented herein repre-

.

seated the culmination of a series of intensive Air Force-sponsored studies

and analyses dating from the immediate post-World War II period.

A General Operational Requirement (GOB. 80; SA-2C) for a *satellite-based

reconnaissance system was established by Air Force Headquarters in March

1955, followed in August 1956 by the publishing of a. related Development Plan

and a Development Directive. Overall responsibility for the development program was assigned to the Western Development Division (subsequently redesignated as the Ballistic Missiles Division) of Headquarters, Air Research and

Development Command, and, in October 1956, the principal development contract was awarded tb Lockheed's Missiles and Space Division.

Following the creation, in February 1958, of the Advanced Research Projects

Agency in the Office of the Secretary of Defense, direction of the development

program - and its funding - became an ARPA responsibility.
LMSD-414889

Prior to January 1958, it was planned that all satellites would be boosted to orbital

altitude by the use of Atlas (SM-65) missiles. However, a series of measures, as

follows, was taken during that month to both accelerate and augment the development program: •

A DX priority was assigned.

The initial flight test date for Atlas-boosted reconnaissance satellites

was moved forward by approximately one year, and additional flight

tests were schedule& This portion of the program was assigned the

popular name. "Sentry".

A number of Thor (SM-75) IRBM missiles were allocated for booster

purposes. This Thor-boosted series of satellites was subsequently

assigned the popular name, "Discoverer".

That portion of the Sentry program which had been concerned with the development of satellite-borne infrared detection systems has been assigned the distinctive designation, "MIDAS" (Missile Defense Alarm System).
LMSD-414889

_4041RENTIAL__

The chart opposite indicates the evolution of development concepts from the original

relatively straightforward Advanced Reconnaissance program, involving electronic

. data- readout systems, to the most recent Development Plan which provides for three

essentially separate and distinct programs:

DISCOVERER

SENTRY

An electronic data-readout reconnaissance system

A system for physical recovery of reconnaissance data

MIDAS

The characteristics of each of these programs are presented in sections which follow.
UM-414889

PAYLOAD RECOVERY DISCOVERER

PHOTO. FERRET. INFRARED

ELECTRONIC READOUT SYSTEMS

PROGRAMS

DISCOVERER

RECONN. PROGRAMS

RECONN.

RECOVERY •

SENTRY

RECONN. READOUT

ADVANCED RECONNAISSANCE SYSTEM I ARS)

•

1956

SENTRY

MIDAS

1957 1958 1959

r iv:LA r, rit m •
LMSD-414889

LMSD PROJECT MANAGEMENT STRUCTURE

Under the direction of the Corporate Vice President and General Manager of the

Missiles and Space Division, Lockheed has established an integrated weapon system-type organisation for program management purposes. This organization is

designated as the "XA Weapon System. "

There are five Management divisions, as follows, within the XA Weapon System

organisation:

Planning - responsible for establishing major development

milestones and plans for the overall development program;

Development - responsible foi the design and development

of subsystems and associated hardware, as well as for their

integration into a functioning weapon system;

Reliability - responsible for assuring the high functional

quality of the weapon system;

Test and Operations - responsible for the in-plant and field

tests of the system, as well as for the provision of facilities

and the QPRI documentation; and

5. Program Administration responsible for detailed budgeting

and scheduling.

6

*114111111111•
Lina•414889

All functional organizations of LMSD, as well as those of the entire Lockheed corporation.

support the XA Weapon System organisation as required for the furtherance of the development program. Prominent among these support groups are extensive research

laboratories, manufacturing and testing organisations and facilities, and quality control.

VICE PRES. AND GENERAL MANAGER LMSD I

XA WEAPON SYSTEM MANAGER

ASSISTANT WEAPON SYSTEM MANAGER

I I I RELIABILITY MANAGER DEVELOPMENT MANAGER TEST MANAGEMENT PROGRAM

ANC OPERATIONS ADMINISI MANAGER TRATION

MANAGER

I

PLANNING MANAGER

VEHICLE DEVELOPMENT

SUBSYSTEM DEVELOPMENT

SYSTEM INTEGRATION

DEVELOPMENT OPERATIONS

SYSTEM TEST PLANNING

VANDENBERG AIR FORCE BASE

TEST OPERATIONS

REMOTE STATION OPERATIONS

LOGISTICS AND BASE SUPPORT
PRINCIPAL SUBCONTRACTORS

The principal subcontractors selected by Lockheed are listed on the accompanying

chart. Donal-wise, this subcontracted effort accounts for roughly SS percent of

total contract costs. Chief among these subcontractors are:

Bell Aircraft Corporation

Eastman Kodak Company (and its subcontractor, CBS Laboratories)

Airborne Instruments Laboratory, Inc.

Aerojet-General Corporation

Philco Corporation

General Electric Company

Associate contractors having a significant role in the development program are

also listed.

8
LMSD- 414889

PRINCIPAL. SUBCONTRACTORS 

PROPULSION,

SELL AIRCRAFT CORP.

AIROJET-GENERAL CORP.

AUXILIARY POWER 

SONOTONE CORP

EAGLE-PICHER CO

NGINEERED MAGNETICS

HOFFMAN ELECTRONICS CORP.

EECHCRAFT R O D INC.

GUIDANCE AND CONTROL 

DETROIT CONTROLS CORP.

REEVES INSTRUMENT CORP

MINNEAPOLIS-HONEYWELL

REGULATOR CO.

BENDIX AVIATION CORP.

=Mk

EASTMAN KODAK CO.

COLUMBIA BROADCASTING SYS

SPICA INC.

AMPEX CORP.

,FERRET

AIRBORNE INSTRUMENTS LAS,INC.

HALLER. RAYMOND St BROWN INC.

MIDAS

EASTMAN KODAK CO.

SAIRDATOMIC. INC.

AEROJET-GENERAL CORP.

GENERAL MILLS INC.

GROUN •SPACIE COMMUNICATIONS

PHILCO CORP.

REEVES INSTRUMENT CORP.

RADIATION INC

• LOCKHEED AIRCRAFT SERVICES,INC

HUGHES AIRCRAFT. CO .

TEXAS INSTRUMENT CORP.

TEST MANAGEMENTS OPERATIONS

AIROJET-GENERAL CORP.

RALPH M. PARSONS CO.

GROUND SUPPORT EQUIPMENT

OTIS ELEVATOR CO.

CONSOLIDATED AVIONICS CORP.

BEMCO INC.

STANDARD MFG. CO.. INC.

NUFFORD CORP.

BIOMEDICAL CAPSULE 

GENERAL ELECTRIC CO.

ALL-ANIEVICAN ENGINEERING CO.

ASSOCIATE CONTRACTORS,

.BOOSTERS AUXILIARY POWER 

DOUGLAS AIRCRAFT CORP.11M-70 THE MARTIN CO.

CONVAIR ASTRONAUTICS (11/• 51 ATOMICS INTERNATIONAL

GUIDANCE AND CONTROL 

INSTRUMENTATION LAB, MIT

GENERAL ELECTRIC CO.

DATA PROCESSING

RAMO-WOOLDRIDGE CORP.
L ► SD-414889

SUBSYSTEM STRUCTURE

For management control and development planning purposes, the Sentry system has

been factored into the ten major subsystem areas as indicated on the chart opposite.

Lockheed is responsible for all research, design, development, and tests in connection

with Subsystems "A" through "H." plus Subsystem "L." Lockheed is also responsible

for:

The development and procurement of all ground support equipment, including

checkout equipment;

The establishment of design criteria and site selection criteria for all launching,

tracking, and communication facilities;

The installation and checkout of equipment and the manning of the above facilities during the R&D phase of the program;

The establishment of Qualified Personnel Requirements Information (QPRI).

Rome Air Development Center has overall cognisance of intelligence data processing,

identified as Subsystem "I."
RECONNAISSANCE SYSTEMS

SEE" VISUAL

sew. FERRET

*Pie COMMUNICATIONS

Mir DATA PROCESSING

EIOMEDICAL RECOVERY

MIDAS SYSTEM

LIASD-414889

SATELLITE VEHICLE

WA° AIRFRAME

SWOP PROPULSION

GPO' AUX. POWER

IIVIr GUIDANCE S CONTROL

FACILITIES

GROUND SUPPORT EQUIPMENT

DATA CONTROL S ANALYSIS
....19,44FIDENTIAL

SECTION II - SATELLITE CHARACTERISTICS

GENERAL CHARACTERISTICS

By definition, the satellite vehicle comprises:

The airframe • The auxiliary power system

The propulsion system • The guidance and control system

The basic satellite presently under

development is 19 feet long and 5 feet

in diameter, and is designed to be

launched by either the Thor IRBM or

the Atlas ICBM. Essentially all principal components, with the exception

of the booster adapter assembly, are

standard and independent of the booster selected for launch purposes. An

exploded view of the satellite and its

adapter assembly is illustrated on the facing page.
RETROROCKET

FAIRING

UAW-414889 .

ADAPTER ASSEMBLY

The nose cap is designed to be jettisoned to expose data-gathering devices (such as a reconnaissance camera lens) located in the nose cone,

-RETROROCKET

DAFT FAIRING

ULLAGE ROCKET

HELIUM SPHERE AND BOOM ASSEMBLY

AFT EQUIPMENT SUPPORT STRUCTURE ASSEMBLY

ELL ENGINE INSTALLATION

ENGINE MOUNTING CONE ASSEMBLY

AFT MID-000Y ASSEMBLY

-PROPELLANT TANK ASSEMBLY

FORWARD FAIRING

FORWARD MID•BODY

ASSEMBLY

FORWARD EQUIPMENT RACK

NOSE CONE ASSEMBLY

NOSE CAP

or "payload compartment. " This removable cone provides approximately 30 cubic feet of equipment volume,

or roughly 35 percent of the total useful space which is available for payload purposes.
RACIAL TYPE RACK MS CUBIC FEET CAPACITY)

"EGGICRATE" TYPE RACK Olt CUBIC FEET CAPACITY)

- A I.

LMSD.414889 •

Electronic equipment racks are located immediately aft of the nose cone

section. Hinged panels provide ready

access to this area after the nose cone

has been secured in place.

Radial-design equipment racks, as

shown in the upper illustration to the

right, will be replaced early in the

program by an "egg-crate" type design, providing both more economical

use of space and easier packaging of

the electronic components.

The midbody section contains nested

lightweight spherical propellant tanks

designed to hold not less than 37.8

cubic feet of fuel (UDMH) and 49. 0

cubic feet of oxidizer (IRFNA) at 63

psi. Fairings are.provided for routing of wiring and plumbing.

Aft equipment beams, surrounding the rocket engine, provide support for batteries,

antenna, pressure vessels, control gas jets, geophysical research instrumentation,

and the propulsion system. Eighteen batteries (8 x 12 x 14 inches) can be carried

here.

14-
APT EQUIPMENT STORAGE

LMSD-414889

Totaling the volume provided by the nose cone, the electronic equipment racks, and

aft equipment storage --- the overall space available for payload purposes is approximately 85 cubic feet.

Attachment of the satellite to its booster is accomplished by use of an adapter section •

which remains affixed to the booster after in-flight separation of booster and satellite.

Separation is initiated by explosive bolts. Retrorockets cause the booster to slow down

in relation to the satellite, resulting in separation of the two stages.

15
A.R•si ENGINE

LMSD-414889

PROPULSION SYSTEM

The satellite propulsion system is comprised of the XLR-81 pump-fed, liquid propellant rocket engine; fuel and oxidizer tanks; pressurisation and vent systems;

helium spheres; and ullage control rockets. Discoverer Flight Test Vehicles 1 and

2 will use JP-4 as the propulsion system fuel; subsequent vehicles will use UDMH

(unsymmetrical dimethyl hydrazine). The oxidizer in both instances is IRFNA (inhibited red fuming nitric acid).

In operation, the propellant tanks are pres-

.

surised by helium, regulated from 3000

psi in the pressure spheres to 63 psi in the

propellant tanks.

Small, solid propellant rockets (the ullage

control rockets mentioned above) are fired

immediately prior to engine ignition in order to orient the propellants in the tanks

and to assure that liquids are at the pump

inlets.

The XLR- 81 engine; manufactured by Bell

Aircraft Corporation, is gimbal-mounted

for thrust direction control.
PROPELLANT FUEL TANK

PRESSURIZATION ASSY. FUEL TANK QUICK DISCONNECT FILLS DUMP

OXIDIZER J OXIDIZER QUICK DISCONNECT FILL G DUMP

. TANK r TURBINE PUMP

GAS CONTROL JETS IQ

ULLAGE ROCKETS 12)

LMSD-414889

Significant nominal performance characteristics of the VD/An-fueled system are:

Thrust

I(minimum)

sp

Burning Time

15, 000 pounds

277

120 seconds

SATELLITE PROPULSION SYSTEM

17

c . ,
1960 1961 1962 1963

II

AIM

11110111111,1111% IMILIAIIN Pal= MT

MUMS EOM SOUKS

It NNE VENN SETETT •

•

Xi SOLAR INOTOWILTAC

3Z SMOAK RASIOISOTOIE

3r MELIA& MAGEE

XL WANGS* uu SOCONSARY

111MTIIIIV COMPOSIENT

MAJOR $ NEANTAD COMMENTS

MAR EMETIONON NAMPESKI

ONSMICAL TEL 'MINNS APO

EMEASSISCINE EMENITIE MEMOMONAL SEM SOUSES

! :

MOM STEW PUNK

MEL •

TUT PHASE •

A OPRIRIMINISAL Pi UNIT NAM.

18

ill

LMSD-414889

AUXILIARY POWER SUPPLY SYSTEMS

The auxiliary power systems include all items required for furnishing electrical power

to satellite-borne equipment. Design criteria include provision for:

Power outputs from 100 watts to 10 KW • Reliable, long-duration operation .

Minimum interference with other • Maximum simplicity with minimum

components weight

Prime energy sources currently under development, and their anticipated availability

dates, are shown below.
(1) THOR

BOOSTED

PAYLOAD GROUP ew

(PRIMARY PAYLOAD: AUX POWER SYSTEM TELEMETRY; COMMUNICATIONS)

STRUCTURE GROUP 450

(AIRFRAME: EQUIPMENT RACKS)

PROPULSION GROUP 570

(ENGINE: PROPELLANT TANKS; PRESSURIZATION SYSTEMS ULLAGE ROCKETS)

GUIDANCE AND CONTROLS GROUP 250

(ASCENT AND ORBITAL CONTROLS)

WEIGHT EMPTY 1,$60

PROPELLANTS 6,540

LAUNCH WEIGHT 9,500

BURNOUT WEIGHT 1,540

LAUNCH AZIMUTH: 152.6°

LAUNCH AZIMUTH: 191°

(2)ATLAS

BOOSTED

5.516

700

615

290

5,1/10

6,170

11.500

4,660

LMSD-414889

TYPICAL SATELLITE WEIGHT DATA

Shown below are weight data for typical models of the Thor-boosted and Atlasboosted satellites.

19

• •

11.06.1* 1
LMSD-414889

SATELLITE PERFORMANCE CHARACTERISTICS

Shown opposite are curves depicting burnout weight vs. altitude for both Thorboosted and Atlas-boosted satellite vehicles.

The term "single burn" refers to a launch procedure whereby the satellite, after

separation from its booster, coasts to a point near its programmed orbital altitude. Its rocket engine is then ignited to provide the required boost to orbital

velocity .•

"Dual burn" refers to a proposed procedure which would enable the achievement

of either higher orbital altitudes or heavier payloads, or a combination of both.

In this instance, the satellite's rocket engine would be programmed to burn twice:

once immediately after booster separation, and again, briefly, for a vernier adjustment of the orbital velocity.
SINGLE BURN

LAUNCH AZIMUTH 1112.11.

SATELLITE Isp2111 SEC.

ISO

a

goo

S

a

iso

100

0

0

SIM

DUAL BUNN

SINGLE MUM

LAUNCH AZIMUTH le Is

SATELLITE I

SP 2112 SEC.

LMSD-414889

0 11100 1400 1500 HMO 1700 MOO MOO 1000 2100

GUNNOUT WEIGHT • POUNDS

THOR-BOOSTED VEHICLES

1400

a 1200

woo

ler 11°. 0

a

I- on

t400

200

A 1000 2000 2000

BURNOUT WEIGHT • POUNDS

ATLAS-BOOSTED VEHICLES

21

LII
LMSD-414889.

um.

SECTION III - COMMUNICATIONS

Details pertaining to the communication equipments and facilities required for each

major development program are presented in subsequent sections directly concerned

with those programs.

In general, Subsystem "H" (Ground-Space Communications) is responsible for the

development, installation, and operation of all equipments required for communication to and from the satellites, as well as from ground station-to-ground station.

Its principal functions comprise:

Orbit Determination - satellite acquisition, tracking, and orbit

computation

Commands to Satellites - both programmed and in real time

Telemetering

Data Transmission - satellite-to-ground

Ground Communications - transmission of tracking data, payload data, .

and administrative traffic.

The Philco Corporation serves as the principal subcontractor to Lockheed for the

development of this subsystem.

Control of research and development flight test operations is directed from the

Development Control Center (DCC) located in Lockheed's Palo Alto facilities.

Direct lines for both TWX and voice circuits connect the DCC and its computing

center with all launching and tracking stations. It is presently planned that a

government facility for R&D flight test control purposes will be constructed adjacent to the main Lockheed facility at Sunnyvale.

22
11111110w LIUD-414889

SECTION IV — DISCOVERER PROGRAM

s.
LIISD-414889

Starting in early 1959. a series of Thor-boosted Discoverer satellites will be used

to develop and test- the ability to recover payloads from orbit. Recovery capsules

(Subsystem "L") for these purposes are being developed under subcontract by the

General Electric Co. , Missile and Ordnance Systems Department, Philadelphia.

Other organisations prominently involved in the program include the Air Force

School of Aviation Medicine; the Air Force Bioastronautics Directorate; Wright

Air Development Center; Hallo:21am Air Development Center; HiCara= AFB; the

Los Alamos Scientific Laboratories; and the U. S. Navy.

Capsule details are shown on

the chart opposite. The Mark I

capsule illustrated'will be installed in the first two recovery flights, with Mark II capsules used thereafter for biomedical research pur -

poses. The Mark I capsule experiments will involve mice;

the Mark Ilcapsules will carry

rhesus monkeys, one 6-pound

primate being carried on each

flight.

MARK I

BIOMEDICAL

RECOVERY

CAPSULE
LMSD -414889 rn Fl DENTI Al

MA . MK-II

RECOVERY

SNELL 77 LES OS LBS

PROPULSION

EJECTION SO 71

RECOVERY

SYSTEM 45 611

IMO PAC 15 17

TOTAL III LBS 279 LBS

sum PLANE PIN PULLER

SPIN ROCKETS

RETROROCKET

SEPARAT ION

STRUCTURE

PROPULSIVE SYSTEM

EJECTION

MECHANISM

PARACHUTE

RECOVERY PACKAGE

RADAR BEACON

"RIESCUIELITE"

SEA MARKER

POWER SUPPLY

RIO PAC

ANIMAL

METABOLIC SUPPORT

RIE•ENTRY RECORDER

ABLATIVE SHELL

25

A I
v*ve....'";- PARACHUTE

• •

BEACON LIGHT

CHAPIN

RECOVERABLE

PAYLOAD

ABLATIVE

SHELL

RELEASE

RADIO BEACON

ALTITUDE 10.000 PT.

LMSD-41 1 L,

CAPSULE RECOVERY PLAN

As a Discoverer satellite passes over the Chinialr., Alaska, range during its 16th

orbit, cone and signals from the ground station will initiate a sequence of events

leading to capsule ejection on the 17th orbit, some 97 minutes later. The capsule

will be moved clear of the satellite by the action of compressed springs. Spinstabilized, it will be propelled earthward by means of a retrorocket. The spent

rocket, spin devices, and their programmer are then jettisoned. The main

parachute is programmed to open at an altitude of 50, 000 feet, at which time the

remaining, unburned portion of the protective ablative shell is released, a radio

beacon is activated, and chaff is ejected.

RC 121 radar picket aircraft will vector C-119

pick-up aircraft toward

the descending capsule,

and pick-up attempts will

be made down to a minimum altitude of 1000 feet,

In the event of failure to

recover a capsule in the

air, recovery at sea will

be effected by USN' Destrayers on station in the

recovery area for this

purpose.

26
• C-1111 PICKUP PLANE

RC-121 RADAR LOCATING lk

VECTORING AIRCRAFT

Li4SD-414889

A sea marker, a flashing beacon light, and the radio beacon will aid the surface

vessels in locating the capsule. Skin divers and small boats will be employed as

necessary.

27

—COTIMUTTIAt--
DEVELOPMENT

CONTROL CENTER 

PALO ALTO.

LAISD-41

TRACKING STATIONS

Locations of the satellite tracking stations for the Discoverer program are shown

on the chart below; all stations are fully equipped, manned, and ready for flight

test operations.
LMSD-414889

SECTION V- SENTRY PROGRAM

29

C0111111-MIAL
PROGRAM OBJECTIVES

The primary objective of the Sentry program is the attainment of a reconnaissance system which uses satellite vehicles as the data-gathering medium. The

development goals are:

To sense and locate with a high degree of resolution all

electromagnetic radiations emitted by or reflected from

the territory. installations, and equipment of potential

enemies;

To transmit this information back to our own forces; and

To record and produce these data in a form of maximum

utility to intelligence agencies.

Two types of reconnaissance systems are being developed under the Sentry

program:

A visual - or photographic - system

A Ferret - or electronic - system

All Sentry satellites are Atlas-boosted and will orbit nose-dawn at an altitude

of approximately 300 statute miles.
LMSD-414889

VISUAL RECONNAISSANCE SYSTEMS

In a broad sense, the Sentry visual reconnaissance system (Subsystem "E")

involves the design and development of equipment capable, on command, of

obtaining reconnaissance photographs of any part of the world. Its operational objectives are to obtain:

Mapping of territories of interest

Strategic intelligence information regarding

Weapons and bases in being

Military logistics

Industrial war capabilities

Bomb daniage observations

Weather observations

To date, development effort for the visual system has been concentrated

on a film process involving electronic readout of the negative image.. In

the meantime, magnetic tape systems are being thoroughly investigated as

a possible alternative to film. It is also presently planned that a development program will be initiated to effect physical recovery of the raw reconnaissance data (film or tape) in addition to electronic readout systems.

The initial visual system will incorporate a 36-inch focal-length camera.

The possibility of developing a system with focal lengths on the order of

90 inches is also under intensive investigation.

31
L

LMSD-414889 MIN

VISUAL RECONNAISSANCE - SATELLITE EQUIPMENT OPERATION

The 36-inch focal-length system

uses a 70 mm camera and can be

programmed to photograph areas of

particular interest, rather than con- LENS

tinuous- strip photography. Ground

resolution is 20 feet. The system came*

incorporates steerable mounts to

permit aiming the camera for taking PIMISSURS

oblique photographs. MOM.

Runs of newly exposed film are

us CAN

stored in a series of tensionSUPPONT

controlled, expandable loopers from TWIN

which the film i s drawn continuously

into a processor. The film is proceased by contact with a web presoaked with chemicals.

THOMPSON

ORIV1

SOLUTION

WHIN

FILM

UPPLY

team.

FILM

TAKII-UP

IMML •

JUNCTION

OH

FULLACALIS MOCKUP OF WINCH SYSTIM

The processed film is fed into a second series of loOpers, gradually building in volume

until a batch is removed by readout contact with a ground station.

Readout is accomplished by scanning the film and converting the negative image to a

video signal for transmission to a grOund station by means of a wideband data link.

32
LIAMD-414889

The operating sequence for the visual reconnaissance system is depicted on the accompsnying chart.

33
LMSD-414889

CONFIDENTIAL 311111112 ' •

VISUAL RECONNAISSANCE - GROUND RECONSTRUCTION PROCESSES

After transmission to a. ground station by the wideband space-ground video data

link, the signals are recorded on magnetic tape. Simultaneously, reconverted

photo images are displayed as a light-modulated line on a kinescope.

The kinescope lines are photographed by a 35mm continuous-strip camera which

records the photographic images as a series of positive frames called the "Primary

Record." The Primary Record is then developed by a high-speed processor.

Aside from photographic images, the Primary Record also contains auxiliary information channels which provide such data as the satellite attitude and the time

of photography. These data are fed into a high—speed computer in which orbit

and programming information had previously been stored.

S 00 • 0.a1111i• b. WINO. 1•••••••• ==•nr,..Z.V.,=.

74".:*4- • •

••••••••••n••••••Ot••

eeNSier4o4C4iN LT.L=2.• • ....•••n•• n •• .4.00*144.3•Siat•‘n••••

PRIMARY RECORD FILM ON GROUND

($E1414 POSITIVE?

The tape output of the computer and the Primary Record film are then processed

through a Reassembly Printer which produces a replica of the original 70 mm

film enlarged to a width of 9.5 inches. This enlarged replica is called the

"Reassembled Record. "

1
RECEIVING RECONSTRUCTION RECORDING PROCESSING

ITY

REASSEMBLING

INTELLIGENCE

USERS

LM5D-414889

Alphanumeric digits presented at the end of each frame

of the Reassembled Record

present approximately twenty

different items of information

about the photograph, such as

attitude, time, location,

scale, orientations etc.

Equipment has been designed

to grid the Reassembled

Record with a one-degree

terrestial, or other type grid,

photographically super -

imposed.

REASSEMBLY FILM (/.5-INCH NEGATIVE)

Duplicate prints of the Primary Record are made available to Subsystem "I"

(Intelligence Data Processing) for Air Force Intelligence and other uses.

GROUND RECONSTRUCTION PROCILMI

35
SENTRY FERRET RECONNAISSANCE SYSTEMS

Electronic reconnaissance (Subsystem 'T") is employed to incercept electronic emissions originated by actual or potential enemies, and to make these data available in a

useful form to intelligence agencies. Information thus obtained will assist in meeting

the National Intelligence Objectives for ferret systems, which are to have reliable information on:

The imminence of hostilities

Enemy offensive systems

Enemy defensive systems, and

Technological capabilities of an enemy

The Sentry ferret system is being developed to provide

continuous electronic surveillance of all territories of

interest. Two principal subcontractors, Airborne Instruments Laboratory, a division of Cutler Hammer, Inc. ,

and Hailer, Raymond and Brown, Inc. are supporting

Lockheed in this development program.

Satellite-borne equipment will intercept the electronic

emissions, measure and store the signal parameters,

and transmit these data to ground receiving stations. A

schematic representation of satellite equipment functions

- together with a listing of the priority bands for the

initial system - is presented on the chart opposite.

36

PPOTOTYFIR OF SENTRY

FERRET I SYSTEM
PULSE WIDTH 1 SCANNING

SUPIERHETEROOYN -0••

RECEIVERS 

FREQUENCY I

CAMOUFLAGED COMPLEX

•

ISTAR

OSCILLATOR

1 

BINARY

COUNTER

I

siNANy

COUNTER

1

CONVERSION

OF DATA TO

DIGITAL FORM

PRIORITY SAND

RECORD

STORAGE MEDIA

(MULTI-CHANNEL

TAPE RECORDER

DISC. OR DRUM)

LOCATI SIGMA 

•

MONITORING OF ALL WANDS

IN THE SO - 11,000 MC/SEC

SPECTRUM

LMSD-414889

This first series of ferret satellites will observe the following:

Significant changes in signal parameters

Significant redeployment of emitters

Intensified electronic signal activity

Unusual absence of signals, and

Jamming activity or changes in the "normal" jamming level.
LMSD-414889

FERRET RECONNAISSANCE - ADVANCED SYSTEMS

Advanced Sentry ferret developments will provide a more sophisticated system for

the collection and analysis of a wide range of electronic emissions, and will be of

particular value to the intelligence agencies in their preparation of estimates of both

Enemy Order of Battle and Technical Intelligence. Emitters subject to ferret intercept will include:

Some of the characteristics of an advanced system are shown on the accompanying

chart.

As a part of the advanced system program, a "Ferret Alarm" technique is under investigation. Such an alarm system would be designed to provide instantaneous transmission to ground stations of intercepted signals of a critical intelligence nature,

such as those associated with an ICBM launching complex.
)NFIDatTtAt LAUD-414889

39

MOE . •

-- • .

i
StNTRY SATELLITZ ASCENT =DAN= AND CONTROL

The sequence of events for a typical Atlas-boosted Sentry satellite during

ascent and orbit orientation is shown below.
VANDUNIBIERO APE

---eefiFLb4-;.:f44TlAt-

. NW" L1iMSD-414889

SENTRY SYSTEM COMMUNICATION FACILITIES AND READOUT LINES

This chart shows the locations of the tracking and data-readout stations

planned for the Sentry system.

41
SENTRY SYSTEM COMMUNICATION LINKS

Three radio links are required for the operation of the Sentry readout reconnaissance

systems:

Telemetry

Command

Payload data link

The space-to-grouid telemetry link serves to transmit teat data to the ground, tp

transmit operational telemetry data for reporting the status of the payload equipment,

and as a signal source for an angle tracking radar on the ground.

The ground-to-space command link provides a channel to transmit the real-time commands which are used to make adjustments and calibrations of the payload equipment.

This link is also used to transmit programmed commands which will be stored in the

vehicle for execution when the vehicle is out of contact with the readout stations.

The combination of the command and telemetry links is used as a round-trip circuit

for the transmission of ranging tones to determine satellite range. These data, together with the angular coordinates obtained from the angular tracker, are sent to the

computer for orbital calculations.

A space-to-ground link transmits the actual data from the payload

equipment to the ground where they are received, processed, recorded, and prepared for re-transmission to the Technical Operations Center. Tracking data ob-

.

tained during a readout pass are sent by teletype circuits to the TOC for orbital
I

i

• T & A STATIONS i!

L.......- • --......,t

PAYLOAD

DATA 11.1110

RANGE on.

TRACKING

COMMANDS

ANGLE

TRACKING

"11".."'"*"^—'• PAYLOAD DATA lk

TELEMETERING

eanorma....

1 COMMAND a ACQUISITION DATA

LIND-414889

calculation., and command and acquisition data are returned on the same circuit.

Payload data are sent to the TOC by special vrideband ground communications

circuits.

43
%am

LMSD-414889

SM.

SENTRY SYSTEM MISSION CONTROL

The principal objective of the Sentry intelligence data processing system (Subsystem

"I'9 is to continuously determine, display, and report critical intelligence data that

might indicate the imminence of hostilities. The intelligence agencies will be provided with both initial analysis reports and reproductions of photographs and ferret

tape recordings.

As depicted on the accompanying chart, control of the Sentry reconnaissance missions

comprises three distinct functions as follows:

Command - which establishes policy and assigns reconnaissance missions

Technical Operations Control - which executes mission assignments generated by Command, and is responsible for tracking, orbit computations,

scheduling, quality control, intelligence data indexing, and transmission

of intelligence data to---

Intelligence Data Processing - where the intelligence data are processed

for interpretation and evaluation.
DATA

READ-OUT

PROGRAM

READ-IN

TRACKING

STATION

TRACKING

STATION

COMMAND

INTELLIGENCE

• DATA

PROCESSING S/S

PLIGHT

PATH

MISSION SCHEDULE

AND PROGRAM

SENTRY

MISSION

ASSIGNMENT

LMSD- 414889
AZNAUTN

DRIVE MOTOR

APERNIURS

(f Pt NA.)• SCANNER

THERMAL

-MECHANICAL

EQUIVALENT

LMSD-414

SECTION VI-MIDAS PROGRAM

Infrared sensing techniques (Subsystem "G") are being applied to four development

objectives:

A Missile Defense Alarm System

An ICBM Precision Tracking and Prediction System

An Air-breathing Vehicle Tracking and Prediction System,

A Ground Surveillance System.

The Aerojet-Generil Corporation, Avionics Division, is the principal subcontractor

to Lockheed for this program, having the responsibility for the design and development of satellite-borne detection equipment. A contract for a back-up development

program, using an alternative approach, has recently been awarded to Baird-Atomic, ,

Inc.
SATELLITE-TO-GROUND ANTENNA INFRARED DETECTION SYSTEM

MEADOW ANTENNA

SOLAR ARRAY

THERMAL SHIELD

47

LAM-414889

The total weight of the infrared detection equipment, communications equipment,

and auxiliary power is estimated to be 628 pounds.

An artist's conception of the MIDAS satellite, as it would appear in orbit, is Hinetrated below.
r.

LMSD-414889

MISSILE DEFENSE ALARM SYSTEM

For a simple alarm system, MIDAS will employ approximately 20 satellites on

1000-nautical mile polar orbits. From this altitude, each infrared-equipped satellite

will be capable of scanning a. ground area of 12 million square miles every 30

seconds. Sector scanning may be commanded from ground stations.

As illustrated on the facing page, ICBM launchings will be detected and instantaneously reported to far North readout stations. Data Will be relayed by these stations to ZI intelligence and operational centers

This data will then be combined with known satellite space location data to determine and present, on .appropriate display units, the following information:

Number of ICBM's detected

Approximate location of launch sites

Approximate direction of ICBM travel

Approximate burning characteristics of the missiles.
LAISD- 414889

49
•

LMSD-414889

SECTION VII-GEOPHYSICAL APPLICATION

A limited number of geophysical experiments, selected for their application to

specific system development problems, will be conducted under the direction of

the Geophysical Research Directorate, AT Cambridge Research Center.

A detailed listing of the geophysical instrumentation flights scheduled for the

Discoverer program is presented on the chart below. , Subject to weight, space,

ground-space telemetry availability, and current requirement for data -- consideration will also be given to the flight of geophysical instrumentation during

both the Sentry and MIDAS programs.

PROGRAMED GEOPHYSICAL EXPERIMENTS

DISCOVERER

IFLIGHT DATES 11/811 I 7/8111 SAM

INSTRUMENT UNITS:

THERMAL RADIATION 3 3 II

COSMIC RADIATION 1 1 I

DENSITY I 1 1

ELECTRIC FIELD AND ION DENSITY 1

50

t

ikn Vi at., J....A 4
LMSD-414889

SECTION VIII-SATELLITE VEHICLE GROWTH POTENTIAL

Substantially increased payloads or orbital altitudes, or combinations of both, can be

achieved for either Thor-boosted or Atlas-boosted satellite vehicles. The design changes

considered involve:

Substitution of more advanced propellants for MINA - MUM

A slight Increase in propellant tank size ( obtainable with

minimum design change)

Dual-bUrning propulsion system (see Page 20).

The attendant improvements in specific impulse and payload capability are illustrated

below. The case shown is for Thor-boosted vehicles at an orbital altitude of 200 statute

miles and employing an N204 - hydrazine propulsion system; other possible propellant

combinations are being intensively investigated. Similar increases in performance can

be expected for Atlas-boosted vehicles at orbital altitudes up to 1000 statute miles.

THOR-BOOSTED SATELLITE (200-S. MILE POLAR ORBIT) *TANK

(P ERCENT) isacoma ►

LOAM NOMINAL Inn PAYLOAD

PRESENT SYSTEM tIRFNA-UOMIU MOLE-BURN) 100

POSSIBLE ALTERNATE SYSTEMS

IRPNA-UDMH SYSTEMS

INCREASE IN TANK SIZE SST VP EIS

DUAL- URN 100 SSO. 100

DUAL-SURN PLUS WRENS IN TANK SIZE 127 III 11$

N

a 4

0 -.HYDRAZINE SYSTEMS

SAME TANK SIZE AS PRESENT INFNA-UONN SYSTEM 100 IDS PM

INCREASE IN TANK SIZE 117 SOS SU

DUAL-BURN 100 SOS 710

DUAL-TURN PLUS INCREASE IN TANK SIZE 1117 SOS 1MS

* EASED UPON TANK CAPACITY OF PRESENT INFNA-110i114 PROPULSION SYSTEM
HOT FIRING AT SANTA CRUZ TEST EASE

LIESD-414889

SECTION IX-FACILITIES

Lockheed facilities for Discoverer, Sentry, and MIDAS purposes presently total

some 425,000 square feet of floor space at three principal locations: Palo Alto,

Sunnyvale, and Van Nuys, California. By mid-summer 1959, many of the functions now being carried out at these locations will be centralized on one building at

Sunnyvale. This building is currently under construction.

An adjacent facility, for use as a Development Control Center, is in the

advanced planning stage. Under the

direction of an AFBM.13 assigned Sys -

tem Controller, this center will provide overall direction and control of

flight test operations. A temporary

installation for this purpose has been

constructed in the presently used Palo Alto facilities.

A complete facility for hazardous

ground tests, including hot firings

of the satellite prOpulsion system,

has been built in the nearby Santa

Cruz Mountains.
LMSD-414889

Launching and tracking facilities for both the Discoverer series and Atlas-boosted

Sentry satellites are either completed or under construction at Vandenberg AFB.

Down-range tracIdng is accomplished bt use of both a radar station at Point Mugu

and a merchant ship, leased and specially modified for this purpose. AFMTC

launching and tracking facilities will be used for low-latitude orbit flight tests related to the MIDAS program.

Tracking and communication facilities required in the far North for MIDAS purposes

are currently being determined; maximum use will be made of facilities designed

primarily for the operation of early warning air defense systems.

"2"111 '4611

53
4 • ver••"4,1; •••

LMSD-414889

Page

SECTION I INTRODUCTION 2

Systems Evolution 2

LMSD Project Management Structure 6

Principal Subcontractors 8

Subsystem Structure 10

SECTION II SATELLITE CHARACTERISTICS 12

General Characteristics 12

Propulsion System 16

Auxiliary Power Supply Systems 18

Weight Data 19

Performance Characteristics 20

SECTION III COMMUNICATIONS 22

SECTION IV DISCOVERER PROGRAM 23

Capsule Recovery Plan 26

Tracking Stations 28

SECTION V SENTRY PROGRAM 29

Visual Reconnaissance Sy stems • • • • • • • • 31

Ferret Reconnaissance Systems 36

Guidance and Control 40

Communications System 41

Mission Control 44

SECTION VI MIDAS PROGRAM 46

SECTION VII GEOPHYSICAL APPLICATION 50

SECTION VIII GROWTH POTENTIAL 51

SECTION IX FACILITIES 52