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wnp l2 3y.1959

MEMORANDUM FOR DISTRIBUTION

SUBJECT: Revision to Section II, 30 April 1959 DISCOVERER Development Plan

Attached are correction pages to Section II (Funding Progran);

Pages II-1 through II-5, of the 30 April 1959 DISCOVERER Developse:re Plan.

Please insert them pages in subject plan dasro1 the placed pages in accordance mith the procedures outlined in Air Force Regulation 205-1.

1 Incl

Sect II, Funding Program

Pages II-1 thru 11-5

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NOFORN

3 0 OCT 1989

HEADQUARTERS

AIR RESEARCH AND DEVELOPMENT COMMAND

(UNCLASSIFIED TITLE)

DISCOVERER

SPACE SYSTEM DEVELOPMENT PLAN

30 April 1959

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AIR FORCE BALLISTIC MISSILE DIVISION

HEADQUARTERS

AIR RESEARCH AND DEMONISM COWED

30 April 1959

EOM

This volume presents the planning for the accomplishment of the

Advanied Research Projects Agency (ARPA) Program Discoverer. This plan

has been prepared in compliance lithARPA Order I. AB-59, dated 16

December 1958, which calls for the separation of the Thor-boosted

Discoverer Program from the overall WS 117L Program structure and

Headquarters, MP message AFIXT 9353 dated ._"____ 27 1xeil-1-959.--p R z,

•

This plan summarises the technical approach and research objectives,

of the Discoverer Program and describes the physical characteristics of c

and operating techniques for the Discoverer Thor combination. It also

provides an explanation of the various subsystems that comprise the'

whole, the testing program being used in developing the system, and

other significant areas that bear directly on the talk of meeting the

designated requirements. In addition, this volume covers the facility.

program requirements, including: (1) test facilities at ARDC centers,

and (2) the military construction required in support of the development

system. lastly, a summary of the fending requirements is included to

reflect the revised Fr 1959 financial plan. The plan also include, the

FT 60 Financial Plan and the Fr 61 Budget Estimate.

04.

0. J. RITIAND

Brigadier General, USAF

Commander

WDPP 594 ►

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SECUa I -CAL MORAN

Tab 1 - Beckareeed 14.1

Tab 2 -. Desisa Cbaracteristics I•24 - I-244

Tab 3 - Contract Amex I•3•1 • 144

Tab 4 - Schedule Ames I-4-1

Tab 5 - Test Ames 14.4 • 1444

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SECTION III • FACILITIES PROGRAM -III-3

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DISCOVERER

BACKGROUND

The concept for using an Earth satellite as a platform for detecting,

measuring, and transmitting significant scientific data to ground based

stations was a natural outgrowth of progress here and abroad with research

rockets. The need for timely and continuous scientific research Utilizing

instrumented rockets and Earth satellites after the close of the International

Geophysical Year was also emphasized by the first conference on the International Geophysical Year held in the United States. .The impetus which motivated

the United States Government to support new methods for collecting otherwise

unattainable scientific information was man's rapidly increasing ability to

view the world as a whole.. From these observations will come a vast body of

geophysical data which will permit American scientists to observe all the large

scale aspects of the Berth: its exterior, the lower and upper atmosphere,

gravity and magnation, and extraterrestial features.

The results of numerous studies conducted since 1946 by American scientists

established that a satellite used as a scientific data gathering medium was

feasible and would satisfy to a great extent the requirements of the scientist

for information.

The concept of the satellite research system is a result of studies conducted at the Rand. Corporation. A study completed in 1947 together with

similar investigations by other contractors concluded that such a satellite

system was feasible. In subsequent years, further studies were conducted by

the Government lading to the award in October 1956 of a contract to Lockheed

Aircraft Corporation for the develppment and test of a satellite research

system. The following month, Massachusetts Institute of Technology was

awarded a contract for the research and development of the guidance and orbital

altitude control equipment for the system.

As the result of the .Adyansgifeaearch Projects Agency (ARPA) Order No.

17-59, dated 4 September 195J with subsequent amendments, the program was

established to provide for 25 Discoverer flights.

ARPA Order No. 48-59, dated 16 December 1958 confirmed previous instructions to identify this program as DISCOVNBER; thus, separating this

development from the overall le 1171, prow= structure.

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DESIGN CHARACTERISTICS

INTRODUCTION

Discoverer is a program which uses a large satellite vehicle as a scientific

data. gathering medium. This prograa is one of progressive improvement those

goal is to continually increase the capabilities and useful life span of the

satellite so that increasinglradvanced scientific experiments meT be conducted. The immediate Objectives of the Discoverer program shall. bs:

The achievement of orbital capability of the basic, satellite

vehicle.

The development of operational system tahniques and procedures.

The recovery of biomedical and other data through the utilization

of a suitable re-entry capsule.

The execution of nonrecoverable advanced engineering tests.

OVERALL OPERATIONAL CHARACTERISTICS

•

Discoverer is composed of the satellite vehicle, the Thor booster, launch

facilities, tracking facilities, and a complex communication and data

processing network with related facilities. The Thor booster provides

the primer), propulsive power as the first stage for the satellite vehicle.

Separation occurs on attaining thepropei . altitude.and attitude. As the

booster falls'avey, the satellite vehicle continues in a self-stabilized

predetermined coast. At the termination of the coast phase, the internal

satellite power plant activates, supplying the orbital velocity increment required to establish a substantially circular orbit. The internal

controls will then erect the vehicle to the proper attitude. The most

Comma orbits will pass within a few degrees of the poles.

•

The vehicle will continue around the earth, and when within range of a

ground receiving station, upon command, will begin to transmit the

recorded date. The data will be received, processed, and transmitted to

the using agencies.

The vehicle will then begin its next cycle. These revolutions will be

repeated at approximately 90-minute intervals. Because the orbit is

essentielly fixed in space, while the earth rotates inside it, successive

passes -bver the earth's =lice will be displaced approximately 22-1/2

degrees at the equator. Useful operation will be terminated either

vhen air drag slows the vehicle to where it plunges into dense atmosphere,

when the electrical power supply is exhausted, or when a failure of equipment takes place.

1-2-1

WDPP-59 -64

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DESIGN OBJECTIVES AND GENERAL OPERATING DATA

A. SATELLITE VEHICLE 

The DISCOVERER satellite vehicle is being developed over a period of years

and will include a variety of config grations, capabilities, and useful

satellite life spans. Development of the system will proceed from a simple

design of limited capability to anore refined version capable of greater

scientific investigation.

The DISCOVERER Program utilizes : . seven diffefedVveklidle:..s. : v:*. configurations is follows:

Flight Configuration I - Flights 1 and 2

The vehicle airframe will consist of the following sections and

equipments: The nose cone assembly; the forward midbody, assembly including

the forward equipment rack; the aft nidbody assembly; the aft equipment

rack; the adapter, including provisions for the retro-rockets; the propellant tanks, but not the propellant liquids; the pressure spheres, but not

pressure gases; the fairings; and the flight termination system. Functionally, the airframe will be the carrier for the equipment it houses, supports,

and/or jettisons

i

 as applicable, during its ascent to orbit and during its

orbital life. Daring the coast phase, the vehicle airframe will separate

from its adapter which will have been permanently attached to the Thor booster

during preparation for launch.

Flight Configuration II - Flights 3 and 4

Same as Flight Configuration I except that it includes a Mark I

Capsule. During the orbit phase, the capsule, .forising the nose cap, will

be ejected for recovery.

.3. Flight Configuration III - Flights 5 throttak 9 

Same as Might Configuration II except for Advanced Engineering Test

Payload.

Flight Configuration IV - Flights 10, 11 and 12

Sine as Flight Configuration III except for additional propellants

additional batteries, increased total impulse of pneumatic control system

 propellants,

interchangeability of payloads.

Flight Configuration V - Flights 13, livand 15

Same as Flight Configuration IV except that the payload is the heavier

Mark II type capsule. • •

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plight Configuratiou Plights 16. 17, 18 and 19

Same as Plight Configuration V except that improved recovery

system and tracking techniques are used.

Flight Configuration UT 201, al. 22. 2,2, 24. and 25

Same as Flight Configuration VI except that more sophisticated

payloads will be carried.

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B. SUBSYSTEMS

1. The overall system development has been divided into seven subsystems

which are identified as follows:

Subsystem A - Airframe

Subsystem B - Propulsion

Subsystem C - Auxiliary Power

Subsystem D - Guidance and Control

Subsystem H - Ground-Space Communications

Subsystem J - Geophysical Environment

Subsystem IC - Personnel

Subsystem L - Recovery System

Subsystem A - Airframe. The Airframe Subsystem will consist of the

propellant and pressurization tankage, structures, aerodynamic fairings for the

satellite, a destruct system and all mechanical :ind electrical installations

in the satellite not specifically included in the definition of other subsystems.

The Airframe will include a 60-inch diameter cylinder adapter (which

will be attached to the booster and remain with it after separation), and the

orbiting vehicle. The vehicle will be a 60-inch diameter, load-carrying cylinder

about 14 feet long, containing or supporting all other subsy stems. This cylinder

will be inclosed for about half its length in the adapter. The payload and

structure on the front of the vehicle will be protected from aerodynamic effects

by a conical nose section. The engine and pressurized gas storage will be carried

at the rear of the vehicle making an overall length of about 18 feet. Maximum

utilization of structural material will assure the highest possible ratio of payload weight to gross weight.

Subsystem B - Propulsion. The Propulsion Subsystem will consist of

the rocket engine; pressurization; feeding and loading systems (other than propellant and gas tanks); the engine gimbals (but not gitbal actuators); and the equipment required to start, stop, and control thrust magnitude in response to an

electrical signal from the ground or from the guidance subsystem; and the equipment required to control the propellant flow mixture ratio. It will also include

any auxiliary devices required to establish proper uLlage orientation in the

fluid system prior to and during start of the main rocket engine, including the

equipment required to operate these devices.

The Project Bustler XLR-81, 15, 150-pound-thrust, pump-fed engine

will be used for the main satellite rocket power plant. The XLR-81-BA-3, using

IRFNA (inhibited red fuming nitric acid) and JP-4 propellants, having a 263-poundsecond/pound vacuum specific impulse, will be used in the first two Thor-boosted

flights. The XLR-81-BA-5 modified to use IRFNA and UDMEI (unsymmetrical Dimethylhydrazine) as propellants, has a 277-pound-second/pound vacuum specific impulse

and will be used on subsequent flights. Forces required to provide proper

WDPP -59-64

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fUel orientation prior to firing the mein rocket engine at the completion of

the coast phase will be provided by small 20-second duration, 120 pound

thrust, solid-propellant rockets (Waage rockets).

Subsystem C - Auxiliary Power. The Auxiliary Power Subsystem

consists of equipment required to supply electrical. power to all subsyhtems

within the satellite vehicle from a time just prior to launch until the end

of the vehicle's lifetime.

Ite Discoverer Auxiliary Power System will be based an the use of

a nominal 28-volt battery power source, a 2-10, 115-volt, single-phase, general

power ac distribution system, a $00-cycle, 3-phase, precision ac power system

and a -26 volt supply. The 2000-cycle ac inverter furnishes power for the -28

volt supply as well as power for a 4 26-volt series booster regulator, operating

from the prime energy source. The auxiliary power system will incorporate

silver peroxide-zinc 'batteries of refined design, yielding 72 vatt-hom's per

pound.. Power conversion equipment will utilize power transistor inverters

and static transformer rectifier components; due to the limitation . of available electrical energy power, conversion equipment of exceptionally high

efficiency is a requirement. Early power inverters have an efficiency of.

65 percent and are adequate for initial test flights. An improvement program

will be initiated for the development of controlled diode inverters that

show promise or considerably higher efficiency for later flights. 1te

initial utilization of a photovoltaic power supply will be made on at least

one flight to furnish 14-volt dc :power to the acquisition beacon.

Subsystem D - Guidance and Control. The Guidance and Control

Subsystem Will be comprised of those items of equipment required to sense'

and direct vehicle attitude and velocity so as to establish a satisfactory

orbit. In addition it will:

Provide self-contained anew for the initial alignment and

maintenance of the desired vehicle attitude during

orbital operation.

Provide an indication of attitude, and rate of change

attitude, to other subsystems in the vehicle . as necessary.

-e. Subsystem H - GroundrOpace Communication. The around-Space

Communication Subsystem consists of those items of equipment required to

perform the following functions:

Determine the position of a satellite vehicle relative to

the earth, as a function of time, by a process of Obseriration and computation

Command and, program the functioning of the vehicle

payload and auxiliary devices on a time-sequence

basis or in real time

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WDPP-59-64 I-2-4a

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Provide a means. for communicating with the vehicle

from ground stations and for receiving and encoding

environmental, vehicle functional and telemetry

data from other vehicle subsystems •

Provide communication facilities and terminal

magnetic tape recording equipment ground installations

for . efficient and reliable recording and transmission

of received information -

(5) Provide a common time reference for the vehicle and

ground complex and a reference date-time index for the

orbital passes.

Subsystem ground equipment at tracking and acquisition sites includes

all non-airborne specialized equipment required to. transmit, receive,

checkout and test, record, process stare, and deCode indexed information and to safeguard or otherwise perform functions at the tracking

and acquisition sites ininediateky subsequent to launch and throughout

the Discoverer's orbiting life.,

The Discoverer pod:Id-space communications program will be based on a

TBP/S-band system. . •

f. Subsystem "J" Geophysical ZnVironment

This subsystem consists of the studies, equipments,

both rocket-borne and satellite borne, required to provide environmental

data considered essential to insure and simplify the design of a successful

Advanced Reconnaissance System. This subsystem also includes the ground

equipment reqUired to maintain, service; calibrate and checkout prior to

flight, those equipments described above.

Insufficientdata exists on geophysical environment to

insure successful design and test of the satellite vehicles in the

following areas:

Atmospheric density

Cosmic radiation.

c. Thermal environment

d- Meteor physics

Solar ultraviolet radiation

- Atmospheric composition

g. Subsystem K - Personnel. A personnel subsystem exists

whenever any other subsystems, or the booster Subsystem, requires the

interaction of personnel. A properly designed personnel subsystem

consists of the following components:

(1) Human engineering to insure optimum man-machine

compatibility •

.(2) Determination of the kinds and numbers of personnel

required to operate and maintain the associated hardware subsystem •

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Training and training equipment required to obtain

suitably trained personnel

Appropriate personnel support lathe form of

technical manuals and other job aids.

h. Subsystem L - Recovery Subsystem. The Recovery Subsystem donsista of a satellite-borne capsule, suitable payloads, and equipment

that will collect and transmit data by telemetering and that will insure

successful re-entry and recovery from orbit.

Design modifications shall be accomplished as required to maintain

the Recovery Program current.

C. AROUND SUPPORT EQUIPMERT 

1.• The term "Ground Support .Equipment" refers to any or all non-airborne

implements or devices which are required at.the launch complex to inspect,

test, adjust, calibrate, apPraise, gage, measure, repair, overhaul,

assemble, disassemble, service, .transport, safeguard, record, store,

actuate, or otherwise perform a function in` support of the.airborne

. • vehicle prior to launch. -

2. The test ground support equipment shall, be protctype ground support

equipment. That equipment' required for the Discoverer program. is -

essentially the equipment already built and on hand. Continuous redesign,

fabrication and test effort is necessary to

Modify, as required, existing equipment to correct deficiencies

arising during the test program.

Support new payloads and any other changes to the vehicle

and its subsystems which require( GERinggnott.

Z-2-6 WDPP-59-64

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SUMMARY DESCRIPTION OF CONTRACTS 

A. AF 04(647)-97 and AP 04(647)-181 Lockheed Aircraft Corporation

Management

. DOD: The central direction and control of concepts, studies,

analyses, expenditures, programing, scheduling.and reporting; the

administrative support required to provide manning,- 'funding and coordination

of all activities of the trogram;: ) ;tr.', the source of evaluation and progress

information to the customer.

Systems 

LMSD: Perform analyses, design studies and flight tests

(and basic development tests not applicable to a particular subsystem) in

determining compatibility of systems, establishing system concepts, design

criteria and contraints to ensure:. Compliance of space bound system components with the concept for each successive system and complete systems

integration. This includes design, development and/or provision and

operation of ground equipment systems, ground-space tracking, communications,

coamand systems and related test,, servicing, calibration and logistical support

equipment (both contractor and/or government furnished) embracing human

engineering and studies as well as engineering research and required

manufacturing.

Subcontract: Conduct a program of analytical study , and system

simulation and conduct A&E studies.

Airframe Subsystem

IMSD: Develop and produce satellite airframe. Provide:

propellant and pressurization tankage; aerodynamic fairings; structural

supports, brackets and fittings;•mechanical and electrical fittings not

included in other systems; environmental controls; and ground equipment

required for tiansporting, servicing, erecting and launching.

Propulsion Subsystem

LMBD: Obtain and integrate the orbital thrust rocket engine..

Develop and provide propulsion subsystem including: feed and loading systems,

engine gimbals, and equipment required to start and stop rocket engine in

response to command (or program) ullage orientation requirements, and

ground based items for testing, calibrating and servicing.

Subcontract: Bell Aircraft Corporation: Modification and

development cF12175713cket to YIR 81-Be-3 (IRFMA and JP-4 propellants)

14DPP 59-64

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engine; performance-of PFRT and delivery of ground and flight engines,

including spares, engine rework, engine repair and handbooks. Mbdification

and development of YLR 8l-Re-: 3 to IRFRA and UM propellant configuration,

perform PFRT and delivery of ground and flight engines including spares,

engine rework, engine repair and handbooks.

Aerojet-General: besignrdevelop and manufacture of solid

propellant ulIage orientation rockets.

Auxiliary Power Subsystem

LMSD: Develop and/or provide and integrate: energy source and

power conversion equipment required to futnish electrical power for all.

sUbsystems within satellite from time just prior to launch to mission's

ending and equipment required for testing and servicing.

Subcontract: Design, development and production of prime

energy sourcee and power conversion equipment, including power inverters,

voltage regulators, photovoltaic collectors, control relays and design,

development and production of primary and secondary batteries.

Guidance and Control Subsystem

LMSD: Develop and/or provide and integrate: ground based and

on board guidance and control (command) equipment required to stabilize,

direct, separate and boost oebiting vehicle and equipment required for

servicing, testing and calibration;

Subcontract: Design, development and production of horizon

scanners, inertial reference package, control valves and nozzles, and

MIT inertial guidance system.

Ground-Space Communications SubillyrWea

LMSD: Develop and/or provide and integrate and operatic spaceground and ground communication and tracking equipment required by.contractor to coordinate and monitor all flights and assist the government in

determining, equipping and manning facilities rim:tired for service controlled activities. This includes all ground support equipment required for

servicing, testing and calibrating.

Subcontract: Philco Corporation: Conduct a program for research,

design, development and fabrication effort for the ground space communication

subsystem and early operation of subsystem; manning and planning of ground

stations; and installation of Subsystem H ground equipment.

Biomedical Bubrystem

LMSD: Develop a recoverable capsule to accommodate an aeromedical package for use with the Thor-boosted vehicles.

WDPP 59-64

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AF 04(61 7)-165 - Space Technology laboratories, Ramp Wooldridge Corp. 

• • 1. Since Lockheed Aircraft Corporation has the prime contract under

the direction. of AIM,' contribution of the Space Technology Leboratories

liesprimarily in the area of consulting services and technical studies.

These services are performed for, and at 'the specific request of AISMD.

. 2. The . STL studies are general in nature. and..indicete. trendei

than highly -detailed •Tinsi-teMtlts. • STI. is not igniponsible for technical

direction, quality of design, contractor performance, or contractor evaluation.

Lettet.Contract Designated as Ssolemental Agreement #15, Contract

AF 04645)-63, Donets Aircraft Compaq_

Responsible for providing mach. BeftiC08 as are required to adapt the

SM 75 booster, its facilities, ground support equipment, etc., to the

Discoverer and launch the combined SM 75 - Discoverer vehicle into orbit.

D. DA 58 - 10, Air Force Cambridge Research Center

Responsible for conduct of a program of research and development on

equipments techniques and methods for the collection of geophysical.

environmental data. AYCRC has been delegated the responsibility for the

conduct of the program ft* the Geophysical Environment Odaystea.

B. - 11. Navalvail on Moffett Yield Dalifornis.

Ream for Lockheed. 

CSO 58 - 33, istie Research Laboratom Aberdeen, Indiana

Wind Tunnel Tests. 

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SECTION I - TEST ANNEX

DESCRIPTION OF TEST PROGRAK

A. .f AL

1. Test Description

'.The basic test philosophy it that in all tests the progression will

be from the simple to the complex. This approach will be followed in the

verification of ccmponents, equipments, subsystems, and the complete vehicle

system and ground facilities.

Another aspect to the Discoverer test program is that all vehicle

equipments will undergo complete environmental, proof, and qualification

tests prior to installation in the vehicle. Further, the vehicle itself

will undergo static test firing prior to delivery to the flight test base.

Certain flight tests will be concerned with the collection of

geophysical and environmental data for the design of future vehicle configurations. These will include requirement for optical tracking to .

provide precise orbital characteristics. Other tests will be concerned

with verification of components, equipments and systems for future configurations.

•

The Discoverer Flight Test Program involves flights Using the

Thor booster for launching from Vandenberg APB on a polar orbit. The

objectives for Discoverer Program are divided into four broad categories,

namely Discoverer vehicle and system operation testing, Discoverer/Thor

compatibility, and recovery capsule operation and testing.

The first flights are primarily engineering tests to establish

orbital capability and to determine Discoverer/Thor compatibility, as

well as the first tests of the complete system, including the tracking

stations.

The following flights will provide a gradual increase in the test

complexity by the addition of experimental capsules carrying a variety of

payloads and by more advanced engineering tests. The test objectives will

be governed in large part by the results of previous experience and flight

results, primarily refinement of recovery of unique payloads from orbit.

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2. System Testing Responsibilities 

a. Support Testing. In support of the development design of

payloads and consequent vehicle design, the following design support

testing will be accomplishedcas required:

Wind tunnel tests

Environmental tests

Recovery system tests

Propellant tank tests

Telemetry system tests

Ground support equipment tests

Roll control tests (Simulation)

Propulsion system altitude start tests

(9) Aircraft/ship data package snatch test

b. Captive Testing. Douglas Aircraft Company will have the

responsibility for any component and captive testing on the Thor booster.

LM SD will provide captive testing for the Discoverer satellite vehicle in

the font of an inplant systems run and a captive firing of each satellite.

vehicle, less its recoverable payload, at the Santa Cruz Thst Base. From

Santa Cruz, each vehicle will be delivered to the flight test launch area

at Vendenberg AFB.

c. Flight Testing. The responsibility for overall tedhnical

flight test direction and planning falls on LWSD. Preflight checkout

responsibility will be shared, however, by LSD and Douglas Aircraft for

their respective vebicleh and equipment. !bugles Aircraft Compaw .

'sill have primary responsibility for design aneeonstreetion of the launch

pad as the booster contractor. Discoverer system control will be vested

in the Development Control Center, Palo Alto, under direct government

cognizance, cognizance from which control will b e subrogated to other LSD stations

as the need arises•during an operation.

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B. FM= TEST OBJECTIVES 

Overall Program Objectives

The primary objectives of the Discoverer Program will be to demonstrate

orbital capability and to obtain biomedical and advanced Engineering Test data

from the recoverable payload capsules.

Detailed Test Objectives 

Detailed test objectives will be prepared for each flight.

C. FLIGHT TEST PLAN

Vehicle

The Discoverer Program utulizes seven different vehicle configurations

as described in Tab 2, "Design Characteristics".

Facilities 

a. Overall control of the Discoverer flight operations will be exercised

by the Palo Alto Development Control Center. Two UNIVAC Scientific 1103 largescale digital computers in Palo Alto will support the Palo Alto Development

Control Center, converting binary tracking data to an ephemeris, issuing acquisition data to tracking stations for subsequent passes, and. predicting the recovery area. Stations reporting directly or indirectly to the Palo Alto

Development Control Center will be:

(1) The Vandenberg Control Center located at Vandenberg AFB, which

controls blockhouse launch operations and stations 2, 3 and 8 below.

The Vandenberg Tracking Station

The Vandenberg Auxiliary Tracking Station located at Pt.

(Pt Mugu Tracking Station).

Annette Tracking Station Annette Island, Alaska

Chiniak Tracking Station, Kodiak Island, Alaska

Hawaii Tracking Station, Oahu Island, T. EN

Eivaiian Control Center, Oahu Island, T. H.

Telemetry Ships

Space Track, Radar and Optical Tracking

Mugu

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b. The Vandenberg and Hawaii Tracking Stations will use the

following equipment:

MART (Modified Mod II) radar

ITX-18 self-tracking telemetering antenna

Tri-helix antenna

Doppler range detection equipment

Telemetry tape recording equipment

Telemetry decommutators for real time data presentation

Plot boards for radar and TIM-18 tracking data

Commrsion.squipment for teletype transmission of

radar, TIM-18, and doppler tracking data in binary forget •

Acquisition programmer for pre-acquisition direction

of antennas

Equipment for transmission of satellite commends

c. 9twinnette and Chiniak Tracking Stations will use the equipment

listed in 2 aboire*

P

except that-theTIMkaantenmesnd associated equipment are

not provided. '.'them radio signal reception functions of the TIM-18 antenna will

be shifted to the tri-helix antenna already installed.

The Pt Mugu Tracking Station will have the same configuration as

Annette and Chiniak above, and in addition will be equipped with a guidance

computer which determines and issues the necessary commands to initiate and

terminate second-stage burning at optima times.

A Recovery Force presently consisting of nine C-119J aircraft

equipped with search gear is stationed and is being maintained at Sickest AFB,

Email. Three destroyers equipped with radio search gear are also stationed

in Bewail. As needed, the Air Force will assign four RC-121 radar picket

aircraft to assist in the recovery operation.

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D. TEST ORGANIZATION

1. GENERAL

Subject to the overaLliuTImement.brthe-Air Poree Ballistic

Missile Division, the Lockheed-Missile System Division (END) has been

assigned responsible technical direction of the DiscOverer Development

Program. In accordance with ARDC Regulations, the AFRO Weapons System

Project Office (WSPO) exercises technical test control of Discoverer Systems

tests. The Chief, Palo Alto Field Office, is the Systems Test Controller

who is assigned responsibility for exercising control of the technical

testa of the Discoverer during the test planning phase and flight test

operations. Within the broad direction established by Al= for Dimconrer„:—.-

development, system requirements are generated and-integratedty-TABD,

and appear amgenerartind detadied.test plans and support requirements.

Following project approval at AFBMD, the documents become official test

plans with which all participants in the program comply. The test

operations are executed by EMSD and Douglas Aircraft Company (DAC), the

booster contractor, under the control of the Systems Test Controller.

In general, systems test direction end execution is accomplished by•LMSD

personnel. In the case of the SM-75 booster, DAC personnel hams been

assigned responsibility for direction and execution of booster activities.

Test control and direction has been established at each Discoverer field

site, with the center of operations located at the Palo Alto Development

Contra Center (PADCC). Major decisions concerned with such items as launch

under marginal conditions will be made at PADCC based on recommendations made

by various field stations. In all cases, final authority in the areas of

test control and direction is at the PADCC.

•

11. PROGRAM SYSTEM OPERATION

GENERAL

The system consisting of orbiting vehicle, launch and checkout

facilities, tracking stations, control centers, and computing facilities,

is considered as an operating entity and the functioning of each

element of the system is discussed as that element becomes active in the

test.

PRELAUNCRITANFING

The basic planning, initiated several months prior to the

scheduled launch date, includes an adequate description of the test

configuration and test objectives. In addition, the specific plans for

attaining the objectives are explained. These plans thus represent a

summary discussion of the vehicle booster combination and the ground

station configuration as they are planned for any given flight.

•

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F. SYSTEM TEST AND CHECKOUT

1. Vehicle

The complex nature of the satellite requires a constant checkout

of components, subsystems, and systems to ascertain flight readiness to attain

the flight objectives. Equipment has been developed for this checkout. From

manufacturing, the vehicle goes through a checkout period at Palo Alto during

which components, subsystems, and the system are checked to determine that

they are qperatingprolperly and that the vehicle is flight ready.

At Santa Cruz Test Base the vehicle is installed in a test stand

and the engine operated. In the contracted facility at Vandenberg APB, the

vehicle is again checked out, using equipment similar to that at Palo Alto to

determine flight readiness. The Vandenberg APB facility is also equipped to

do major disassmibly of the vehicle should the need arise. On the launch pad,

the blockhouse consoles maintain parameter checks of the vehicle operating

systems until the vehicle is launched.

c. The checkout equipment 'will be modified to suit changing flight

Objectives and will. be improved es test results permit operation evaluation.

Tracking Stations 

The tracking stations undergo it continuous program of checkout to maintain operational readiness. Local checks consist of internal checks and aircraft

"flyby" to assist in calibration. Prior to a flight, or an anticipated obit

pass, the tracking station is checked out in conjunction with the Palo Alto

Develop ment Control Center. As the Discoverer Program progresses, the tracking

station equipment will be optimized, based on test results, to increase reliability for tracking and data acquisition.

Palo Alto Development Control Center 

The Palo Alto Development Control Center maintains a. constant program

of checkout with Vandenberg AFB launch base facilities and the tracking

stations. In addition, Palo Alto Development Control Center utilizes as part

of the testing, the .pal Alto Computer Canter to generate en orbit ephemeris

which is transmitted to the tracking stations for equipment checkout;

4. Recovery Force

The air recovery of the capsules ejected from orbit requires a separate

test program to develop the direction finding and air snatch equipment and

procedures. An additional prograa of checkout and continued training of this

recovery force has been initiated. The recovery equipment and direction

finder must undergo testing and checkout prior to each flight to maximize the

probability of recovery. In addition, aircraft crews will participate in a

continuous training program.

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5. Recovery Capsule

•The recovery capsule is to be supplied by General Electric to suit the

Discoverer configuration. The test and checkout of the capsule is a coordinated

.effort . by G.E.' and USD.

commiumommrsymm COUNTDOWN

Communication system countdown is initiated five hours before launch, with

a communication check to each station which also provides a station' readiness

report and a time synchronization. Throughout the countdown the Palo Alto

Development Control Center directs major activities of individual tracking

stations the recovery force, and the launch base activities system condition

.frog individual status reporti and integrates . separate efforts into a coordinatedl

unified operation. The time reli tionehip of individual station operations are

planned for a simultaneous reMr..tneire-denditionof launch and tracking support .

equipment. ,

IADNCE, EXIT AND ORBIT INJECTION PHASES

The operation of the complete system from the instant of launch to the

end of attitude stabilization on orbit is beyond the scope of this arlma41; only

a representative description is given here.

At the instant of lift-off, all booster/vehicle systems will be operating.

Commencing with lift-off, the booster will be programmed to roll until it

attains its nominal flight path azimuth. During this period, the booster/vehicle

will be in vertical flight.

Atter the roll programming is completed, the booster will be programmed

.in pitch to hold a zero-lift trajectory until the separation attitude.is reached.

Pros then until separation a constant-attitude trajectory will be programmed into

the Discoverer control system.

5. Separation occurs on attaining the proper altitude and attitude. Aa the

booster falls away, the satellite vehicle continues in a self-stabilized, pre;_16-::

determined coast. At the termination of the coast phase, the internal satellite

power plant activates, supplying the required orbital velocity increment to

establish a substantially circular orbit. The internal controls will then erect

the vehicle to the proper attitude.

I. ORBITAL PRASE

1. The operation of the entire system during the period after the vehicle is

on . orbit and stabilized in attitude, and before the time when the capsule is

ejected, is described as the orbital phase.

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2. All tracking stations of the Discoverer system conduct a systematic

equipment check prior to each vehicle contact. This exercise serves to

indicate the readiness of the station and verifies the operability of its

equipment.

J. RECOVER! OPERATION

Present pl anning provides that the recovery capsule Will be ejected from

orbit to be air-recovered by c-119J aircraft, in the ocean area southwest of

Hawaii.

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SECTION II - TEST ANNEX

CCIN4AND AND CONTROL IMPOSSIBILITIES AND PROCEDURES

A. GENERAL •

1.' System command and control is a world-wide problem requiring an

extensive, communication network. The actual functions of command

and control are not complex in themselves. The problem is made

complex because of the geographic separation of the various ground

stations and the need for reliable transmission of tracking and system

status data on a 24-hour basis.

2. The tasks to be acccmplished in the command and control of the

Discoverer test configurations include:

The collection and presentation of various types of data that

can serve as the basis for command generation:

The refinement and analysis of selected data to permit its

employment in the decision ar command deterikingtion process.

The definition and selection of emergency operational modes

in the event of system component failure.

The transmission of syst4mcommends.

e. The evaluation of system response to the commands and the

determination of required modifications to scheduled command flow.

3. Central control authority Will be vested in the Palo Alto Development

Control Center. Aportion of this authority will be delegated to the

Vandenberg Control Center and to the Hawaiian Control Center for the

Control of operations in their local areas.

4. The degree to which control can be exercised over the system is

limited by the capability of the ground-to-vehicle command link and by

the high degree of system automaticity.

B. PRELAUNCH

1. The Palo Alto Development Control Center monitors the system

checkout and the countdown during the prelaunch phases. Specifically,

during the system dry-run at X-2 days and again during the system countdown at T-5 hours, the Palo Alto Development Control Center initiates

the following activities:

Communication system checkout

Simulation transmissions from tracking stations to the

computer center

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c. Drysrun orbit calculation

d. System component repair and test rerun.

During the system countdown, the launch facilities aspects of the

countdown are under the direct control of the Vandenberg Control Center.

The Palo Alto Development Control Center in its direction of the overall

countdown, is continually receiving and retransmitting system status

information and other pertinent data such as weather and recovery force

status. Vandenberg Control Center plots the important data received

from Palo Alto Development Control Center. In turn, Vandenberg Control Center

continuously advises Palo Alto Development Control Center of the status of

the launch countdown.

The ftwaiian Control Center is also in constant contact with Palo

Alto Development Control Center during the countdown. Of particular

concern to Hawaiian Control Center is the estimated time of launch

and the weather condition in the planned impact area. The mission

of all control centers during this phase clearly is to establish the

readiness of the system for the planned flight. The decision to

initiate or delay a launch is made at the Palo Alto Development Control

Center. This decision can be made only after all the major system

components have been verified as operative.

C. LAUNCEI AND ASCENT

1. The Palo Alto Development Control Center functions during this

phase are concerned primarily with system coordination as follows:

The tracking stations are alerted and notified of initial

orbit parameters.

The Computer Center receives the times of vehicle engine

start and termination of orbital boost

c. The recovery force is informed of orbit achievement and

redirected if required.

2. The Vandenberg .Control Center functions are the direct control

of the launch facilities and vehicle command during this phase of the

test operation.

D. MIT

1. The exercise of control over the vehicle in orbit is limited

to the following commands:

Reset .of the orbit timer

Adjustment of the orbit timer

Control of orbit altitude and period

Initiation of the recovery sequence

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2. The intervals at Which these commands are given are controlled

by the vehicle position in orbit relative to the tracking stations. Therefore the Palo Alto Development COntrol Center has very little freedom

in commend choice or determination insofar as the vehicle, itself, is

concerned. Roweverl -it must continuously monitor the Discoverer

system during the orbital phase. thexpected component failure in the

vehicle or on the ground will dictate a redetermination of the normal

operational sequence.

E. RECOVERY

The decision to initiate recovery is mode by the Palo Alto

Development Control Center and the command issued to the vehicle on

orbit by one of the Discoverer tracking stations. The ships of the

recovery force will previously have been deployed to the predicted

impact area prior to launch. The aircraft will have departed shortly

before the dump command is sent. Prom this point co avail= Control

Center becomes the focal point for the exercise of system control

as delegated by Palo Alto Developaent rUontrol Center.

Progress ot .themearch and recovery operation is plotted

against a predeterained'time schedule. Appropriate periods, Which

have been established following:rigid safety standards, are pilloved

for ali . and sea search. Changes in *setter conditions are carefully

evalusted ' in.teres of these predeterikined standards .. The Palo Alto

Development ControlCenter is continuously informed of the progress

of the recovery operatiob t Any. decision to postpone or halt their

recovery attempt or the Capsule search millbe made at Palo Alto

Development Control Center on the basis of the information received

from Namaiiin Control Center.

P. SYS= TEST EVALUATION

A comprehensive evaluation of test results will be accomplished

at all appropriate levels

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G. DATA FLOW

1. System test data generated will be initially observed and recorded

at seven geographical locations as follows:

Vandenberg Air Force Base, California

Point Mum, Ravel Air Missile Test Center, California

Telemetry Ship, 950 nautical miles downrange

Keene Point Tracking Station, Bewail

Chiniak Tracking Station, Alaska

Xnnettee Tracking Station, Alaska

g. Recovery Force, East of Hawaii

2. The types of data involve& are:

Telemetry data

Radar tracking and control data

Launch (aebilical) data

rptical data

Weather data

Prelaunch servicing notes

g. Recovery data

b. Operations data (range interference, communications).

3. Data will be recorded and transmitted as follows:

Radar, TI2-18 treater (Ohara provided) and Doppler

rapgetrackingimecise digital data.will be punched on teletype tape

in binary format and transmitted to the Palo Alto Development Control

Cater for computer analyela and-computations.

Radar and TLM-18 tracker (where provided) data will

be presented at the tracking stations as analog plots for station

an-the-spot evaluation of operations.

c. Telemetry data will, be recorded on magnetic tape

which will be transmitted to Sunnyvale for analysis by the fastest

available means.

. d. Critical telemetered data will be decammutabed. if

. necessary and presented-in.realtime at the tracking stations.

Reports of significant events will be made to the Palo Alto

Development Control Center immediately.

e. Space track data -.radar data will be transmitted directly to

the Pale Alto Control Center in real time; optical data willbe appropriately

reduced by Space Track and then transmitted to Palo Alto Control Center.

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4. To insure the rapid incorporation of test results in the planning

and conduct of subsequent operations it is imperative that a complete

evaluation of each test be accomplished within the time span occurring

between flights. Because of the scope of Discoverer test operations •

this places a most stringent time factor on the tasks associated with

post-test data handling and evaluation. Every effort vill be made, therefore, to streamline the data flow process so that lag times may be minimized:

DATA HANDLING FROCIVIIES

• 1. General

1

Bach item of the above types of data will be correlated 'with

system timing and vill be clearly identified as to source, content, and

test number. Other items not listed, but which are pertinent to test

results, will be included in-written reports. Because of the many

individual pieces of infatuation *bleb must be assembled within a short

period of time, every attempt viii be made to deliver'each item of data

vithin.a specified time. Deviations dictated by conditions peculiar to

an individual flight will be covered in the detailed test objectives.

Cthir • necebsary deviations resulting frai conditions arising during or

subsequent to a test will be coordinated through the Palo Alto Development Control Center. Designated representatives fraa Douglas- Aircraft

and DOD will be present at Vandenberg AFB for each flight to collect

and handcarry the required launch data to Bartaikmica and Palo Alto.

2. Thar Launch Data

Douglas (Vandenberg APB) will be responsible for supplying

booster data which included launch data, telemetry data, prelaunch

servicing notes and operation data.

DiscOvarer Data

Lockheed (Vandenberg An) will be respcmsible for•supplying

Discoverer Data items as listed above. Delivery of radar and telemetry

tapes generated during orbit flight will be the respcmilbAity of the

tracking station managers utilizing the ocamunicatice network to Palo

Alto Development Control Center.

DATA MEMO!

1. Discoverer Data Reduction

a.. With the exception of data derived from metric optics, all

raw Discoverer test data requiring reduction to usgeleeltammu0OLL14e!preceased, by /MOD. Since nearly all quantitative informatics derived from

a flight will be of this category, rapid processing of such data is

essential to the timely flow of information. Also, because of the large

volume and the random order of arrival of many separate items of data,

the processing scheme must be both expedient and highly flexible. To.

permit an early evaluation of results, the data reduction process will

be accomplished in two parts in the manner described below.

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"Quick Look" Data. Data reduction required to support

"quick Look" evaluation activity will be accomplished an a first

priority basis within 24 to 36 hours after riceipt of pertinent radar

and telemetry tapes. Naainal "Quick Look" data requirements vill be

specified in detail 60 da/z prior to each flight. Additional data requirements which mey be necessary because of flight events be

specified after a preliminary review of real time records within eight

hours following the test.

Final Data. A final, comprehensive compilation of

data as required for detailed subsystem analysis will be completed within

a period of three to five days after launch.

2. Thor Data Reduction

The reduction of booster data-Will be accomplished by Douglas

Aircraft Company at Banta Monica. These. do:taw:ill be transmitted to

cognizant organizations.

J. SYSTEM VALUATION

1. A complete operational evaluation of •test results will be made.

This evaluation will encompass all woven system test activities as they

affect the achievement of ultimate progrma goals and Objectives. Major

emphasis, however, will be devoted to the timely evaluation of system

flight tests as required to properly.tedirect the prove'. The areas

to be covered will include:

Overall system performance in terms of predicted versus

actual results.

Validity of test plans and conduct in terms of the timely

achievement of test objectives. • .

Techniques and procedures eMployed in,the . conduct of system

test operations. . Adequacy and suitability of systems communications, ground

support equipment, facilities and logiötics, .

•

2. Detailed follow through action. Viii be taken on investigation of

problem areas revealed by preliminary evaluation and detailed analysis.

A completely integrated evaluation of overall imitate operation will be

performed. Necessary remedial actions' affecting the planning and conduct

of the neat test will be coordinated with all orgenizitions concerned

and fully implemented at the earliett possible date.•

.3. Accurate and complete records of program test activity and results

will be maintained. A. continuing evaluOion•Of system operations on a

.flight-to-flight basis will be performed. Operationi concepts, equipment,

and procedures will be modified as necessary for proper program redirection.

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SECTION III

MIISTART CONSTRUCTION FROGRiM

GEKIRAL SUMMIT

The Discoverer program requires facilities to support the, following

essential functions; test direction, booster and satellite assembly, and

checkout maintenance and repair; launch and launch instrumentation; satellite

tracking, control, and telemetry; capsule recovery; and data interpretatien

and dissemination.

All facilities required for the Discoverer program are existing.

These facilities, with exception of the SK-75 Launch Complex at Vandenberg

AFB, were progra;msd under the Sentry (16 117L) Development Plan in the

FT 1958 Military Construction Program.

3. The existing facilities required to support the Discoverer program

and their functions are as follows:

LOCATION FACITATT DESCRIPTION

Vandenberg AFB Administration Building

Launch Base- T-31354 1,475 sq ft

Admin. and Storage Bldg.

Bldg. T-11363 1,350 sq ft

Engineering Building • Bldg. T-13364 2,500 sq ft

Flight Test Opns. and

Supply

Bldg. T-11362 1,940 sq ft

G.H.E. Bldg.

Bldg. T-11354 2,950 sq ft

Sub-system •LP Bldg.

Bldg. T-11345 2,400 sq ft

G/M Assembly Bldg (Min

Bldg gr 9227) 9,600 SF

Shop and Administration

Bldg 3200 SF

"UM

ENZILIN

Program Direction

MD Base Services

DISD Base

Engineering

Test Opos. and

Supply

Naintenanci. and Storage

G.R.E.

Biomedical and

Recovery Package

Maintenance and

checkout

Missile Checkout

GSE Maintenance--

. .

WDPP 59-64

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MUM

IACATION

Vandenberg AFB 

Launch Base

FACILITY DESCRIPTION

Receiving and Storage Bldg.

Bldg. T-11344 2,100 sq ft

FUNCTION

LMSD Base Services

Interim MAB Missile Check-out

Bldg. T-11352 15,200 sq ft

SM-75 Launch CoMplex

Thor Launch Pads 4 and 5

Associated Blockhouses

and Service Structures

Vandenberg AFB .VHF Telemetry Receiver Bldg

Wreektng . Station MOO sq ft

60-foot Dish Antenna

Tri-Helix Antenna

VERIORT Radar Van

Installation

Mark II. Optical Tracker

Launch Thor-boosted

Discoverer vehicles

at maximum rate of

two per month

launch and Orbital

Tracking and Telemetry Data Reception,

trajectory measurements

and calctlations to determine

time to initiate boost.

Administration 6400 sq ft

and VHF Telemetry

Receiver Bldg. with 60-foot

Dish Antenna and Tri-Helix

Antenna

VERIORT Radar Van

Instillation

VHF Telemetry Van Instils

lation vith.Tri-Helix

Antenna

VERICitT Radar Van

InstaLlation

VHF Telemetry Van Installation with

Antenna

Orbital Tracking

and Telemetry Data

Receptionlaunch Ascent

Tracking and Telemetry Data Reception

Final Stage launch

Tracking and Telemetry Data Reception

Orbital Tracking and

telemetry Data

Reception Including

First Pass Acquisition and Recovery

Package Tracking

and impact Prediction

Kama Point

Tracking Station

Oahu, T.H.

Point. Mugu

Tracking Station

N.A.M.T.C. •

Pt. Mugu, Calif.

Pvt. Joe E. Mann 

(Ship)

Annette Tracking VHF Telemetry Van InstalStation . lation

Annette Is. Alaska Antenna

VERLaW Radar Van

Installation

CONFiDENTIAL .f.

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LOCATION FACILITY DISCRITTIOR PUNCTICS

Annette Tracking Pan.Am Leased Person.-

Station nel Rousing

Annette Is. Alaska,

Chiniak Tracking VHF Telemetry Van instal. Same as Annette.

Station lation with Tri-Helix Tracking Station

Cape Chiniak, Alaska Antenna

Existing AC & W Composite Bldg.

Hawaiian Control Wing E of Hale 6,000 eq ft

Center Raked. Bldg.

ECTthems AFB —

Center for Direco

tion of Capsule

Recovery

Operations.

WDPP 59-64

III-3

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