PROJECT TRANSIT

(NAVIGATION SATELLITE)

Objectives

Analysis of data on
TRANSIT 1A discloses

. important objectives
achieved,

TRANSIT 1B is
scheduled to be
launched in April

INTRODUCTION
-NTRODUCTION

Objective of the Navigation Satellite Project
(TRANSIT) is to Provide a globa} all-weather
means of fixing Precisely the POSition of'mobile
missile launching Hlatforms such as/surface crai
submarines and aircraft to an accuracy of 0, 2

nautical miles,

NAVIGATION SATELLITE FLIGHTS

The TRANSIT 1A Satellite was launched from the
Atlantic Missile Range on September 17, 1959,
This satellite was the first in the planned Series
of TRANSIT experiments. All Components of the
Satellite operated satisfactorily during the launch
ing and subsequent ballistic trajectory. In Spite
of the failure to Dlace the Satellite into orbit,

1. An accurate determination of the Satelit,
trajectory by means of Doppler tracking,

206A preliminary appraisal of refraction
effects,

3A cuantitative evaluation of the stability
and accuracy of the frequency generating and
measuring equipment,

4,0A preliminary evaluation of TRANSIT
navigation Capability, air

FUTURE LAUNCHES e
SS SAUNCHES

Two TRANSIT 1B Satellites are being fabricateg
and tested in Preparation for the launching in.

April 1960. TRANSIT 1B will transmit on four
frequencies: 54, 162, 216, and 324 me. By

SECRET

1?



MILITARY SPACE PROJECTS

FLIGHT DATA On
SATELLITES ACHIEVING orpit
t

DISCOVERER FLIGHTS

DISCOVERER vi. (206-1052)
Se RER VI

Date Launched: November 7, 1959 ~ Subsystems: Airframe,
Booster: THOR #206, IRBM Auxiliary Power,
Gross Weight 117,200 lbs. Guidance ang Bio-
Payload Weight 300 ibs, medical

Perigee: 103 Statute Miles Second Stage: DISCOVERER Vehicle

Apogee: 505 Statute Miles - On-Orbit Weight 1, 753 lbs,

Eccentricity. 05 Propulsion: XLR81-Be-5 Engine

Period: 94, 42 minutes . _ Fuel. Unsymmetrical Di-Methy1

Payload: Mark 7 biomedical : Hydrazine/Inhibited Red
TeCovery capsule Fuming Nitric Acig

Flight Characteristics; Ballistic
. trajectory to orbit,

DISCOVERER var (212-1050)
Eo

Date Launched: November 20, 1959 Subsystems: Airframe, Propulsion,
Booster; THOR #212, IRBM Auxiliary Power,
Gross Weight: 117, 200 lbs. me Guidance and Bio-
Payload Weight: 300 lbs. . medical
.Perigee: 120 Statute Miles Second Stage: DISCOVERER Vehicle
Apogee: 1026 Statute Miles On-Orbit Weight 1,750 lbs,
Eccentricity: 119 . Propulsion: XLRB1-Be-5 Engine
Period: 103,67 Minutes : Fuel: Unasymmetrical Di-Methy]
Payload Mark IT biomedical Hydrazine/Inhibiteg Red
recovery capsule Fuming Nitric Acid

Flight Characteristics. Ballistic
trajectory to orbit,

29




rey Ir —

—
in the vehicle. {The third F-1 payload is under-
going systems testing and is scheduled for
delivery to the Lockheed Missile and Space Divisi:

. on January 29, 1960r7 '
. —
Training courses-., # Training courses on the characteristics and:
completed, = Se { operation of the F-1 payload and ground support
“sh equipment were completed for modification and of
. | checkout personnel and for personnel who will be
[fsesignea to Vandenberg AFB. oe.
“a, FACILITIES
7 aw ;
Launch stands Beneficial .occupancy datefor Launch.Stand No. 1,
near completion. Point Arguello, California, except for the pro-
pellant loading system, “is January 1960, Final
completion of Stand.No. 1 ts scheduled for March
and Stand No. 2 for April. .

Plans and specifications forthe Technical Suppor
Building at Vandenberg AFB have been completed
Preliminary concept studies for a Technical
Support Building at Point Arguello were ¢omplete
on December 14, 1959, me,



DECREE - 24-hour
Communications
Satellite,

All design Plans
approved; equipment
fabrication is under
way.

Construction of the
Puerto Rico site
under way,

No action on
Spanish site,

Equipment fabri-
cation in progress at
contractors’ plants,

3. DECREE - Global (24-hour) Communi.
Cations Satellite, Design, development and
le .

launching of seven Satellites into 24-hour .

The first complete component ang Systems test;
for the first Phase of the COURIER Program are
Planned for March 1960,

FACILITIES AND SITES

Action to implement use Of the site at Torrejon
Air Force Base, Madrid, Spain, has been with.

Final circuit and mechanical design for the
8round station complex is 90 Percent complete,
Al equipment units have been breadboardeq and
are operating satisfactorily, The vans are
expected to be delivered to the subpontractor

SECRET  &

15


SECRET

ILLUSTRATIONS
Figure
DISCOVERER VII Launch 1
Stacking of Major Components
en LAGENA Stage for First SAMOS Flight
ae tage —
ry ae |
zs MIDAS infrared Scanner _—— = 3
TRANSIT Satellite in Shroud 4
SATURN Simulated Booster at
ABMA Static Test Tower . 5
SATURN Booster Transportation 6

SATURN Blockhouse Construction at AMR : 7



Recovery parachute
designs have been
finalized.

A 1/10 scale booster

model was used in drop

tests of the SATURN
Booster,

Work on the ABMA
Static Test Tower is
Proceeding on
schedule, -

A contract for con-
struction of the
SATURN complex
has been awarded,

Methods of supplying
liquid hydrogen to
AMR are under Study,

Portation Large,
and booster to Redstone Arsenal,

A computer study

of the SATURN booster, and a drop test Program
using a 1/10 scale booster model have been com.
pleted. Analysis of drop-test results is in Progres

FACILITIES STATUS
eet tus

CAPTIVE TEST FACILITIES

In-house work on the ABMA Static Test Tower is
Proceeding on schedule. i
Pated in having this facility ready for the first full
Scale captive test firing in April 1960,

LAUNCH FACILITIES

Launch complex construction was initiated
following award of a contract in November Covering
construction of the launch pad and amplifier room,
Lox Storage area, fuel storage, and high Preesure
Bas facility, Construction of the SATURN block -
house, which was initiated earlier, is Procefding

for the SATURN vehicle calls for increased use

of liquid hydrogen at an early date. Storage and
transfer facilities at the Atlantic Missile Range are
being planned, Required size and location of these
facilities are under study,

SEGRE 7

?hA


Hight shroud is Shown in Figure 4,
TRANSIT type oscillators will be installed on the
next three DISCOVERER Satellites, This will
Provide an Opportunity for additional testing of
the TRANSIT tracking system,

Launching scheduled The TRANSIT 24 Satellite, Scheduled to be
for May 1960, launched in May 1960, incorporates Several func.
. Honal and structiral Changes. The 24 Satellite

running from the 3-mce stable Oscillator will be
used in the telemeter System and will also ‘provide
@ means for accurate time correlation between
8round stations, The total Payload weight is 265
Pounds including the GREB, Pick-a-back, Satellite,

Light-weight Operational TRANSIT Satellites and Prototype

TRANSIT satellite configurations immediately preceding them wil)

being designed for weigh between 50 and 100 Pounds. Current version
“"* operational use, of the NASA SCOUT vehicle appear to meet the

TELEMETRY AND TRACKING

Receiving Stations- At present there are five fully instrumented 8round
The Lasham, England, Stations. The sixth TRANSIT Station at Lasham,
Station is being fully - England, wil) be completely equipped by June 1960.
instrumented, *, The Naval Ordnance Test Station (NOTS) at China

Lake, California, has Started construction of
eight additional 8round stations which the TRANSIT
Satellite can use, These Stations represent an
advance, in that instrumentation designed Specifi-

13


PROJECT SHEPHERD
(TRACKING NETWORK)

Objective The objective of Project SHEPHERD is the

DOPLCC to be A doppler system complex, known as DOPLOCc,
phased out. was used initially to complement the MINITRACK
System. In late December, a decision was made
~ to phase out both the R&D and Operational aspects

CURRENT S TATUS
eS

Tracking ef DICCVINER Data received on the Minitrack System indicates

VI, VU and vin. that DISCOVERER vy came down on October 20
and DISCOVERER VIE on November 26.
DISCOVERER vin, launched on November 20,
is still in orbit,

Navy furnished with The Chief of Naval Operations has directed the
weekly search . t establishment of a Program to familiarize Fleet
ephemeris, Ommanders ‘with the potential threat to naval

the Space Surveillance System, [x ony


SECRET
PROJECT NoTUS

(COMMUNICATION SATELLITES)

INTRODUCTION

—— EE LNON ;
Satellites to be used . The objective of the Communication Satellite
for receiving and Project (NOTUS) is the development of a

retransmitting messages. communication System, utilizing satellites to
Provide long range radio communication links,
The satellite communication system is expected
to relieve the Presently overcrowded trunking
facilities and to improve reliability of global

communication;
Project being The Communication Satellite Program is being
re-evaluated, : re-evaluated, Program decisions reached will

be included in the next report,

DELAYED REPEATER

COURIER - The initial phase of the Project is the develop-

Delayed Repeater. ment of an operational delayed repeater Batellit.
(COURIER) which receives messages over one
point and retransmits them over another,

INSTANTANEOUS REPEATER.

The advanced system consists of three phases:

«
STEER -- Strategic 1. STEER - Strategic Polar: Communi-
Polar Communications Cations Satellite. Design, development and laun
Satellite. ing of four instantaneous communications satellj

into six-hour polar orbits to obtain two-way con
munications, through the Satellite, between gro.
Stations in the United States and Strategic Air
Command aircraft flying in the northern polar

region.
TACKLE - Advanced 2. TACKLE - Advanced Polar Communi-
Polar Communications. Cations Satellite. An interim Program to use a

STEER developed test bed for the early develop.
ment and testing of components to be used in
. Project DECREE. Project TACKLE will be

SECRET :


4
%
\

Ace age:

x}

bY

TENS

FIGURE 5. SATURN Simula:
ABMA Static Te

ted Booster at
st Tower,



3. East Atlantic Station. Action has been
initiated to obtain use of RAF Station Kirkbride
as the site of this Station,

4. New Boston Station. Fina) acceptance
inspection of Angle Tracker, Command Trans-

temaining facilities are scheduled for completion
. -intrementally between February ang September
1960.

a Ottumwa, Towa.Station, Plans and
specifications for the technical facilities for the
station are complete and ready for advertising,

6. Satellite Test, Center, Sunn e, Caliz
fornia, Increment one of this center. ‘(formerly
Development Control Cen ) was completed ang
accepted from the Construction agency during
December, Increment two is Stheduleg for com.

Pletion in June 1960, .

7. Space Operations Contro} and*Data
Processing Facility, Offutt AFB (formerly
Technical Operations Control and Processin,
Center. Design was initiated in October 1959and
is scheduled to be completed in March 1960, \

21



Biomedical capsule

thermal tests
- conducted,

Live specimen testing
to.be resumed in
January,

First increment of
Test Center com-
pleted.

throughout the capsule system, was completed
on November 25, 195 , in the High Altitude

‘Temperature Simulator, The tests -were con

results indicate that Simplification of the syster
Tay be feasible, Howeyer, it appears. that
additional water evaporator Capacity may be

Biomedical testing with a live Primate ia expecte
to be resumed in January, following Capsule
Tmodifications now being made, Modifications

FACILITIES
—

Increment one of the Satellite Test Center
{formerly Development Control Center) :
Sunnyvale, California, wag completed ang
accepted from the construction-agency during

. December, Increment two.is. scheduled for

‘completion in June 1960,

:


SECREF

Ice and rain shields Design of ice and rain shields for the booster,
for the SATURN to be made of rubberized fiberglas material,
booster have been. has been completed. The shields 8reatly reduce
designed. formation of ice and snow on the LOX tanks

PROPULSION
All SA-T engines have Delivery of five H-] Production Engines during
been delivered. the reporting period completed delivery of all

Several areas of inves- A number of studies are under way to provide

tigation to improve per- improvements in the SATURN Propulsion system

formance are under way. These include: Investigation of a dual ignition
System for H-] engines; Studies of engine aero-
dynamic loading; and Investigations of 2 mono-
Propellant gas generator system.

TEST PROGRAM
ESSE

Nine H-1 engines have . Testing of nine H-1 engines (H-100) thru H-1005

been successfully tested for SA-T has been successfully completed at

at ABMA. , ABMA, There have been only minor malfunction
. and no major hardware changes were required,

Testing of the complete Testing of the complete instrument compartment
instrument compartment cooling system was continued. Three test runs
cooling system continued. completed to date indicate that minor adjustment
and modifications are necessary to prevent spot
“tooling and to improve. circulation,

The simulated SATURN booster was installed in
the ABMA Static Test Tower ina Satisiactory .
checkout of handling techniques and various
Clearances, (see Fig. 5)

RELIABILITY
——eeeee ss
Reliability test procedures Reliability test procedures are being established
are being established for SATURN C components on which procuremen

for SATURN components. action has been initiated. Completion of test
Procedures prior to Component delivery will
Permit an early start on reliability testing.

24 -



PROJECT TRIBE

(VEHICLE DEVELOPMENT AND MODIFICATION)

- PROJECT SATURN
:

SATURN to fill early
need for orbiting large
payloads, .

Development Operations
Division of ABMA and
SATURN Program are
to be transferred to
NASA,

Booster contains eight

Rocketdyne H-] engines.

Recommendations
made on configuration
of upper stages.

INTRODUCTION
ANTRODUCTION

Project SATURN evolved.as the earliest possible
solution to the urgent need for. boosting large
Payloads into orbit, The Army Ordnance Missile
Command was designated to Provide a space
vehicle booster capable of generating approxi-
mately 1.5 million pounds thrust,

As a result of the President's decision to
transfer the Development Operations Division
of the Army Ballistic Missile Agency and the
big booster Program to the National Aeronautics
and Space Administration, technical supervision
for the program has been assumed by NASA
under an agreement worked out between NASA
and DeD. Administrative Supervision of the
Program remains with ARPA and SATURN
development remains the T esponsibility of
AOMC until the transfer plan is approved by the
Congress.

The SATURN booster Consists of three main
Sections: the tai] section, the container Section,
and the upper Stage adaption section, The con-

tank (105 inches diameter) for LOX, and eight
REDSTONE-type tanks (70 inches diameter),
Surrouncing it ~ four for LOX end four for fuel.
The tail section Contains eight Rocketdyne H-1}
engines with a nominal sea-level thrust of
188,000 pounds each,

Upper stages for the SATURN vehicle have been
the subject of continued Studies and review to
determine an optimum configuration and a desirab
growth sequence,

SECREF

21




PROGRESS HIGHLIGHTS

During the Quarter Ended December 31, 1959

capsule. DISCOVERER VIO, launched on November 20, also achieved
orbit. The orbital Period, however, was greater than planned and the
recovery capsule was ejected on the fifteenth Pass, Nine aircraft and a
surface ship tracked the capsule beacon after ejection, but the signal was
lost after a short time and no further contact was made. - .

|
|
i obit.

The second TRANSIT vehicle (navigation Satellite) is scheduled to be
launched in April 1960 from the Atlantic Missile Range,

The communications satellite project (NOTUS) is undergoing
re-evaluation with a view toward the possible elimination of one or more

24-hour satellite - DECREE,

The satellite detection System, under Project SHEPHERD, continues
to track satellites in space. DISCOVERER Vi came down on November 26,
and DISCOVERER VIII is still in orbit. A decision has been made to phase
out of the tracking network the doppler system complex, known as DOPLOc.

In the SATURN Project (1.5 million pound cluster engine), configuratio:
of upper stages has been approved. It has also been decided that all upper ~
stages will be fueled with hydrogen- oxygen Propellants, | Testing of all H-)
engines has been successfully completed, and the full eight-engine Captive
test firing is now scheduled for April 1960,

SECREF


FIGURE 3.

MIDAS Infrared Scanner



Launch of DISCOVERER
IX set for late January,

Final AGENA "A"
vehicle in modification,

First AGENA "Bt
vehicle ready for
checkout.

SECRET

initiate the ejection sequence, Subsequent
investigations indicate that the power failure

was probably caused by the load

limiter.

Because of the greater than planned orbital
Period, the DISCOVERER VII Capsule wag
ejected on the fifteenth pass, Nine C-119
aircraft and a surface ship tracked the cap.

was made. Subsequent analysis i

the vehicle guidance system “hunting" for a
Stable attitude at the greater. than planned
apogee resulted in Premature exhaustion of
control gas. The vehicle, therefore, was

improperly oriented at the time
ejection.

DISCOVERER Ix
ee ES

of capsule

Launch of DISCOVERER IX is scheduled ten.
tatively in late January. The exact flight

date depends upon.completion of

various

planned modifications and delivery of the

payload to Vandenberg AFB.

STATUS OF AGENA VEHICLE

The last three AGENA "A" vehicles for the’
initial DISCOVERER flight design Program

underwent hot firing at Santa Cr
(SCTB). Two of these were acc

uz Test Base
epted by the

Air Force on Nove: er 17 and are now at

Vandenberg AFB,

The first AGENA "BH vehicle in the follow-on
Program was essentially ready for modification

and checkout at the close of this

reporting

Period. This vehicle has an engine restart

capability and includes integral
tanks of double the AGENA "Au
permit extended engine burning

Propellant
capacity to
time.



Reliability
improvement,

COURIER system
Capacity now estimated
to be in excess of 12
million bits per ground
station orbit,

Equipment being fabri-
cated at Philco,

Trajectory studies
define maximum
Payload weight.

tests will begin.

SATELLITE EQUIPMENT

until approximately September 1960 may result
if this Proposal is approved.

Development of the Satellite recorder/play back
equipment and the ground station data readout
equipment has Progressed to a Point that Permits
a re-determination of COURIER System capacity
It is currently believed that the original estimate

will have a Capacity in excess of 12 million bits
per ground station per orbit.

Components for the satellite Package are al)
under development and are in the breadboard
Stage. Models will be built as soon as all tests,
now in progress, are successfully completed,

PROJECT STEER
a TEER

Capability of 600 pounds in a circular Polar orbit
of 6 hours. General Electric Company is re.



a

me

THIS DOCUMENT CONTAINS INFORMATION
AFFECTING THE NATIONAL DEFENSE oF
THE UNITED STATES WITHIN THE MEANING
OF THE ESPIONAGE LAWS, TITLE 18, U.S.C.,
SECTIONS 793 AND 794. THE TRANSMISSION
OR THE REVELATION OF ITS CONTENTS IN
ANY MANNER TO AN UNAUTHORIZED PER-
SON IS PROHIBITED BY Law,

MILITARY SPACE PROJECTS

.

QUARTER ENDED 31 DECEMBER

Department of Defense

Washington 25,D.C.

1959

ea

‘SERE- 6 - M~O M6,


‘SA

- SAMOS 'to piovide
¢ both Visual (Photo-
graphic) 2nd Ferret

. (Ele oma gnetic)*,
Data. : Sy

Acquisition of data
“" “by capsule recovery. --

AGENA vehicle for
first SAMOS flight
nears completion,

First payload (E-1)
operated successfully
under orbit

. conditions.

feeiccen

MOS PROJECT

{RECONNAISSANCE SATELLITE)

oTM~,

Lod tebe
INTRODUCTION —
INTRODUCTION

The objective of the SAMOS project is the
development of a reconnaissance system utilizing
polar orbiting satellites to aglect and process
visual (photographic) datafand ferret (electro-

eing developed for acquirin
the recovery system ~ for
" a capsule is ejected from
the satellite.and recovered nd (2) the electronic
data reddout system - for: bo! isual‘and ferret 7
in which data is. transmitted t& groun stations] TM
. ead
GENERAL
Stacking of the § jor components of the AGENA
second stage for the first SAMOS flight vehicle,
shown in Figure 2, was completed on November ¢
1959. Completion of modification and checkout
is scheduled.for Januazty 1, 1960, Subassembly
of the second AGENA vehicle is Progressing
on schedule. The first SAMOS launch is now
scheduled for June-1960 i ‘

VISUAL REC ONNAISSANCE SYSTEMS
7

Following comprehensive testing, the first flyabl:
‘(E-1) payload was operated successfully for 72
hours under simulated orbital conditions. During
subsequent vacuum tests, however,. improper
installation of'a claroping ring assembly resulted
in the payload pressure shell being damaged
beyond. repair. The payload has been diverted fo:
type test use only. Work on the second deliverab
” E~1 payload’ has. been accelerated for use.ags the. f
flight article. Delivery is scheduled for January,
1960, to Lockheed. ~
en,

SECREF fF





The first full eight-
engine captive firing
of SA-T rescheduled
from March to “April
1960.

Studies indicate the

24-hour cormmunicati ons -

satellite mission can be
accomplished with one
engine out.

All fabrication and
assembly drawings have
been released for SA-T.

Hydraulic actuator 8
show Satisfactory
performance.

SECRET

CURRENT STATUS
US
GENERAL

The current SATURN test schedule Provides for
one booster (SA-T) for captive test firings and on
for each of four Night vehicles (SA+1, SA-2, SA-:
and SA-4), Asa result of minor technical difficu]
associated with prototype Production, the full eigh
engine captive firing of SA-T has been reschedule
from March to April 1960. Fabrication of SA-1
components has begun and no Slippage is expected
to result from the Gelay in the test vehicle. .

This rescheduling should have no effect on flight

tests currently Scheduled to begin in third quarter
1961,

Studies of first Stage "engine-out" Capabilities
of a three stage SATURN vehicle with a 24-hour
communications satellite mission have shown
that the mission could be accomplished if one
engine fails. A reduction of approximately

350 pounds in the optimum payload for 8 engines

use in the event of one engine's failure, Propellar
reserves for each flight will have to be determinec
by the particular mission and pay load requir ement

GUIDANCE AND CONTROL



A committee, chaired by NASA and including
Tepresentatives from ARPA, the Air Force,
Department of Defense, and ABMA, has
recommended adoption of the ABMA "'c" Series
SATURN development program. The group
recommended that: .

1. A long Tange development plan for the
SATURN vehicle be established that will provide,
through a consecutive development of "building
block " upper Stages, a substantial early payload
Capability and a final Configuration that exploits
the maximum Capability of the SATURN first
Stage (booster). Vehicle reliability will be
emphasized in the."building block" program
through a continued use of each development
Stage in later vehicle configurations.

2. All upper Stages be fueled with hydrogen-
oxygen propellants, :

3. The initial vehicle configuration consists
of the following:

a. The eight-engine first stage (booster)
" currently under development at ABMA.
BoA newly-developed Second stage with
a diameter of 220 inches using four of the current

CENTAUR engines uprated to 20, 000 pounds thrust
each,

a. A 150, 000 to 200, 000 pound thrust .
hydrogen-oxygen fueled rocket engine for ultimate
use in second and third Stages oi later SATURN
vehicies of the "C" series.

boA design study of the hydrogen-oxygen
upper stages using the 150, 000 to 200, 000 pound
thrust engines ag ultimate second and third stages
of later SATURN vehicles of the "Cc" series.



DISCOVERER PROJECT

(COMPONENT TESTING SATELLITE) .

Project Objectives -
Development and test-
ing of components for
Military Space
Technology Program.

DISCOVERERS vy
and VIII Jaunched into
orbit successfully,

Payload re covery
efforts unsuccessful,

qT

SECRET

OPICAL SUMMARY

IN’ TRODUCTION
ION

The objective of the DISCOVERER Satellite
Program are to conduct research and developme
on components, equipment, instrumentation, pre
Pulsion, data Processing, Communications and
operating techniques all dealing with military
Space technology,

DISCOVERER FLIGHTS

DISCOVERERS VII and vit

both flights and orbital status Was achieved, aj.
though the DISCOVERER VID apogee was much _
higher than Planned, These Bights represent the

neither of the Payload recovery attempts was
achieved, Initia) telemetry Teceived on the first

o
if
8
Fd
o
a
a
ts)
Ea
a
wo
z
E
o
a
o
4
o
es
uo
fi
a
o
a
E
q


ctr:

FIGURE 4, TRANSIT Satellite in Shroud



STATUS OF FUNDS

(In Millions)
December 31, 1959

oof.
Funded (ARPA
Orders Issued). Amounts

1/ Excludes $84.

1 pro rammed

SECRET

27

during Fiscal Year 1958 ang Prior years
-for WS 117L Program, DISCOVERER, SAMOS and MIDAS Projects
outgrowths of WS 1171,

FY 1959 & . | Programmed Cumulative Cumulative
Project ‘Prior Years FY 1960 Obligations Exp enditure
DISCOVERER 1/ $136.6 $ 66.6 $166.0 $143, 2/

¢_SAMOS1/ 105.6 159.5 168.7
SS =— ea
ha :
“i MIDAS 1/—— : 22.8 46.9 39.9
SS = ===
Meteorological
Satellite 12.8 -- 11,4
Navigation Satellite 10.6 16.8 12.4 1.4
Curnmunications. 16,7 - 388 17.5 6.8
Satellite
Tracking 31.9 12.0 29.6 14,1
Feasibility Studies 20.4 12.0 19,2 10.9
Vehicle Development and
‘Modification
SATURN 34.0 70.00 06° 69.3 38.9
CENTAUR 21.5 - 21,5 16.0
Upper Stage 4.3 4.9 4.3 3.1
Modification
/sLarge Thrust Test Stand, .7 5.7 5.4 5
. “ ‘ 7
cast. - ot
TOTAL ~- 4, (347, 9 $433.2 :$565.1 $386.4 4
; f , ; >

are
7
7


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MINITRACK furnishes
data to NSSCC.

New NSSCC building
occupied.

Central transmitter
site chosen.

During the Teporting period, the NRL MINITRAC:
System began to furnish observational) data to

the interim National Space Surveillance Control
Center (NSSCC) located in Bedford, Massachuset:

The new building at NSSCC was Occupied on
December 1, 1959. The 15m computer at

As a result of preliminary surveys, the central
transmitter site for the active MINITRACK Syster
has been located at Lake Kickapoo, near

19


SECRET

CONTENTS
PROGRESS HIGHLIGHTS 1
TOPICAL SUMMaRy | .
DISCOVERER (Component Testing Satellite) 3
SAMOS (Reconnaissance Satellite) | 6
Ph MIDAS (Very Early Warning Satelite) ! 9
TRANSIT (Navigation Satellite) 12
NOTuSs (Communication Satellite) ; 14
SHEPHERD (Tracking Network) - , : 18
LONGSIGHT (Feasibility Studies and.
Exploratory Research) 20
TRIBE (Vehicle Development and Modification)
SATURN" (Clustered Engine) 21
.. STATUS OF FUNDS” 27 .
. LAUNCH SCHEDULE 28
FLIGHT DATA 29

iv


FIGURE 2, Stacking of Major Components Agena
Stage for First SAMOS Flight.



Common design
ssible for MIDAS
: an SAMOS airframes,

\

Aerojet-Gengral
equipment deliveries

Baird Scanner unit yy
thermal tests Conducted. *:

Use of pyrotechnic
targets evaluated,

Integration of MIDAS/
BMEWS facilities
considered,

Summary of con-
struction progress for
MIDAS program
facilities,

3 and subsequent, ot
not be interchangeable.

Atlantic Missile
infrared scanner

Range. (An
is shown in

Aerojet-General
Figure 3.)

using ‘pyrotechnics on
tar get.', Minimum permissible burhing time
would bes 30 seconds, assuring at least one "look
by the orbiting MIDAS scanner in the full scan
mode, \

~ \
FACILITIES.
—_—_—Y

A Preliminary ‘determination has been made that
Ballistic Missile -Early Warning forward site
computers were too'heavily loaded to Permit the
Processing of raw MIDAS data; that MIDAS
could use BMEWS comipunications routes but
not necessarily the saméerminal equipment; .
and that mutual electronic, interference con.~
siderations made it impreclid for MIDAS and
BMEWS to share forward sit buildings,

North Pacific Station,

2. North Atlantic Station. Studies © being

continued to locate a Suitable site for thik, station.

SECRER

1



SECRET

THE SECRETARY OF DEFENSE
WASHINGTON

January 26, 1960

Dear Mr. President:

lam forwarding herewith the Military Space Projects Report
for the quarter ended December 31, 1959,

also achieved orbit. Because the orbital Period was greater than Planned
the recovery Capsule was ejected on the fifteenth pass. Aircraft and a

- surface ship tracked the Capsule beam after ejection, but the Signal was
lost after a short time and no contact was made. The next DISCOVERER
daunch is scheduled for January 29, 1960, following extensive modifi-

The second navigation Satellite, TRANSIT, is Scheduled to be
launched in April. 1960 from the Atlantic Missile Range.

In the SATURN Project (clustered booster), Configuration of
the upper Stages has been approved and it has been determined that all
upper stages will be fueled with hydrogen-oxygen Propellants. Testing
of all H-1 engines has been successfully completed, and the full eight-
engine captive test firing is scheduled for April 1960.

With great Tespect, I am

Faithfully yours,
¢

/s/ James H, Douglas
Deputy

1 Inctosure:
Military Space Projects Report

The President

The White House




Preliminary guidance
and staging sequence
determined.

Cost reduction to be
effected by use of
available space on
CENTAUR flights.

the guidance and staging Sequence of the
ATLAS/AGENA "BM combination. The pre-

PROJECT TACKLE AND DECREE

Payload space available on the last three flight
of the CENTAUR R&D Program will be used by
Project DECREE for preliminary development
and test of thé satellite vehicle and communi -
Cations payload, This will decrease booster
costs by Precluding the necessity of separate
Project TACKLE Jaunches and will Provide the
additional advantage of testing the satellite
vehicle at the 24-hour altitude and Possibly in
the equatorial Plane.



ADVANCED RESEARCH PROJECTS AGENCY
WASHINGTON 2.D.c.

25 January 1960

SUBJECT: Progress Report on Military Space Projects for Quarter
Ended December 31, 1959

This transmits the Military Space Projects Report for the quarter
ended December 31, 1959, :

During the Past quarter, “decisions were made to transfer @ number
of military Space projects from the management Cognizance of the

7
lInclosure: A. W. Betts
Quarterly Report on ; Brig, General, usa
Military Space Projects Director

a


Approximately 50 test
fixtures are already
@vailable*for testing
of SATURN booster
hardware.

A plan for transporting
the SATURN Booster
from ABMA to AMR has
been devised.

Authorization given to
initiate design of the
roll-on, roll-off barge.

A plan has been devised
for recovery of spent
SATURN Boosters.

SECRET

Approximiately 50 test fixtures are already
available for testing of hardware to be used on
the captive test booster, eS are general)

adaptable for testing components for the first four
flight boosters also.

BOOSTER TRANSPORTATION SYSTEM

A SATURN transportation plan Covering movement
of the booster from the Army Ballistic Missile
Agency to the Atlantic Missile Range has been
finalized. (See Fig. 6.) The SATURN boos ter
will be towed on its wheeled transporter, already

Carrier,
down the Tennessee, Obio, and Mississippi
Rivers to New Orleans. A Sea~-going vessel

will take it across the Gulf and around Florida

to Fort Pierce, Florida. An inland Waterway tug

The Army Transportation Corps was authorized
to initiate design of the roll-on, roll-off barge,
This barge was chosen because it Can make the

BOOSTER RECOVERY

Recovery of the Spent SATURN booster is current):
envisioned as follows: A 57-foot diameter drogue
chute will be used to Slow the fall of the booster
and deploy the three 108-foot diameter chutes.
The 108-foot diameter chutes will reduce the boost
rate of fall to 90-100 feet pensecond. Beginning
at approximately 100 feet from the water, eight

SECREF

25


SECRET

PROJECT LONGSIGHT

(FEASIBILITY STUDIES AND EXPLORATORY RESEARCH)

Progress continues
on space power supply
Projects.

Space Propulsion
Projects continue,

in existing programs that might be of future
military Significance, This Project Tesulted
in Coordinating and broadening the base of the
basic effort to advance the State of the art,
especially in Space technology,

SPACE POWER SUPPLY

and in heat rejection.

was developed that Simulates the actual blast
of a nuclear Getonation,

SPACE MATERIALS, STRUCTURES,
PHENOMENA, ELECTRONICS, GUIDANCE &

CONTROL

SECRE-

20


ér-i payloads/in The first two F-] Payloads w,
modification and LocRBeed on October 23, 1959//
checkout area, -.-. in the Modification and checkout ¢

wee ; SECRET —
~] payload support AU E-1 Payload support equipment hag been

WPment installation installed in the Sunnyvale checkout area,

-Cormplete,

E-2 Feyloa
on schedule,

Extensive deliveries
of support equipment 2 quiz
made at Vandenberg Vandenberg AFB, Installation will be made in

AFB, the } fissile Assembly Building (for Payload checky

Vandenberg"ary include Payload handling equip.
ment, payloa test Support equipment, oscillograp)
Tecord camera,;.and 35mm quality evaluation

fy

viewer, :
. , ‘,
Recoverable systern Final design Parameters are being established for
Parameters being © the E-5 (recoverable * Oto graphic Teconnais sance
established, System). As presently:planned, the E-5 Payload

will use a mirror system.to Permit TMmounting of

Ns eeteng
por , i
4 FERRET RECONNAISSANCE SYSTEMS i
‘ a!



SECRET

| ; /  Mipas PROJECT

(VERY EARLY WARNING SATELLITE)

INTRODUCTION ~:

MIDAS will Provide The MIDAS project is aimed toward establish-
early warning 6: ing a reliable, Operational Satellite-borne .
ballistic missile \ missile alarm Capability in the 1962 time Period,
attack, . \ i

‘€apable of detecting ©manations from ballistic
missiles being launched, as the missiles rise
abdye the atmosphere. woe ~

\ CURRENT STATUS
SSRRENT STATUS

\
GENERAL
Flight schedule The MIDAS ight schedule was revised early
revised to permit in the quarter tp realize higher altitude flights
earlier attainment earlier in the development Program, Commencin,

of objectives. with Flight 3, MIbas Satellites will be Jaunched
into circular’ polar brbits of 2,000 nautical miles

altitude. The 1,000 mautical mile orbit flight
has been eliminated, ‘Wlights land 2 remain
unchanged at 261 nautical miles, with Flight 1
scheduled in February, The Slippage reflected
in this date was caused by delay in obtaining
Occupancy of an Atlantic Miskile Range launch pad

MIDAS COMPONENTS

AGENA vehicle The AGENA. second stage vehicle for the first
being prepared at MIDAS flight test vehicle was hot fired at Santa
AMR for first flight. Cruz Test Base (SCTB) on October 2% 1959,

On November 30, 1959, a successful fall-duration

hot firing was Conducted. It is now being, prepare: j

Prepared for acceptance hot firing at Santa Ce, Zz. |