+ October, This equipment will be installed in the Satel-
lite Test Center; a second unit will be installed in the
Vandenberg Air Force Base Tracking station. The
late delivery of the equipment for the Satellite Test
Center wilt not affect the scheduled activation date.
Some revision of the integration activity will be
Fequired; however, this will not affect the MIDAS
launch schedule, Delays in delivering the second
unit of ground station ‘equipment, however, will cause
some slippage in the Vandenberg Air Force Bése
tracking station activation date for support of MIDAS
flights.

Facilities

¢ A detailed evaivation of launch pad require-
ments for the MIDAS Operational phase has been
accomplished. This study indicates the need for a
three-pad faunch complex during the establishment
of the operational network, and a requirement for
from two-to-three pads for maintaining the MIDAS
satellite network once the buildup phase has been
completed.

° Final acceptance of North Pacific station tech-
nical facilities at Donnelly Flats, Alaska, was accom-
plished on 29 September. The heated vehicle storage
building at Fort Greely is scheduled for completion
on 3! October. Completion of the combined dormi-
except for exterior area
on 30 December. The

tory and dining hall facility,
Grading, will be completed

Figure 8. jouw

Overall siew of the MIDAS
fustalied in the Satellite ‘th Center, Tl

oscillograph egnipment. The egsiproen,
recorder tenable, TO cesiom

Donnelly Dome microwave relay station is scheduled
for completion on 15 December. Beneficial occu-
Pancy of the remaining North Pacific communications
stations is programmed for 1 January 1961.

e All New Boston station support facilities located
on Grenier Field, New Hampshire, were completed
and accepted during the report period. Support facil-
ities on the New Boston station are on schedule.
Design of the data acquisition and processing
building modification has been completed and a
construction contract is Presently being negotiated.
Completion is scheduled on an incremental basis
with final completion scheduled for 1 Janvary 1961.

ripment: currently
be hed ons bonter ks
tucks tn tbe reer Bouse the one

Y

g

“



Flight Test Progress

The TRANSIT.
November has b.
This change was
and ABLE-5B fay

3A launch scheduled for early
een rescheduled to 29 November. © The ABLE-STAR vehici
tequired because the COURIER 1B
inches have created a launch sched.
@ launch-of TRANSIT 3B is scheduled

for 21 February 1961: and TRANSIT 44 for .May

“CONFIDENTIAL

MONTHLY PROGRESS — TRANSIT © The mobile trackin;

'g station has been moved from

Salisbury, Southern Rhodesia to Pretoria, Union of
South Africa. The station Was operating and success-

fully tracked the COURIER 1B flight.

is currently undergoing
Force acceptance. The
shipped to the Atlantic
The THOR booster for
system checkout prior

le for the TRANSIT 3A flight
final checkout prior to Air
vehicle is scheduled to be
Missile Range on 21 October.
this flight is undergoing sub-
to being installed on the stand,

WDLPM-4.245



-CONFIDENTIAL-

Sateliite Vehicle

© Test and checkout of the ABLE-5B satellite
vehicle wos completed on 27 September. Initial
magnetic field background and source checks were
accomplished at the Fanselan facility located in
Malibu, California, on 30 September. Vibration tests
on the vehicle are scheduled to begin on 3 October.
Following completion of the thermal vacuum environ.

WDLPM-4.245

mental acceptance tests the vehicle will be delivered
fo AMR on 4 November,

Guidance and Controt

© The Hughes Advanced Guidance System com-
puter was delivered on 14 September following the
completion of acceptance testing. Peripheral equip-
ment installation and checkout was complete at the
end of the report period,

CONFIDENTIAL bat


MANNED SATELLITE

- RETRO & POSIGRADE ROCKETS
=

7 — 4 a

aH

is HORIZON SCANNER

- ROCKET

PITCH & YAW JETS

~
a
WEIGHT AT SEPARATION 2,500 Ibs ORBITAL CYCLES 3-18
a ORBITAL ALTITUDE ORBIT INCLINATION 33 Degrees
i APOGEE 126 N. Miles § HEAT SHIELD Ablative

* PERIGEE 94. Miles § RECOVERY Water or Land

it Figare 1. Complete vebicle (top view) with satellite installed on ATLAS booster. Manned satellite

we (bottom view) showing pilots’ fight position, end detail views of retro end posigrade rockets and pilot

Safety system escape rockets.

WDLPM4.245 CONFIDENTIAL 1



! ENTER ELLIPTICAL ORBIT
E OF

a
s

7

COAST ELLIPSE

* AGENA

1st. <

> NMI
SEPARATION &

SHORT COAST

’
¢
K

omy
—:

180° coast.
Neco

2000 NMI.
BOOST: \ y
7
j Cenc soonh bts 3 and subs From : tb, horiao ides atttud
. inch-to-orbit traje ights 3 and subsequent. Z hem, wil 130% Scanner, ides attitude,
boost through vepaton aoe and control is led. Sian ‘ae directional control 10 establish the orbs and
by the ATLAS radio inertial system. The AGEN. vebicle orientation,

Figure 3.
Propowed MIDAS

System. Four satellites spaced equidistant in each
Planes at 2,000 n.m, altitude, Provides maximum

two orthogonal
a Esse with minimum number of satellites,

coverage of

B2

PROGRAM HISTORY

The MIDAS Program was included in Weapon
System 117L when WS 117L was transferred
fo the Advanced Research Projects Agency,
ARPA subsequently separated WS 1171 into
the DISCOVERER, SAMOS and MIDAS Pro-
grams, with the MIDAS objectives based on
an infrared reconnaissance system. The
MIDAS (Missile Defense Alarm System) Pro-
gram was directed by ARPA Order No. 38,
dated 5 November 1958 until transferred to
the ‘Air Force on 17 November 1959. A ten
launch development Plan for MIDAS (WS.
239A) has been approved. Additional author-
ization has been obtained to utilize wo DIS-
COVERER flights (designated RM-1 and RM-2)
to carry background radiometers in support
of MIDAS,



WDLPM-4-245

DYNA

Program History—Competition for the DYNA SOAR
study contract was initiated in 1958 nd resulted in

findings were etaborated on by Dr. Charyk to require
@ study program, Phase Alpha, with objectives of |
reaffirming the Proposed glider design ond indicat.
ing any changes required to that design. In April

Uft Off Weight

Burnout Weight

Ignition prior to

Stobilizing Fins

Figure 1. DYNA SOAR
drawing and specification

48" 10" —_—

a

Propellant Consumed

c ‘SECOND stags MODIFICATIONS

Propellant Tanks Copacity Increased
Intertank Section ‘Strengthened
HIRST STAGE MoDINCATIONS

‘Skirt Section ‘and tntertank
Section Modified and Strengthened

SOAR

1960, the Phase Alpha study was completed and the
results were presented to the Department of Defense,
On 9 May, formal Spproval of the DYNA SOAR Step
| Program was received by AFBMD/BMC from
WADD/ASC,

Program Objectives—the DYNA SOAR Program will
explore the Possibilities of manned flight in the

|, a full scale, minimum sized manned glider will be
developed. A modified version of the TITAN ICBM
will boost the glider into hypersonic flight at veloci-
ties up to 19,000 ft/sec and permit conventional

lie'l/e”

Separation

Added

tebicle configuration
fia,

SaCREP...


Figure 4. The fess Jannch
sari fess 609A

tories on Chews ves be
XRM-91 prey fe fulton (top),
the instant oj rst stage ‘gntlog

(center), ie missile movin
hs the jazgee sail (lower, oie
load umbilical visible on
the Es of the second stage, The
as Seon, 1 ie nk cop site page)
vail hand
m $ ‘in fin nebo motors bave
just been ignited.

Ha



NASA
-AGENA “Bp”
PROGRAM

‘SPACECRAFT

AGENA “8”

Program will also di
capobility of the AGENA “B" retro system to retard
the second stage. To achieve these objectives the
experience gained by the Air Force in designing
equipment, developing techniques and Preparing
Procedures for launch spacecraft will be utilized.

levelop and demonstrate the

WDLPM.4245 CONFIDENTIAL x


“WDLPM-4-245

seener-
SAINT

e Project SAINT is a program for the development
Of @ satellite inspector system. The initial effort is
concerned with the design, fabrication and ground
launch of a reliable Prototype vehicle to demon-
strate the feasibility of satellite rendezvous and
inspection. At the same time, studies and analysis
will be undertaken to define the configuration of
the system. Development effort on certain long lead
components required for the system will be included.
The program is being conducted by AFBMD under
System Development Requirement No, 18, 21 April
1960,

Program Objectives

© Design a Prototype interceptor vehicle utilizing
fOnservative choices of subsystems and a deliberate
step-by-step development progression, emphasizing
reliability and component compatibility. Conduct a
feasibility demonstration of the rendezvous and
inspection capability after ground tests have given
assurance of system reliability. The flight demonstra-
tion will utilize an existing target satellite if one is
Property orientated, otherwise @ specially launched,
Passive, target satellite will be utilized. Conduct
studies to determine the configuration and techniques
of operation of the eventual system,

@.. Develop and ground test the critical subsystems
required for the system but not Provided in the
demonstration Program. These include a rendezvous
maintenance system, additional inspection and data
Processing equipment, an integrated launch and
homing guidance system, an advanced power sup-
ply and ‘selected ‘countermeasures equipment.

Satellite Inspector Feasibility Demonstration

©@ The Satellite Inspector System will provide a cap-
ability to intercept and inspect unidentified earth
satellites which theéaten the United States. In the
demonstration, the Prototype inspector vehicle will
achieve a co-orbital rendezvous to within some fifty
feet of the target setellite, obtain on image of the
target through ifie TY System ond relay the image to
@ ground station. The inspector vehicle will be sized
and components selected so that imuch of the design
might be applicable to the initial system which
will be developed following a successful feasibility

“—Sreha—

demonstration. Major subsystems of the interceptor
vehicle are: maneuvering propulsion, radar seeker,
guidance, TV inspection, computer, communications
and telemetry, attitude control and electrical power.

© A total of four launches ‘are planned from the
Atlantic Missile Range, with the first launch in Decem-
ber 1962. The SAINT vehicle includes an ATLAS
booster, an AGENA “BY second stage and the ren-
dexvous vehicle which weighs Gpproximately 1800
Pounds,

© The demonstration Program will utilize existing
launch, tracking, and date reduction facilities insofar -
5 possible. There will be requirements for additional
Sound support equipment at the Atlantic Missile
Range and augmentation of the southeast: Africa
Tracking site to handle the telemetry and communi-
cations requirements for the demonstration. The tar-
Get ephemeris will be determined for the demonstra.
tion program by tracking data from existing FPS-16
Gnd Millstone Radars,

Satellite Inspector System

© Following the successful feasibility demonstra-
fion of a Prototype satellite inspector, continued
development couid lead to an operational system.
The complete system will provide a considerable.
increase in copability. For exemple, rendezvous
would be maintained for a period of 48 hours to
allow sufficient time to evaluate the sensor data.
Additional sensors such as ferret, IR, X-Ray detectors,
magnetometers, etc., will be included in the payload.
Orbital altitude coverage will be extended to at
least 1,000 nautical mites and the reaction time will
be reduced to 12 hours Gfter the target ephemeris
has been determined. The system will comprise a
complex of launch facilities, Ground support equip-
ment, ossembly and launch checkout equipment,
boosters, launch guidance equipment, rendezvous
vehicle, telemetry and command and control subsys-
tems, ground communications stations, together with
any necessary technical manuals, procedures ond
Personnel required to support the system. The launch
vehicle may be an ATLAS first stage with o CENTAUR
second stage,



‘CONFIDENTIAL-

by ong range planning and maximum integration
with other programs. Use of the basic four-stage
solid propellant, SCOUT vehicle, developed by NASA
and modified to achieve Program 609A objectives,
will affect an economy in vehicle development.
Necessary modifications include provisions for sta-
bilizing the fourth stage without spin and use of the
vehicle in less than the full four-stage configuration,
Close integration with the current ballistic missile
Program will effect an economy by permitting tests
and experiments to be conducted on regularly sched-
uled ballistic missile test flights whenever possible
without delaying schedules. Economy in the opera-
tional phase will be exercised by the use of this low-
cost vehicle as a standard flight test platform to
perform scientific and military experimental research
in support of all Air Force facilities. RELIABILITY will
be obtoined by a tweive vehicle R&D flight test
Program, at least four flights of the basic SCOUT,
and maximum use of knowledge gained in prior Air
Force ballistic missile flight testing. VERSATILITY will
be achieved by designing a vehicle capable of being
readily adapted to a wide range of payload varia-
tions, and capable of being flown in several configu-
rations of four stages or less. This VERSATILITY results
in the following flight capabilities: (a) vertical probes
having a wide variance of payload weight/attitude
combinations; (b) boost-glide trajectories; {c) ballistic
missile trajectories; {d) downward boosted, high-
speed re-entry profiles, and {e) full orbit to approxi-

es _

mate maximum of 400 miles with 150-pound
payloads,

Program Management—An abbreviated devel-
opment plan, covering the R&D phase only, was
approved on 9 January 1959. Funds in the amount
of $11,500,000 hove been made available for this
R&D phase of the program only. A letter was issued
assigning management responsibility to AFMBD, with
emphasis on integrating the program with the scien-
tific and military research experiments conducted on
regularly scheduled ballistic missile flight tests (Piggy-
back Program). In June 1959, Aeronutronic Division
of the Ford Motor Company was chosen through nor-
mal competitive bidding as the Payload, Test, and
Systems Integration Contractor. Arrangements have
been made for the procurement of vehicle compo-
nents and associated support equipment, modified
to meet Program 609A requirements, through NASA,
rather than through the SCOUT Program contractors.
Atlantic Missile Range facilities consisting of launch
complex 18 will be made available to the Air Force
for this program. A Project 609A division has been
‘established within the 6555th Test Wing (Develop-
ment) at AMR to supply Air Force technicians to par-
ticipate in the dssembly, checkout and launch
Operations of the R&D phase under the direction of
the Payload and Test Contractor. An all-military
operational capability will be developed from within
this group.

KOVAL

Figure 2,

Fonr differens
os:

different
arrangements
of Project 609A
sages.

WDLPM-4.245



ssener- = -CONDENTHL—

detailed proposal, Following an evaluation of this

© Work is continuing on the Stage |, Stage il and
the rocket engine work statement essential for pro-
urement of the booster vehicles required during the
ATLAS/CENTAUR Phase of the Program.

Final Stage Vehicle

©. A study of the reference problem for final orbit
injection is in Progress for a six-hour inclined orbit

© Representatives of AFBMD,. Space Tech

ries and General Electric pon 14, 15 and
16 September in Philadelphia and held an informal
Genéral program review on the over-all temperature
contro! problems of the Final Stage Vehicle (PSY).
Methods which have been investigated to meet the
temperature contro! requirements were reviewed in
detail as well os the back-up analysis substantiating
the mechanization, The experimental test Programs
being performed in the temperature control area

<> i were’ reviewed and the Proposed temperature
Proposal, the AGENA second stages will be procured. *

contro! system evaluation and checkout tests were
discussed.

© General Electric has given contractual authoriza-
tion to Rocketdyne and Marquardt for Phase |
studies of the FSV Propulsion subsystem.

© Space Technology Laboratories’ FSV preliminary
design drawings were forwarded to General Electric
for information. One of the main differences between
the STL and GE concepts was the design of the
Propellant tanks. The STL: two-tank concept allows
@ more efficient volume utilization of the FSV struc-

, but requires precise Propellant metering from
the two tanks, The GE configuration: utilizes a tank
of greater volume requiring a larger FSV basic struc-
ture. A meeting is Planned to investigate in detail

the center of Gravity shift problems involved In the
two configurations,

18-pound weight saving obtainable by using this
system.

WDLPM-4.245



CONFIDENTIAL

The ARPA COURIER Program consists of two flight
vehicles to be launched from the Atlantic Missile
Range. The program objective is to test delayed
"epeater communications between a satellite and
ground stations, The program also will be used to
determine the Operating characteristics and capa-
bilities of the ABLE-STAR {AJ10-104) second stage
vehicle. The program is being conducted under ARPA
Order No. 98-60 (Project Code No. 2200). AFBMD
responsibility includes development of ‘the Jaunch
vehicle, payload integration, launch, injection of
Payload into orbit, and verification of orbital param-
eters at injection. The Army Signal Research and
Development Laboratory will design, develop and
fabricate the Payload, and will be responsible for
world-wide ground station requirements, Primary
payload contractor is Philco Corporation,

Vehicle Description—the two-stage’ COURIER vehi-
cle consists of a THOR booster, an ABLE-STAR (AJ10-
104) second stage and a 500 pound COURIER
Payload. Booster flight control is exercised by a gyro
Platform and a programmer. The second stage is
controlled by @ gyro used to govern engine gim-
balling during powered flight. Stability during sec-
ond stage coast is provided by the “on-off'*
Operation of jet nozzies operating from a dry nitro-
gen supply. The second stage propellants are inhib-
ited red fuming nitric acid and unsymmetrical
dimethy! hydrazine. The engine will have a restart
capability. The 500 pound COURIER Payload is a
60-inch sphere, containing radio repeaters, storage
and memory equipment, and a battery power source.
Flight Description—Both vehicles are to be launched
from the Atlantic Missile Range. After first stage burn-
out, the ABLE-STAR vehicle will place the payload
into the desired trajectory and then shut down. The
second stage and payload will coast to the desired
650 nautical mile orbital altitude and the ABLE-STAR
-engine reignited to attain orbital velocity. The orbital
inclination will be 28.5 degrees from the equatorial
plane. The orbital period will be 110 minutes.
Payload Objectives—Storage and memory elements
in the payload will deliver messages, upon command,
fo each of three ground stations; as well as exchang-
ing “real time” information when the satellite is
within line-of-sight of two ground stations, During
these periods a ground station can relay messages
direct to the next ground station, through the satellite
simplex repeater equipment.

Ground Support Stations—These stations will be
located at Camp Salinas, Puerto Rico; Torrejon Air
Force Base, Madrid, Spain; and. Halemano, Hawaii.
Station design and development is under contract to
Internationat Telephone and Telegraph Corporation.

79.3!

SIONCICIONC)

SECOND STAGE—ASLE-STAR {AJ10-104)

Thrust at altitude 1090 pounds
Specific impulee (voc} 278 seconds
Total imputee (ssin} 23 X 10° Ibe/sec
Serving Hime” 294 seconds
Propetiont Uguia

FIRST STAGE—THOR imam

Trews (4.19 151,500 pounds
Specific Impulse (0.1) 248 seconds
Specitic impulse (veep 287 seconds
Berning time 138 seconds
Propellant Liquid

WDLPM4.245 CONFIDENTIAL

Fl



Headquorters, United States Air Force

Headquarters, Air Research and Development
Command

Strategic Air Command

Air Force Command and Control Development
Division

Air Force Flight Test Center

Rome Air Development Center

Air Force Missile Development Center
Wright Air Development Division

Air Force Special Weapons Center

Air University

Arnold Engineering Development Center
Air Proving Ground Center

Air Defense Command

Air Training Command

S#CREr-

DISTRIBUTION

58

W

ew 86 ww ew wow LX

Air Photo and Charting Service

Air Force Missile Test Center

United States Air Force Academy

Air Technical Intelligence Center

555th Test Wing

Air Force Ballistic Missile Division (arDc}
Bollistic Missiles Center (AMC)

Assistant CINCSAC {SAC MIKE}
Aeronautical Chart and Information Center
Rand Corporation

San Bernardino Air Materiel Area

6594 Test Wing (Satelite)

1002 Insp. Gen. Group

3415 Technical Training Group

Tactical Air Command

8th Air Force

WDLPM-4-245,

Sether

aA - © iw


The DISCOVERER Program consists of the design,
development and flight testing of 37 two-stage D
vehicles, using the THOR IRBM as the first stage P

booster and the AGENA as the second stage, satellite
vehicle. The program was established early in 1958

e

under direction of the Advanced Research Project's i
Agency, with technical management assigned to

~ sibility was transferred from ARPA to the Air Force Ss

by the Secretary of Defense. Prime contractor for the
Program is Lockheed Missile and Space. Division,
The DISCOVERER Program will perform space
research in support of the advanced military recon-
nelésance satellite Programs,

‘
| AFBMD. On 14 November 1959, program respon-

a- o
PROGRAM OBJECTIVES
| ~- (0) Flight test of the satellite vehicle airframe, pro- v
. Pulsion, guidance and control systems, auxiliary
Power supply, and telemetry, tracking and ‘com-
I _ mand equipment.
(b) Attaining satellite stabilization in orbit,
. (c) Obtaining sotellite internal thermal environment
_ data. r
{d) Testing of techniques for recovery of a capsule
| _ elected from the orbiting satellite. e
le} Testing of ground support equipment and devel-
. opment of personnel proficiency.
| (f Conducting bio-medical experiments with mice r
‘and smal primates, including injection into orbit,
| _ re-entry and recovery. AoeNa AOINA
SECOND stage oan —
Weight
; PROGRAM SUMMARY Inet 1,262 1328 1346
| - Early lounches confirmed vehicle flight and satellite Cried eevipment = rd at .
orbit capabilities, developed system reliability, and Impulve propelionts 6,525 12,950 12,950
; established ground support, tracking and data acqui- Other za marily pail
~. . . " TOTAL WEIGHT 662 15476 15722
| sition requirements. Later in the program, biomedical tnaine MUNEToS XLMBIG07  xiterneo
and advanced engineering payloads will be flight Thrusttbs., vee. 15,600 15,600 16,000

tested to obtain support data for more advanced Spec. Imp.-tec., voc. a7 a 290
SPace systems programs. DISCOVERER vehicles are Burn time-sec. » Wo 0 0

i THOR BOOSTER DM-18 DM-21
launched from Vandenberg Air Force Base, with Weight Dry 4950 6,500
‘overall operational contro! exercised by the Satellite

Fuel 33,700 3700
Test Center, Sunnyvale, California Oxidizer (LOX) $8,200 $4,200

| GROSS WEIGHT {ibs 108,850 108,400
Tracking and command functions are performed by Engine MB-3 MB-3

| ~ the stations listed in the Table on page A-4. A history Thru, fee ty bagel byes
of DISCOVERER flight to date is. given on page A-5, Spec. Imp.. sac. (S.t) uA 248.3

Burn Time, see, 163 us



WDLPM-4-245

Figure 8. The second stage, being rated inte

the (tafe) ing ats with
4TL4S 20D. The ed a
‘ated ie poriign mu figs ai mpi bocce

‘be weight Afirental
abproximately 130 tons,

48 being


The ADVENT Program will investigate the feasibility
of using satellites in synchronous orbit as instantane-
0Us repeaters for microwave radio communications,
A satellite vehicle station in synchronous equatorial
orbit will remain in a fixed Position relative to any
point on the surface of the earth, Active communica-
fions equipment contained in this satellite will receive,
amplify and instantaneously retransmit Gny message
beamed in its direction,

PROGRAM HistORY

The Research and Development program for active
communication satellites was initiated by ARPA in
January 1959, Following early research and develop-
ment, a three-phased development program (STEER,
TACKLE and DECREE) was initiated in May 1959 by
‘Amendment No. 1 to ARPA Order No. 54. Phase |
{STEER} was given priority in order to demonstrate
the feasibitity of Providing an early UHF communica-
tions capability for Positive control of the SAC strike
forces. AFBMD was given fesponsibllity for the
design, development, and flight testing of the com-
plete system, including launch, satellite tracking and
control, and Necessary support facilities and ground
equipment. WADD and the U. S. Army Signal
Research and Development Laboratory (USASRDL)
were delegated responsibility for the development
of the communications subsystem for Phase land
Phases Ht and Ill, respectively.

Figure 3. Proposed satellite with
fisonable fairing “aonioed
Gentace I tage

.
ENSIBENFHip
WDILPM-4-245

|
L

SETTISONABLE
NOSE FAIRING

SCANNI

Un

f—— MICROWAVE
COMMUNICATION
ANTENNA

f—— EARTH HORIZON
INNER

y— SOLAR CELL PADDLE

/ FINAL STAGE VEHICLE

CENTAUR
ELECTRONIC
EQUIPMENT

CENTAUR
STAGE

SECRET

C1



Figure 1, ABLE-3 fighe wat rs

ee being launched from Atlantic Missile Renge.
(left) of four-stage ABLE-3 vebi

Dimensional drawing



ATLAS/AGENA “B""

ADVENT Launch Schedule

MONTHLY PROGRESS —. ADVENT
Program Administration

The Secretary of Defense, by memorandum’ dated
15 September, assigned over-all management
responsibility for the ADVENT Program to the Depart-
ment of the Army. FY 1961 funds in the amount of
$19,108,900, Previously allocated under Amend-
ments No. 9 and 10 to ARPA Order No. 54, have
been withdrawn by ARPA in connection with the
transfer of the program management to the Depart-
ment of the Army.

Technical Progress
Communications Equipment

© Sylvania Electric Products submitted the design
plan for the 60-foot automatic tracking antenna
system for the ground terminal equipment. Approval
of the plan, now being reviewed by Signal Corps
Engineers, is expected during October,

* Technical coordination meetings have been held
with the microwave communications equipment con-
tractor for both the sotellite and ground terminals.
Consideration was given to ADVENT system design
and system problems, satellite subsystem design and
ground communications subsystem layout. The scope
of the design plan to be submitted on 15 October
was defined. It is the intent of USASRDL to work with
the contractor on the plan so that rapid approval
will be possible. A subcontract with Magnavox was
approved for development of the sequence gener-
ator in connection with the ‘anti-jamming equipment.
Meetings have been held with Bendix, Syivania and
General Electric to discuss thermal and RF
interferences.

‘© Contractual negotiations with Varian Associates
for development of a high power, X-band, Klystron
tube have been completed.

WDLPM-4:245,

© Internot laboratory work is being continued to
verify stage-by-stage and total chain performance
of a proposed satellite borne design for the micro-
wave communications equipment. An experimental,
solid state, parametric configuration of an output
mixer and low noise IF input stage has been devel-
ped as a possible replacement for the vacuum tube
triode mixer. Tests indicate that this circuit possesses
more than ample bandwidth, sufficient gain to drive
@ planar triode output stage and also provides hard
limiting, An experimental model of a complete
satellite repeater chain, meeting the requirements of
bandwidth and sensitivities, has been tested. Work
has begun on a laboratory set-up for determining
some of the effects of jamming signals on repeater
Operation in terms of phase distortion and inter-
modulation products. Specific investigations of cir-
cuitry and component application have been initiated
as G result of discussions with Bendix in connection
with the design plan,

° Formal ARPA approval has been received for
the selection of Fort Dix, New Jersey, and Camp
Roberts, California, as the East and West Coast
ground station sites for ADVENT. Soil borings have
been completed ot Fort Dix ond will begin shortly
‘on the West Coast,

Launch Vehicles

© The ATLAS/AGENA “B” Stage | and i! work
statements were approved by ARPA with qualifica-
fions stated in Amendment No. 10, dated 22 August,
to ARPA Order No. 54. On the basis of work state-
ments incorporating revisions directed by ARPA, a
Purchase Request in the amount of $1.0 million was
initiated for initial funding of three ATLAS boosters.
Revised work statements for the AGENA second
stage have been transmitted to Lockheed Aircraft
Corporation with a request for submission of a

SHORET os

—




Sanne,

MONTHLY PROGRESS — minas Program

Program Administration

° AS a result of recent investigations by Space
Technology Laboratories on the significance of the

Flight Tes? Progress

© The vehicle for the third MIDAS flight is currently
in the systems fest phase of checkout. This is the
first MIDAS vehicle to have restart capability, Because

6. A

future MIDAS fighis, Fie nitrogen

£41 cooling system which tools
vadiometer,

Figure back, radi
iSCOV! rbks 1
isc oy si, tay ad

The scheduled taunch date for this flight remains 28
February 1961,

Technical Progress
Second Stage Vehicles

© Assembly of the AGENA “BY vehicies for the
fourth and fifth MIDAS flights is Proceeding on

Infrared Scanner Unite

mente anae ente for Hats 3,4 and 5 oe boing manufac
Geral Caron ond fr Hg 6,7 end 8 hy nenree
Generat Corporotion,

° The infrared detector Paytoa

carried on the third MIDAS flight has been delivered,
Acceptance testing of this payload will be completed
in eatty October, The second fight payload ie vinrey
uled for delivery on 15 October. Two more payloads,
one for backup purposes, remain to be delivered,

© Temperature Profile tests of the engineering test
mode! of the Baird-Atomic configuration are in Prog-

Ground Support Equipment

© Delivery of the initia! Baird-Atomic ground infra-
red data display equipment is scheduled for ts

fometer of she tybe to be cevvied on

-2. 7 function
Melorened roy Foran

ars part of the nitrogen.

the sensitive element of the

ne SEGREF:

WDLPM-4.245


CONFIDENTIAL

NASA AGENA “B" Program Flights

RESPONSIBILITIES
LUNAR FLIGHTS

———— AFBMD

wane Jet Propulsion
Laboratory

EARTH SATELLITE
— - — AFBMD
— —— Goddard Space Flight Center
% =~ Spacecraft injection

WOLPMA.245 CONFIDENTIAL Ks



MONTHLY
Fight Test Progress

DISCOVERER Xv

© DISCOVERER XV was launched from Vandenberg
Air Force Bose at 1515 PDT on 13 September and
was successfully injected into Polar orbit. Two-thirds
of the satellites launched in the DISCOVERER Pro-
Gram have attained orbit. THOR booster trajectory
‘was satisifactory; AGENA performance was nominal.
Propellant exhaustion caused shutdown, rather than
integrator command. A comparison of programmed
and acival orbital parameters is shown in Table |,

VERER Program

PARAMETER NOMINAL ACTUAL
Azimuth, degree 172.0 175.2
Perigee, statute miles 120 129
Apogee, statute miles 410 478
Injection Angle 0 -0.2
Eccentricity 0.0371 ~~ 0,04
Period, minutes 93.44 94.2

TABLE 1, DISCOVERER xv Programmed
Orbital Parameters

© Date received on the first pass over Kodiak and
Hawaii indicated that the satellite was stable and in
correct altitude but that control gas consumption was
excessive. The capsule was ejected on the 17th orbit
but, because of a loss of control gas, the pitch-down
Prior to ejection was not ‘accomplished. As a result,

. the capsule impacted about 1,000 miles south of the
Impact point predicted Prior to capsule ejection. Sub-
sequent analysis indicates that the roll rate gyro was.
not property restraining the rate of satellite roll
movements to the proper frequency. This caused the
satellite to roll between limits faster than normal and
resulted in higher than normal control ges expen-
diture,

© The capsule descent was tracked by the Hawaiian
tracking station until re-entry; a computer run of this
date resutted in a revised impact point prediction,
Aircraft and the recovery ship “Dalton Victory were
dispatched to the impact area. The first aircraft to
reach the area located the capsule by radio beacon
@t 2105 PDT and a second aircraft sighted It thiety
minutes later. Marker beacons, strobe lights, smoke
bombs and aluminum dye were dropped to mark the
area. On the moming of the 15th, @ Coast Guord
amphibian arrived but did not land because of rough
Seas. Because of deteriorating weather and sea con-
ditions, a plan to drop parachutists and a raft was
abandoned.

Aa SEGWEF.

© AtTIVS PDT on 15 September electronic contact
was lost. Fifteen minutes later, the Gircraft lost sight

_ Of the capsule which was then listing ‘and riding low

in the water. The capsule was not seen again
although the search continued throughout 15 and 16
September.

DISCOVERER Xvi

© DISCOVERER XVI is scheduled for launch from
Vandenberg Air Force Base in October. This will be
the first AGENA “B* vehicle to be Jaunched. Vehicle
subsystem and system checks ‘were completed during
September and the vehicle has been installed on the
launch pad. The AGENA “8” is an improved version
of the AGENA “Av containing integral propellant
tanks which form part of the satellite skin and having
double the propellant ‘capacity,

© The increased payload capability of the AGENA
“B” will permit use of extra batteries and contro!
gas required for two, three and four day intervals
between launch and capsule recovery. The recover-
able payload is similar to those flown on DISCOV-
ERER XIV and XV, The ascent Peremeters for AGENA
“BY DISCOVERER satellites Gre markedly different
from previous DISCOVERER vehicles. A comparison
of predicted parameters for DISCOVERER XV and
DISCOVERER XVI are shown in Table tl.

DISCOVERsR Discovensr
xv xvi
(AGENA “A"HAGENA “8"

ASCENT PARAMETERS
THOR Burnout Time,

seconds from liftoff 163 163
THOR Velocity at Burnout,

fps 13,660 10,610
AGENA Ignition Time,

seconds from liftoff 269 237
AGENA Bum Time, seconds 7 240

Injection Velocity, fps 26,032 25,964
ORBITAL PARAMETERS

Apogee, statute miles 410 426
Periges, statute miles 120 130
Eccentricity 0.0371 0.035
Inclination Angle, degree 79.63 81.83
Period, minutes 93.44 93.5

TABLE it. Comparison of Ascent and Orbital
rs for AGENA “A" and AGENA "B”’
Satellites

tua B WDLPM-4.245



CONFIDENTIAL

MONTHLY PROGRESS — ABLE-5.

Program Administration

*° A proposal for on alternate mission for the
ABLE-5B vebide was developed and forwarded to
NASA for consideration. This alternate mission was
designed to complement and increase the value of
the ABLE-5A lunar orbital flight by placing the sec-
ond satellite in an elliptical earth orbit which would
Permit simultaneous measurements to be made by
two identical (ABLE-5A and 5B) vehicles. However,
since this Proposal was contingent upon the success-
ful flight of ABLE-SA, it hes been rejected.

* Negotiations have been conducted with Space
Technology Laboratories for the reduction and
Gnalysis of PIONEER V data and for additional
analysis and reduction of EXPLORER VI data
recorded under weak signal conditions. The results
of EXPLORER V! date reduction and analysis accom:
Plished to date is being completed, with publication
of final report scheduled for 1 October. Completion
of the PIONEER V data reduction and analysis pro-

March 1961,

Flight Test Progress

ABLE-5A Flight

* The ABLE-SA vehicle was launched from Stand
12 at the Atlantic Missile Range on 25 September at
0713 PST. Countdown for the launch was initiated

ow the transporter uses

WDLPM-4-245

on 24 September, but the launch was postponed
because of high winds and unfavorable weather in
the launch area. The final countdown proceeded
smoothly to liftoff, which was normal in all respects.
The flight proceeded as planned through the com-
pletion of first stage operation. Performance of the
ATIAS booster wos excellent with all systems
Operating properly. ATLAS sustainer engine cutoff
occurred at 271.7 seconds after liftoff and Stage I/
Stage II separation occurred 1.5 seconds later.
However, a malfunction occurred in the second
stage propulsion system at ignition, and as a result,
the objectives of the flight were not met.

© Second stage ignition was denoted by combus-
tion chamber pressure fluctuations which occurred
immediately after chamber Pressure buildup. Cham-
ber pressure then stabilized at 60-70 percent of the
nominal value. The data also indicated an abnor-
mally high rate of Propeliant depletion during
second stage buming. Although the exact cause of
the malfunction has not been definitely established,
it is possible that Propellant loss external to the
combustion chamber may have occurred. This could
have resulted in on Improper fuel-oxidizer ratio with
@ consequent reduction in combustion chamber
Pressure and a reduction of second stage thrust.
The reduced performance of the second stage Pre-
vented the attainment of orbital velocity.

© The other flight events apparently occurred as
planned. Telemetry data received from the satellite
vehicle indicated satisfactory performance of the

Flues 6 Spitem chechons of second stage vabicle being performed
jn Milenio Mites Beane aaa The AMEE vehiie rie orormed
the A]10-101 propulsion ‘System,

CONFIDENTIAL br


“CEGaET

ABLE Vehicle

The ABLE Upper-stage vehicle has been flight tested suc-
cessfully as the second stage on THOR re-entry vehicle

ABLE Projects and TRANSIT 1A. The vehicle uses
AJ10-42 of AJ10-101 Propulsion systems {improved
versions of systems used originally on the Vanguard
Program), guidance systems, and electronic and instru-
mentation equipment. The ABLE vehicles are guided
during second stage ‘engine buming. Vehicles using the

Contracter:

‘Acrojet-General Corp,

Height 18 feet 7 Inches
Diameter 4 Gost & Inches
Weight

Ano42 4622 pounds
AJ10-10) 4178 pounds
Fool

Unsymmetrical Dimethyt Hydrazine

ee —

Development of the Allegany Ballistics
laboratory X.248 engine for the Van-
guard Program was accelerated when it
was selected as the third stage for Project
ABLE-1. The unit represented the most
advanced solid Propellant engine of its
size available at the time. Since the
engine had not been qualification or
flight tested, test firings were conducted
In a vacuum chamber simulating approxi-
mately 100,000 feet altitude. Design
modifications involving the igniter,
nozzle, and internal insulation were
found to be required. The modified
engine performed with complete satis.
faction on the successful flight of ABLE.1
and subsequentiy on ABLE-3 and ABLE-4
THOR,

AJ10-101 system are spun with the third stage and pay-
load prior to second stage engine burnout to provide spin
stabilization of the unguided third stage and payload,
‘On flight vehictes using the AJ10-42 Propulsion system,
only the third stage and payload are spun prior to second
stage separation by a spin table bearing system located
at the second to third stage seperation plane. Only minor
differences exist between the two proputsion systems,

‘Oxidizer
Inhibited White Fuming Nitric Acid

Guidance

AN1042

Radie-inertiot (BTL)
A10-201

Advanced Guid, Syst. (STL)
Computer (urroughs J-1)
Used as second stage fer:

AN10-42 — TRANSIT 1A, TIROS,
AJ1O-101 — ABLE 3 and 4

ABL 248
Vehicle

Contractor:

Allegany Bofiistle Laboratory
Height 4 feet 10 inches
Diameter 1 foot 6 inches
Welgt 518 pounds
fet Solta

Used 0 third stage on:
ABLE 3 ond 4

TRANSIT 1A, TIROS



Altitude—noutical miles
a

Abi

T :
THOR/AJI0-42/401 248 3000 | THOR/ASIO-101/a80 248
2000
1000
800
600
L 1 r 1
400
L ? L ,
200
t. rm 1 L L a] i i 1 L L L.
2 4 é 8 10 12 2 4 6 8 10 12
THONALIONIO4 3000 . THOR/AGENA “a” ond “
2000
1000
bE F 4
800
E E ;
: 600
L 1 L
400
L 2 L
3
200
1 . i 1 1 1 1 4. 1 1 i
2 4 é 7 a 10 12 2 4 6 8 10 12
Paylood Weight x 300 pounds Poylood Weight x 100 pounds

1. Polar—AMR or VAFB
2, AMR—90 degrees
3. VAFB—AGENA “A

MS

4. VAFB—AGENA “B” (xERS) -Ba-7)
5. VAFB—AGENA “pr (XLR61-Ba-9}



f§

T T T
| ATLAS/AGENA “A” ang “gr — “\ ATLAS/As10-104/h51 248 ~

fo3

NAUTICAL MILES
3
VA

|
fs :
5 q ad 3
< 400 3
400 FI
34 co 3s 40 a
800, T 3
200 ATLAS/AJ10-101 /ABL 248 — |
‘ 2 3 4 5 600) 8
4 §
2 ATLAS/ MERCURY 8
= 1000 5
= 400
3
5 N
so
] 10 XY
wo
Q
R 200 00 AN
3 100) 3 NX
PAYLOAD WEIGHT x 1000 POUNDS BURNOUT VELOCITY —FPs x 1000
1. AGENA “A"— Polar Orbit 4. Lunar Probe
2. AGENA “BY— Polar Orbit 5. Venus Probe

3. AMR—90 degrees

WDLPM-4245 SHORE mr


‘CONFIDENTIAL

fon Chamber and Geiger-Muller Tube —fiux and
rate data for electron Particles (greater than 1.25
Mev per particle) and Proton particles (greater than
20 Mev per particie).

Proportional Counter Experiment— measure inte-
grated intensity of cosmic ray particles: electrons
(greater than 12 Mev per particle) ‘and protons
(greater than 75 Mey Per particle).

Spin Search Coif Magnetometer and Phase Com-
Parator—map the magnetic field {normal to vehicle
spin axis) and investigate very low frequency secu-
lar magnetic field variations. Phase comparator cir-
cult uses Spin Search Coil and Flux Gate inputs to
determine magnetic field direction, relative to iner-
tial space.

Flux Gate Magnetometer— measure magnetic field
Parallel to vehicle spin axis,

Micrometeorite Flux and Momentum Experiment
—count impacts of micrometeorites and interplane-
tary dust particles on two differing thresholds.

Plasma Probe Experiment— measure the energy
and density of streams of Protons having energies
of the order of a few kilovolts Per particle.

Low Energy Scintillation Counter—measure the
flux intensity of electrons above 50 Kev and protons

Ground Support Program

Atlantic Missile Range— track vehicle for first 12
hours after launch {except for o three hour period
starting a few minutes after liftoff, provide ATLAS
guidance, provide first vernier correction for pay-
load

Manchester, England — tack vehicle for 6 hours,
starting 13 minutes after launch, Provide second
vernier correction for Payload stage (end additional
corrections as required),

South Point, Hawali—track vehicle for 11 hours
starting 6 hours after launch, transmission of com-
mands, including vernier corrections as Necessary,

Other support stations that will track and record
data from the vehicle during periods of tracking


1 Powered Flight Trajectory : dn, — woe avis pines

2
chittude controied by

fm. dewnrange, cont ted by ner

lets. Receives AGENA time to fire and

Comat Period Ferled-—2.4 minutes duration, to 380 |
revetion
J Reed age ows a

ll
a

Orbital Trajectory

for abs dail on ees

each bation ead iting of equipment nied by Cat aoe?
is given om page A. 4

aha the nose section oot the
A vebich, Ejection is med
Pe occer on omen on ihe 171b orbit,
fer capsule impact within the Predeter.
—— mined recone a tes soxth of Hawaii,
and surface vessels ave deployed
ame the area as a recovery force.

tion command is seat to ibe satellit the

hs, “es comme on theses ib orb The ookice 2
reorients iss position (see inset) 10 tion Paes Occur
ete reiaity teajeciory on the 17 eb Th ae

activated at about 50,000 and
ia irati « radio whereas signal for tracking purposes.
recovery force is recovery (impact



Telemetry ships are positioned as required by the
specific mission of each flight. Figures 2 and 3'show
& typical launch trajectory from Vandenberg Air
Force Base, and figure 3 shows schematically a typ-
ical orbit. An additional objective of this program is
the development of a controlled re-entry and recov-
ery capability for the payload capsule (Figure 4).
An impoct area has been established near the
Hawaiian Istands, and a recovery force activated.
Techniques have been developed for aerial recovery

- by C-119 aircraft and for sea recovery by Navy
surface vessels. The recovery Phase of the program
has provided advances in re-entry vehicle technol-
ogy. This information will be used in support of more
advanced projects, including the retum of a manned
satellite from orbit.

FLIGHT VEHICLE

The three versions of flight test vehicles used in the
DISCOVERER Program are defined in the launch
schedule shown on page A-5. Specifications for the
two THOR configurations and three AGENA configu-
rations used are given on page A-1.

AGENA VEHICLE DEVELOPMENT

The AGENA vehicle was originally designed by the
“Air Force as the basic satellite vehicle for Advanced
Military Reconnaissance Satellite Systems Programs,
Basic design wos based on use of the ATLAS ICBM
as the first stage, ATLAS trajectory characteristics and
the stringent eccentricity requirements of the
edvanced programs led to the selection of a guid-
‘ance system suited to achieving orbital injection in a
horizontal attitude. As a result, an optical inertial
system was developed for vehicle guidance .and a

SAMOS ond MIDAS
AGENA VEHICLE

A2

PERFORMANCE

CAPABILITIES

200~ 20,000 MILES
ATTITUDE
ROLL ~ 0.1 DEGREE

PITCH ~ 0.1 DEGREE
YAW ~1 DEGREE

SECRET

AomiA ve"
Aone “ae

al

/7~FUEL_AND
OxXIDIZER

LM
SPHERES

ULLAGE ROCKETS

ene (UoMH)
Gas jet system for orbital attitude control, An urgent
need for attaining higher altitude orbits resulted in
development of the AGENA "BY versions. The YLR81
Ba-5 version of the LR81-Ba-3 ‘engine (Bell Hustler
engine developed for 8-58 aircraft) is used on
AGENA “A! vehicles. The YLR8}-Ba-5 version of this
engine was developed to provide increased perform-
ance through the use of unsymmetrical di-methy!
hydrazine {UDMH) fuel instead of JP-4, .

Early AGENA “B" vehicies will use the YLR81-Ba-7
version of this engine. The majority of AGENA "BY
vehicles will use the XLR81-Bo-9 engine incorporating
@ nozzle expansion ratio of 45:1, and providing a
further increase in performance capability including
‘engine restart and extended bum capability.



WDLPM-4-245

B7


A. THOR—DM-18 7 AGENA "A"

B. THOR—DM-21 / AGENA “8 C. THOR—DM.21/ AGENA "'B!
MB-3 Block 1 / XLR61-Ba-7 MB-3 Block2/ XLR61-Ba-9

A Failed to aitain orbit,

Flight History
aio Sa —
0 10ly 1 2 959 AGENA destro: L
SOB mony 1059 16 ord maa
1 1022 16328 February Aeciged orbis seccsstally, Tolemetry received for 514 seconds after
. of.
" 1018 70 4 Atscinad orbit successfully. Recovery capsale ejected on 171h
9 April ‘ues not recovered. aos ceey ttd we 18 obi
W 102 1 , i and boos ful. Failed
wo fe ath et pemi td e  me
Vv 1023 179-25 June Same as DISCOVERER til,
v 1029 19213 August all tictines secesfaly achieved except capsule recovery after
vi 1028 200° 19 August Same as DISCOVERER V.
vil 1 Misained orbis fully,
051 206 7 November Sitcom ober l back of 400-cycle power prevested sta
vill 1 Attained orbis , Prevented AGENA engine
HN 10580 21220 November indo ited obta wlcig ggemtd AGENA entne
‘NOt recovered,
x 1 THOR shut down prematurely. Umbilical did not retract,
052 2184 February 1960 Quek dienes ere tating lor of bellem prosasea *2% Pere
x 1054 22319 February THOR destroyed at T plas 36 sec, by Renge Safety Officer.
xt 1055 234 41 f Attained orbit } Recovery capsule ejected on 17th orbit
3 5 Apri was mot recovered. tat, peooen except recomery mevessfel
achieved.
xl 105: Launch , i orbital ignis
Se NC ema tag wl tn wn
during orbital sage boost,
xit 1 ed orbit 4 aj it
057 231 10 August heat ork vt success ie Recovery So sade cece gs 17th orbit
objectives except the airborne recovery were iuccessfully achieved.
xiv 1056 237° 18 August (tecined orbis successfully. Recovery capuate ejected on the 171b orbit
iad way Secepaly tccoced If aceon objectives
successfully achieved.
xv 1058 246 13 September — Autainad orbit saccessfally, Ejection end recovery sequence were
. Capsule is the 5; located
tion or blr at
wus SEGRET as



BOOSTER

Support programs

BOOSTER SUPPORT PROGRAMS

ABLE

TRANSIT

COURIER

MERCURY

. 609A
DYNA SOAR

NASA AGENA "3"



my

EXEMPTED FROM DECLASSIFICATION IAW BO, 12958

I PAGES EXEMPT



“CONFIDENTIAL

PROJECT MERCURY

NASA Responsibility

Booster-Capsule integration
Capsule
Ground support
Recovery

Flight 1 Flight 2 Flights
| (canceled) = 3-16

NASA

Flight
Laboratory Copsules
Capsule (McDonnell)
Re-entry
heating,
dynamics,
recovery

Unmanned non-orbital fights
Manned and unmanned orbital flights
Launch from AMR
Earth track 33°N/33°S/Lat. (for orbital
flights)
3-18 orbits
Orbit altitude:
Apogee 126 a.m,
Periges 94 nm.
Automatic pilot safety equipment with
manual backup

AFBMD Responsibility

Booster
ATLAS “D""

|

Modified

INew guidance antennae

Thin skinned tanks

Shifted tonk bulkheads

Light weight thrust structure
Capsule separation mechanism
Interface electrical connections
LOX dome protection
Programmer Modified

Range safety destruct time delay
Abort-sensing system,

Detects dangerous variations
Launch in tank pressures, fuel injector
Pressure, electrical power,
Gttitude and sustainer hydraulic
pressure. Can initiate escape
sequence

Integrated countdown— including pilot insertion
and capsule countdown. AMR launch Stand 14—
@dapted for pilot and capsule.

GE ground guidance equipment modified to
Provide: (a) real time data, {b} additional discrete
command signals during powered flight.

(a) Ballistic trajectory—108°
{b} Orbital trajectory—072°

Table 1. Outline of NASA and AFBMD responsibilities in PROJECT MERCURY,

WDLPM-4-245

CONFIDENTIAL os


Technical Progress

Second Stage Vehicles

© The results of an investigation into system and

equipment performance on DISCOVERER XV were
Presented on 20 September. The presentation
included analysis of the various Problem areas
encountered; action taken to improve test Procedures,
inspections and equipment specifications; and action
to incorporate improvements in DISCOVERER Xvi.

© The XLR-81Ba-9 engine (serial No. 307) was
fitted with a new thrust chamber and subjected to a
full duration colibration run, The 240 second firing
was completed without ‘appreciable nozzle throat
erosion, using a titanium uncooled extension which
had previously completed a five day humidity test.
The nozzle extension was in excellent condition fol-
lowing the firing. This test completed the Preliminary
Flight Rating Test for this engine which is now being
Prepared for re-acceptance inspection prior to ship-

ment to Arnold Engineering Development Center for
reliability testing,

Pignre 2, Aig Porce techniciens adjusting
electronic checkout equipment during
ile The ante Cate, AGENA
a by is
ihe Vandenberg die Ponce ase it
cently battle
ss

Figure 3, Change-over AGENA "A" 10 AGENA “B” ig the missile
on

Vandenberg Air Fi The AGENA "A:' on she sight, DISCOVERER 37 par =

‘once Base. w right, is ich was

bed 13 Se r. O31 AGENA "4" be On she is the
ACENA sll eo ner ACE October x Discov ER Sp"

ss Steuer. Matra



Figure 1. DISCOVERER XV oie to lam

rb om 13 Se r. The trans.
of the THOR booser is lowrred tor ieee te,
mt im the right background. The wo nitrogen storage
bydeo- pneumatic trailer ese shown on tbe ight,

SaentT—



CONFIDENTIAL—

NASA
SPACE LAUNCH
FUGHT PROGRAMS OFFICE VEHICLE PROGRAM OFFICE
JET PROPULSION MARSHALL SPACE
LABORATORY FLIGHT CENTER
GODDARD SPACE
FLIGHT CENTER AFSMD
AGENA ATLAS THOR launch
Contractors Contractors Contractors Operations

NASA AGENA “BY Project Organization Chart

Flight Program—Although it Is intended that this
Program wil continue for Several years beyond
1962, only the launches through 1962 are firm,
The current schedule is as follows:

Launch Date Booster Mission

July 1961 ATLAS Lunar Test Vehicle

October 1961 ATLAS Lunar Test Vehicle

January 1962 ATLAS Lunar Impact

March 1962 THOR Scientific Satellite

April 1962 ATLAS Lunar Impact

April 1962 THOR Meteorological Satellite

duty: 1962 ATLAS Lunar Impact

July 1962 THOR Backup

October 1962 THOR _ Meteorological Satellite

Note: Lunar flights will be launched from the Atlantic
Missile Range; all others will be made from
Vandenberg Air Force Base.

Program Responsibilities—Under NASA Order
No. $4601-G the Air Force is supporting the NASA
AGENA “BY Program. This will permit NASA to take
full advantage of the technical and perational back-
ground and experience developed by the Air Force
in space booster Projects; permit contractors to dis-
charge their contractual obligations with NASA and

Ka “CONFIDENTIAL

USAF utilizing already established management reia-
tionships, insofar as Pratticable; ond provide NASA
the benefits of contract @dministration services and
Procedures already established for USAF Programs
employing the same basic vehicles os those sched.
uled for this Program.

Program Status—AFBMD has taken the following
Getion to support the NASA AGENA "BY Program:

1, Awarded Lockheed Missile and Space Division
@ Contract {letter Contract -592) dated 12 Aprit
1960) for the procurement of modified AGENA
“B" second stage vehicles, jettisonable spacecraft
shrouds, overall systems engineering and vehicle
launch,

2. Issued a contract change ‘notice to Convair
Astronautics for five modified ATLAS “D" boosters
fo support the lunar flights.

3. Allocated eight THOR boosters 10 NASA.

. Initiated contractual action with General Elec-
tric and Bell Telephone Laboratories for guidance
systems to be used on the ATLAS and THOR boosters,
respectively.

5. Published the Program requirements document
setting forth the requirements to be imposed upon
the Atlantic Missile Range to support this Program.

WDLPM-4-245




be
tice ce fom the west

fat fe ibe
Be,
jaring crection



“CONFIDENTIAL-

PROJECT MERCURY
———

a

AFBMD Responsibility
in support of
PROJECT MERCURY
NASA HS-36
includes:

Design, engineering studies

Launch support
Equipment modification Trajectory data
Hardware fabrication Missile allocation
Flight scheduling
Provide sixteen (16) Modify boosters for NASA prelim- Launch, control and define trajectories
ATLAS boosters. inary research and manned orbital of booster-capsuie vehicle up to, and
flight and safety objectives. including, injection into orbit.

Table 2, AFBMD responsibilities in support of PROJECT MERCURY.

Project MERCURY Launch Schedule


‘CONFIDENTIAL

Our knowledge of space, of the sun, and of the solar
system has been substantially increased by the infor.
mation transmitted by PIONEER V. Analysis of the
data obtained during the satellite's journey into
space has revealed the following major scientific
discoveries:

1, An interplanetary magnetic field exists with a
steady magnitude of more than one Gamma
and @ peak of up to ten Gamma. This field
fluctuates in a manner that is connected to
solar flare activity.

2. The planar angle of the interplanetary mag-

+ netic field forms a large angle (about 90
degrees) with the plane of the elliptic,

3. The exospheric ting current of 25,000 miles
diameter encirctes the earth as a giant dough-
hut at a distance of 40,000 miles from earth.
The five milion ampere Current moves west-
ward around the earth,

4. The geophysical magnetic field extends at
times to 65,000 miles.and this field oscillates
in intensity in the outermost exosphere,

5. The sudden decrease in galactic cosmic rays
{the Forbush decrease} always associated with .
large solar flares does not depend on the
Presence of the earth's magnetic field. This
Unexpected discovery will require formulation
of a new theory to explain the Forbush
decrease,

6. Penetrating radiation in space is not limited
to the Van Allen belts. At least during periods
of solar activity 5 to 50 Roentgens per hour
Gre incident on the satellite.

7. Energetic particles in the Van Allen radiation

wind. Some process for particle acceleration
must exist in the belt,

ABLE-5

The ABLE-5 program provides for faunch of two
ATLAS-ABLE vehicles to Place satellites into lunar
orbits late in 1960, A Proposed ATLAS/ABLE lunar
Program wos submitted to AFBMD by NASA on 4
February 1960, following discussions between
AFBMD end the NASA Goddard Space Flight Cen-
ter in January,

Program Objectives

1. Place a satellite into lunar orbit with’ on apo-
lune of 5,000 nauticat miles and perilune of 3,500
nautical miles,

WDLPM-4.245

2. Maintain adequate eorth-satellite communica-
tions and esteblish communications parameters for
future space probes.

3. Demonstrate effective guidance system per-
formance, Particularty for the satellite vehicle.

4. Successful conduct of payload: experiments.

Program Vehicie (Figure 1.}

First Stage —ATLAS series D missile General Electric/
Burroughs Corp. Mod 3 guidance system,

Second Stage— ABLE vehicle with Aerojel-General
AJIO-101A Propuision system,

Third Stage— Allegany Ballistic laboratory ABL-248
solid propellant rocket, unguided, spin stabilized by
spin rockets fired at termination of second stage
thrust,

Fourth Stage (Satellite Vehicle) — Space Technology
Laboratories designed, Incorporating an injection
rocket -capeble of being restarted four times to
increase payload velocity and two times to decrease
Payload velocity, The satellite also contains a telem-
etry system (capable of continuous operation), four
solar cell paddles, and scientific equipment for con-
ducting the experiments, Satellite vehicle weight is
380 pounds.

Launch and Powered Flight

Thete vehicles will be launched from the Atlantic
Missile Range on a true azimuth of 93.5 degrees.
ATLAS performance parameters have been based on

Orbital Characteristics

Major Axis... .., +++ 0.25211 x 10* feet
Eccentricity... 0.1899 degree
Orbital period . ++++1,008 minutes
Apolune .. ++++++4,937 nautical miles
Perilune .. ++++3,361 nautical miles
Duration of eclipses ......... less than 90 minutes

Scintillation Counter and Pulse Height Analyzer

—Measure electron energy (greater than 100 Key
Per particte) and proton energy (greater than 2.0
Mev per particle).

. a


Although originally designed as the basic sat.
ellite vehicle for the Advanced Military Satellite
Programs, fight testing of the AGENA was accel-
erated when the DISCOVERER Program was
created, using the THOR/AGENA combination,
Because of its availability, the Bell Aircraft
LR81-Ba-3 rocket engine was selected for AGENA,
Propulsion, and later modified to use unsymmet-
tical di-methyl hydrazine instead of JP-4 fuel.
Subsequent modifications resulted in the AGENA
“B” configuration, in which Propellant tank
capacity was doubled and the engine modified
to provide single restart and extended bum capa-
bilities, The increased Performance of this design
greatly enhanced the potential of the THOR/
AGENA combination. An optical inertial system
for guidance and orbital attitude contro! was
developed to meet the critical orbital ‘eccentricity
and aititude requirements for the Programs in-
volved. Gas jets and reaction wheels are used
to control attitude. Payloads may be installed
on the forward equipment rack or distributed
throughout the vehicle. The flight test program

from the orbiting satellite.

The ABLE-STAR Upper stage vehicle contains an AJ10-104 propulsion system which
an advanced version of earlier Aerojet-General systems. In addition to Providing
increased performance capability, the system includes automatic starting, restarting,

be extended by increasing the nitrogen supply.

WDLPM-4-245

AGENA

Prime contractor:

Lockheed Missile and Space Division

Engine manefacturer:

Sell Aircraft Corp.

American Aviation

Length

“A” version 14 feet

“B" version 19-5 teet®
21 feat**
inches

7,987 pounds

14,800 pounds
YURG1-80-5
XLR81-80-7°
XLRB1-Bo-9"*

Feel
Unsymmetrical Dimethyl Hydrazine

Onidizer
Inhibited Red Fuming Nitric Acid
Guidance optical-inertial

Used as second stage for:
DISCOVERER

SAMOS

MIDAS:

NASA/AGENA “8”

ABLE-STAR Vehicle

Contractor:
‘Aarojel-Genieral

Height 14 feet 2 inches
Diameter 4 feet 7 Inches
Weight 972 pounds
Engine As10-104

with Restort Capability
Nozzle Expansion Ratlo—40.1

Feel
‘Unsymmetrical Dimethyl Hydrozine

"Oxidizver

Inhibited Red Fuming Nitric Acid

Guidance
STL ABLE Guidance System
Berreughs J-1 Compyter

Used as second stage for:

TRANSIT 18, 24, 3A, 38, 44,
COURIER 1A, 1B

M3


&

| |
— GROUND SUPPORT FACILITIES |
4
to Facility Equipment* : Flight Function |
Satellite A Over-all control, convert tracking stations data to obtain a pre- |
~ Test Center dicted orbit and generate subsequent ephemerides issue aequi-
sition data to tracking stations for subsequent passes, predict
recovery data, . |
i Vandenberg AFB BCDEFGHIJK Launch, ascent and orbital tracking, telemetry reception, trajec-
4 : fory measurements including time to ignite second stage. .
be |
‘ Point Mugu BCDEFGHUKL Ascent tracking and telemetry data reception, transmits com-
mand to ignite and shut down AGENA {via guidance computer),
- Telemetry Ship DF Final stage ascent tracking and telemetry data reception. |
++ (it. J08 E. Monn) ;
_. New Boston, BDEFGHIIK Orbital tracking and telemelry data reception, |
New Hampshire :
(tracking station)
~~ Kodiak, Alaska BDEFGHIJK Orbital tracking and telemetry data reception, including first pass |
(tracking station} acquisition, recovery capsule ejection and impact prediction.
_ Kaena Point, BCDEFGHUK Orbital tracking and telemetry data reception. |
Oahu, Hawaii :
(tracking station}
Hickam AFB Over-ail direction of capsule recovery operations. |
Oahu, Hawaii
2 pe
’ *Equipment .
A. 2 UNIVAC 1103-4 digital computers 4H. Plot boords for radar and TLM-18 trocking date
_ 8 VERLORT {Modified Mod Ii} radar '\ Convection equipment for teletype transmission of redar, |
C. TLM-18 self-tracking telemetering antenna TLM-18 and doppler tracking data ia binary format
D. Tri-heliz ontenne + Acquisition programmer for pre-acquisition direction of
antennes
i by Toceeay a wen amet X Ground command fo scielite tromsmission equipment i
G. Telemetry decommutetors for real time date. presentotion b+ Guidance computer :



in April 1960, Amendment No, 5 to ARPA Order
No. 54 reoriented the program. The research and
development effort Previously directed toward
providing a 9round-to-satellite-to-aircraft UHF com-
munications capability for the SAC strike forces was
cancelled. A single integrated ADVENT Program for
the development of a 24-hour microwave communi-
cations satellite replaced the former STEER, TACKLE
and DECREE Programs.

On 15 September 1960, the Secretary of Defense

transferred ] Management responsibility for
the ADV m1, ARPA io, the Department
ri '@ development responsibilities of

AFBMD and USASROL were retained essentially status
quo. The Army was given responsibility for funding
and for over-all systems engineering to Provide
guidance and a basis upon which detailed design
data can be evolved by AFBMD and USASRDL,

PROGRAM OBJECTIVES

The Primary ADVENT objective established by
Amendment No. 5 is to demonstrate the feasibility
of achieving a military system for microwave com-
munications (surface-to-surface) employing satellite
repeaters in 24-hour equetorial orbit. The feasibility

HORIZON SCANNERS

1/4 ANTENNAS

5S” RECEIVING

MICROWAVE COMMUNICATION
ANTENNA ARRANGEMENT

Figure 2. Initial design of final stage vehicle.

of placing a satellite in predetermined position in
@ 19,300 mile equatorial orbit must be demonstrated.
The feasibility of being able to stabilize the satellite,
control its attitude and orbit, and keep it on station
within the required tolerances must also be demon-
strated. The satellite must be capable of Providing
worldwide communications on @ real time basis at
microwave frequencies with a high channel, wide
bandwidth capacity. Amendment No, 5 also requires
the design of a single basic configuration of a final
stage vehicle compatible with launching by either
AGENA "B" or CENTAUR second stage boosters.

The ADVENT Program, as defined in ARPA Order 54,
Amendment No. 9, dated 11 August, will consist of
the following flight tests, lounched from the Atlantic
Missite Range:

@, Three ATLAS/AGENA “BY flights, nominal
5,600 nautical mile orbits, beginning March 1962.

b. Two flight tests, using payload Space on NASA
ATLAS/CENTAUR research and development ftights
number 9 and 10, December 1962 and February
1963,

¢. Five ATLAS/CENTAUR flights launched into
19,300 nautical miles equatorial orbits, beginning
March 1963,



CONFIDENTIAL

revised funding requirements necessitated by the
increased cost of the Development Test Program.

Flight Test Progress

point, T plus 151 seconds, the telemetry failed and
consequently the duration of the fourth stage burn-
ing is unknown, The trajectory was as planned and
the 32.8 tb payload Probably reached an altitude
of 14,400 nautical riiles. All of the Payload test
objectives (vehicle development objectives) appear
fo have been ‘accomplished. The secondary objec-
tives {payload objectives) were not accomplished,

Technical Progress

* Serious quality control and fabrication deficien:
cies have been discovered in the guidance system
timer unit. The taunch of the first guided vehicle
scheduled for 21 October will be delayed. The
Haydon Company is working on a three-shift basis
and Minneapolis-Honeywell and Aeronutronic per-
sonnel are assisting in modification design and are

monitoring the timer rework. There is a Possibility
that the delay will be less than ten days.

© = The ABL-X254 Focket motor program for the first
guided vehicle was found to be defective. The motor
case developed a 360° crack, located along the
forward attachment ting, during curing. A satisfac-
tory modification fo the motor case has been devel-
Oped. The fabrication and delivery of a new motor
could cause a schedule slippage, but the timer prob-
tem appears to be the critical item,

° A successful finear charge motor destruct test
was accomplished at Edwards Air Force Base on a

required to demonstrate 609A guided vehicle
destruct capability to AMR range safety.

Facilities

° Final design drawings for the two @ssembly and
checkout buildings ond the combined system test

building were received from the architect-engineer.
Following a final design review, scheduled for 11

WDLPM-4.245

~

=



— pees BOOSTERS

© The primary Pacing factor in the accom-
- plishment of space missions has been, and for

some time will continue to be, the

‘of Air Force ballistic missiles and upper stages

10 boost the payload vehicle. Space flight plan-
7 ping requires close examination of all tech.

This, in turn, has required that space schedules

be sufficiently flexible to incorporate rapidly

those advances in the state-of-the-ort which

_ increase the potential for reliable and pre-
dictable space research.

© Because of the wide range of its activities,

- AFBMD hes accumulated a broad base of expe-
rience in booster selection for space missions.

Experience in ballistic missile R&D programs

_ ond in development of Upper stage vehicles
have provided much information. Research

Programs in the propellant and materials areas

also are providing new capability for space

~ . The number and variety of boosters
available permit the selection of « combination

of stages tailored to Provide specific capabili.

_ ties for specitic missions,

: ©@ The following pages describe briefly the
booster vehicles currently being used by AFBMD
_ 10 support military and civilion



ts’
toe}
Nhe
ryt | UPPER PAYLOAD*
8 i
B. ssconp stacs—asce-stan {Al10-104) PAYLOAD (36-inch diameter)
TP Threst ob oltitude 9090 pounds 4 .
Specific impulse {vor} 278 seconds A
Total inpuice (min) 2.3 X 10" the/see ya | ‘
Pomieet Henrie Se F | PAYLOAD SPIN. MECHANISIA
' 222TSS.
A. Finst STAGE—THOR imam 7
Thevet fs. 1) 151,500 pounds t Fauir "ART
Specific impulse fs. 1) 248 seconds a we
‘Specitic impulse (voc) 287 seconds
4 aosteg ime ise | PROPULSION SYSTEM
Propeltant Uquid 1 54.79 in,
Nye
A i _
? STAGE 1/il
rah SEPARATION PLANE
' y
STAGE | GUIDANCE
‘COMPARTI
—TRANSIT 18, 2A, 3A and 38 ’ MENT
' "20-inch diameter (TRANSIT 24 and 3A)
Program Objectives Powered Flight Trajectory The powered flight

1. Provide accurate navigational reference informa-
fion for POLARIS lcunches.

2. Precise ‘determination of satellite position by
measuring the doppler shift of satellite transmitted
radio signals.

3. Investigate the refractive effect of the jonosphere
on radio transmissions,

4. Acquire additional geodetic and geographical
data by precision tracking of the orbiting satellite,

Flight Vehicles TRANSIT 1A consisted of three
stages as shown in Figure 1, TRANSIT 1B, 2A, 3A
and 3B are two-stage vehicles as shown above.
Launch Plans Ail vehicles will be launched from
Atlantic Missile Range pad 17A or 17B. Launch
azimuth for TRANSITS 1A and 1B is 44.5 degrees
and for TRANSIT 2A, 140 degrees.

frojectory for TRANSITS 1B and 2A is shown end
described in the fight trajectory diagram.

Payload Description The spherical payloads are
approximately 36 inches in diameter and weigh
between 200 and 270 pounds. Payload equipment
includes four transmitters (on frequencies of 54, 108,
162 and 216 megacycies), two receivers, and a gate
which permits the insertion of data only when the
gate has been opened at a Previously scheduled
time. Power for the first five months will be supplied .
by batteries, recharged by solar cells located in a
12-inch band around the sphere. The TRANSIT 1B
Payload will also contain an infrared scanner which
will operate for the first four days of orbit. On TRAN-
SIT 2A @ 20-inch sphere, mounted on top of the
36-inch sphere, will contain instrumentation for
studying solar emissions. The Payloads will be spin-
stabilized in orbit,

zs SHGRET. 5 wanna



Flight Time inertial Speed Downran, Altitude
Point (seconds) Comments (ttZsech Distance (oom) (aan)
18 2A Transit vehicles 18 2A 18 2A 1A 2A

10 10__End of vertical rise 1346146 0 0 0077 O07

2 167 167 _Finst stage bumout 13,611 12,929 752 7 42 aaa
End of second

3 402 “48 fit buming perce 453° 24.476 756 780 20.1 ama
4 14091 aa7 Eesirt second stage RAG RS 4202 4000 5000 S000
5 1,504 1482 "Injection into orbit 24258 24257 4A163 “41900 5000 5000

FLIGHT TRAJECTORY —reansit 1Band 2a .

Orbital Performance Achievement of Program
objectives is based Primarily on Measufing the
doppler shift of satellite transmitted radio signals,
During the first three months of flight, the four trans-
mitters will be operated to obtain experimental con-
firmation of the theoretical mathematical telationship
between the frequency and the refractive index of
the ionosphere. Studies have shown that refraction
effects on the doppler shift can be eliminated by
using the transmission from two satellites. After four
months of tracking the satellite by measuring the
doppler shift of the satellite radio signal, the exact
Position of the satellite at @ny point in the orbit
should be known, Using known orbital Positions,
ships and aircraft can then use satellite signals to.

WDLPM-4-245

make analogous computations to establish accurate
position. Navigational fixes of 0.1 mile accuracy are
expected to be obtained.

Ground Support Stations Tracking stations will
be operated in Maryland, Texas, New Mexico, Wash-
ington and Newfoundland. First and second stage
tracking and telemetry and second stage guidance

Germany for TRANSIT 1B and South America’ for
TRANSIT 2A. The mobite tracking and telemetry van
will be located in southeast Africa for TRANSITS 3A
and 3B. These locations were selected as the closest
sites possible to the orbit injection point,

ECR rs





transmit crude television images of the far side of ———— PATH OF Moon
the moon. This was the first flight in which an ATLAS cy wo wm ABLE-8 TRAVECTORY
ICBM was used as the booster for a multi-stage space \ “o> "= SATELLITE ORBIT OF moon

INJECTION
ROCKET
Np NITROGEN -
Saretiite Vehicle SPHERE
Gross Weight 300.2 tb
Gross Weight (Bumovt) 229-4 lly HYDRAZINE.
Specific impulse {voc} 230 sec
Theat (voc) Fret SPHERE
© THIRD StAGE Ant 248-a9
Gross Weight 903.2 ty yee
Gross Weight (umout) 374i ORM
Iimpulee (vee) 250.5 sec
Theat (voc} 3100 tb THIRD STAGE.
§ SECOND stAGE AJ 10-10) SEPARATION
Gross Weight 51073 % PL,
rons Weight (Burnout) 1816.1 tb ane
Seeein pee (voc) mae pores
‘A. FIRST STAGE ATLAS “Dp”
Gross Weight 266,390 THIRD STAGE
Grost Weight (Burnour 1,790 t ENGINE
Tew Bu ' ; 316.5 sec
Tors i Sustainer yriel SECOND TAGE
fie Impulse {vac} Booster 2 SEPARAT!
Specte Impl (8 L) Boeter sare ptane
Figure 3, ABLE-S vehicle configuration drawing and speci ist, Thind
and (right). Tr i
howe it deaclag MSerato® right). tajectry of ARLES Ge fit, Thing
second. The payload was designed to investigate oe Me . ~
space environment and Propagation effects and to LEGEND

ABLE-4 THOR — This vehicle was launched on 11
March from the Atlantic Missile Range and succeeded \

in placing the PIONEER V Satellite into a solar orbit, ‘

At its closest approach to the sun, the satellite will \

Pass near the orbit of Venus, and return fo intersect ‘ ~
the orbit of earth at its greatest distance from the \ SUNN
sun. The vehicle consisted of a THOR first stage, ABLE x

second stage with AJIO-101 liquid fueled propul- \

sion system end on STL guidance system, and an

ABL-248A-3, solid fuel third stage. The 95 pound
payload contains instrumentation for conducting
scientific experiments related to magnetic field and
radiation phenomena in deep outer space. At 0733
hours EST, on 26 June, the last radio signal was
feceived from PIONEER V. The transmitter has been
Operated throughout the three ‘and one-half month
Period and has demonstrated that, except for the
batteries, the communications fink could have been
maintained for a distance significantly greater than
the 50 to 60 million miles originally estimated. At
the time of the last transmission the vehicle was
22,462,000 miles from earth.

D4 CONFIDENTIAL WoLPMA245



CONFIDENTIAL

Program Responsibilities — Steps | and I of the
DYNA SOAR Program are to be conducted by the
USAF with NASA Participation, USAF will provide
Program management and technical direction, with
WADD having responsibility for over-all system
management,

AFBMD is responsible for the booster, booster sup-
Port equipment, special Gir-borne systems, ground
Support equipment, and booster requirements of the
launch complex. WADD will have responsibility for

vide technical support
of the glider in obtaining basic Geronautical and
space design information,

Technical Approach — AFBMD's techincal approach
fo meet the objectives of the program are:

1. Modifying a TITAN ICBM by adding stabilizing
fins; strengthening the holddown and skirt area, inter-
tank and interstage sections; redesigning the guid-
ance bay; incorporating @ malfunction detection
system; and initiating a new staging technique (fire
in the hole}.

2. Modifying the LR 87-AJ-3 or LR 91-AJ-3 rocket
‘engines to obtain structural compatibility with the
modified booster; inciude malfunction shutdown and
tail safe systems; and adding o cartridge start system.

3. Lighten and simplify the second stage engine.

4. Modification of an AMR launch pad.

5. Provide an integrated launch countdown.

MONTHLY PROGRESS—DYNA SOAR Program
Program Administration

© The DYNA SOAR Program is making noteworthy
Progress, primarily in the areas of detailed program
planning, preliminary engineering and Program
management,

©. The Martin Company submitted its DYNA SOAR
launch facility report on 26 September. The DYNA
SOAR Facilities Working Group hes decided to use
the gantry approach rather than the erector approach
for Atlantic Missile Range launches.

* The Aerospace Corporation is providing techni-
cal supervision support to the booster portion of the
DYNA SOAR Program. Space Technology Labora-
tories‘ efforis have been terminated.

WDLPM.-4.245

© The Martin Company has completed and sub-
mitted the following trade-off studies:

1. Second stage Propellant Load and Pressuriza-
tion System on 26 August,

2. Structural Design and Criteria on 2 September.

3. Staging Techniques fincluding fire-in-the-hole)
on 12 September,

4. Reliability and Safety on 15 September.
5. Booster-Glider Interface on 19 September.

6. Malfunction Detection and Waming System on
3 October.

CONFIDENTIAL | 1



Prime contracter:
Douglas Aircraft Co.
Engine manufacturer:
yi Neh Early in 1958, the decision te. accelerate the national space effort was made effec:
‘ively potible only because of the aveilabiity of the THOR IRBM. THOR No. 127
DME 61.3 feet

DA 559 feet was diverted from the R&D flight test program for use as the ABLE-1 space probe

DM-21A 60.5 font first stage. With top national Priority cssigned to the space research effort, THOR
mate 108,000 No. 163 was wied to boost the DISCOVERER | into orbit on 2 February 1959. Since
DaCatA lar 720 cena then, the THOR has become perational as an IRBM and has been very reliable
brary MBS Bost | @s a space flight booster. During 1959 all THOR boosted space flights achieved
OM-2t fork oe successful first stage performance. THOR Performance has been increased through
peat Prey perl weight reduction modifications and use of RJ-1 (instead of RP-1) fuel. A modified
Feel THOR, designated DM-21 {used with an AGENA second stage], incorporates a short-

tox ered guidance compartment and additional weight reduction changes. A later
Guidence — Bell Te version of the DM-21 pro-

Laboratories or autopilot only

Used os stege fort vides an increase in thrust to

Discoverer 167,000 pounds through
ABLE and -4

TANsiT installation of the MB-3-
‘COURIER Block II engine. The DM-
NAS/AGENA b 21A, used with the ABLE-

DELTA STAR second stage, has a larger transition section than DM-18/DM-21 and does

u not incorporate all the weight changes effective on the DM-21.
THE ATLAS ICBM, Providing over twice the thrust of the THOR, is being used as

ATL A Ss the first stage booster for the three Advanced Military Satellite Programs and for
Project Mercury man-in-space. The first ATLAS boosted space flight was launched

Prime. contrecter, from the Atlantic Missile Range on 18 December 1958, Designated Project Score,
Convair this vehicle (ATLAS 108) successfully placed a communications payload into
Engine menufacteren: orbit around the earth. In November 1959 the ABLE-4 space probe did not attain
peenciN Dive Meth in objective, however, ATLAS firt stage performance was successful, The first
Neate feet ATLAS-boosted flight test vehicle in Project Mercury was launched on 7 September
with test objectives satisfactorily achieved. ATLAS performance on both the 26 os
Plameter 10 feet February and 24 May MIDAS launches also wos satisfactory. Future flights will
Weight 261,206 pounds use modified ATLAS series “D" missiles to carry increased payload weights.
Engine Project Mercury boosters also include *
Serles DATIAS  MA-2 abori-sensing and other pilot safety
Feel JP features. The success of the ATLAS
Oxidizer tox “
boosted, space flights to date plus
penatieeduiel the performance and reliability being
Uurreughs Corp. (computer) demonstrated in the ATLAS RED flight =
ned as tia! stege for test program, lend confidence in this
SAMOS booster as a reliable means of real-
MIDAS izing advanced space objectives,
COMMUNICATIONS $ nee ei 1
SATELUTE
ABLE ond 5
PROJECT MERCURY a

ma SEGREF- WOLPM4u4s


SATELLITE

swaisas SLITIALVS.

systems


“CONFIDENTIAL

Project MERCURY represents the transitional threshold
between this nation’s cumulative achievements in
space research and the beginning of actual space
travel by man, The primary program objective is to
place a manned satellite into orbit about the earth,
and to effect a controlled Fe-entry and successful
recovery of the man and capsule (Figure 1).
Unmanned ICBM trajectory and near-orbital flights,
and unmanned orbiting flights will be used to verity
the effectiveness and reliability of an extensive
Fesearch program prior to manned orbital flights
{Figure 2). The program will be conducted over a
Period of nearly two years, The initia! R & D flight
fest was accomplished successfully in September
1959, The total program accomplishment is under
the direction of NASA. The primary responsibility of
AFBMD to date consists of: (a} providing 16 ATLAS

LEGEND

RESPONSIBILITY:
AFBMD =
NASA qmeen

t
T
1
ESCAPE !
ROCKET /

t

CAPSULE /

ATLAS ' ,
BOOSTER a,

Figure 2. Flight test trajectories tor Proj
represents the path of the fnal
Woes bord oseleshead en into orbit,

Ge “CONFIDENTIAL

boosters modified in accordance with Program objec-
tives and pilot safety factors, and (b) determination
. 6f trajectories and the tounching and control of
vehicles through injection into orbit. The division of
responsibilities for this program is given in Table 1.
Specific details of AFBMD support are given in
Table 2.

Major contractors Participating in the AFBMD portion
of this program include: Space Technology Labora-
tories, systems engineering and technical direction;
Convair-Astronautics, modified ATLAS boosters;
GE/Burroughs, ATLAS guidance equipment; and
Rocketdyne, engines. All of these companies also
Provide special studies and engineering efforts pecul-
far to meeting Project MERCURY requirements.

A BALLISTIC TRAJECTORY
TO SIMULATE REENTRY CONDITIONS

B NEAR ORBITAL INSERTION, IMMEDIATE
REORIENTATION, DECELERATION, REENTRY
ATLANTIC RECOVERY

C FULL ORBIT 3-18 ORBITS 94-126 NM.
WEST COAST REENTRY ATLANTIC RECOVERY

MERCURY, defning specific objectives, Trajectory C
(manned) ighe. The poles cs hie end NASA rerpousilli
it.

WDLPM-4-245



CONFIDENTIAL

modification incorporated os a result of the
COURIER 1A flight. Table # fists nominal and
Gctue! orbital parameters,

PARAMETER NOMINAL ACTUAL

Apogee, nautical miles 650 658.2
Perigee, nautical miles 650. 501.7

Eccentricity 0 0.0195
Inclination Angle, degree 28.5 28.3
Period, minutes 109 106.7

TABLE |. COURIER 18 Orbital Parameters

© The paytoad contractor reports that the
Payload is operating as well Qs or better than
ex le

© =Downrange tracking of the flight was
excellent. The mobile tracking ven at Pretoria,
Union of South Africa was Operated and suc-
cessfully tracked the ABLE-STAR vehicle during
the second burn period and injection into orbit.

Figure 2. COURIER 1B following liftoj
fro stand 178, ‘Alani Meee ed
on 4 October,

ra CONFIDENTIAL

WDLPM-4-245



——_— —
THOR eS om-18 ME pm.21 DM-21A ATLAS TA Series D
| Weight—dry 6,727 6,590 6,950 Weight—wet 15,100
Fuel 33,500 33,500 33,500 Fuel 74,900
Oxidizer 68,000 68,000 68,000 Oxidizer 172,300
aa 108,227 | 108, 108,450 TOTAL WEIGHT ,
TOTAL WEIGHT 090 Thewtibe So 262,300
Thrustibs,, S.L. 152,000 | 167,000 152,000 Boost
_ Spec. Imp.-sec., S.L. 2470 247.8 247.0 Sustainer 356,000
Burn Time —sec. 163.0 152.0 163.0 Spec. Imp.-sec, 82,100
Boost
Sustainer 286
_ 310
NOTES AGENA “a “e"
© Payload weight not included. Engine Model YURBI-Bo-S | XLRB1-Bc70 | yrRB1-Ba.9d
Does include controls, guid.
, APU and residual
- pellants pe Weight—inert 1,262 1,328 1,346
h lants 6,525 12,950 12,950
© Does not include THOR sipulte Propel ? si
Other 378 su Bill
adapter (225 tbs.) or ATLAS .
_ adapter (315 Ibs.). STOTAL WEIGHT 8,165 14,789 14,807
Single restart capability. Thrust-tbs., vac, 15,600 15,600 16,000
O Single . Spec. Imp.-sec., vac, 277 277 290
@ Dual burn operation. Bum Time—sec. 120 2400 2400
© Allegany Ballistic Laboratory.
= 510-104 |,
AJ 10-42 IEA) 10-101 ABLE.STAR ABL 248
~ . Welght—wet 1,247.1 847.9 1,297 59.5
Fuel 875.1 869.0 2,247 O 455.5
Oxidizer 2,499.6 2,461.0 6,227 (solid)
— TOTAL WEIGHT 4,621.8 41779 9,71 D 515
Burnout Weight 1,308.6 944.1 1,419 50.5
Thrust-lbs., vac, 7,670 7,720 7,900. i 250.5
Spec. Imp.-sec., vac 267 267 278 3,100
= _ HL
DISCOVERER (1 thru 15)... MIDAS (1 and 2) ...... 0... Dg ABLE-4 and -5 ... oo DL
DISCOVERER (16 thru 19) . MIDAS (3 and subs) DG TRANSIT 1A... AHL
DISCOVERER (20 and subs} thru 3). D-E TRANSIT 1B, 24, 3A, 3B, 4A. C.-K
COMM, SATELLITE . . and subs) . --DG COURIER ....., cK
eSand-4 6... AdL  TIROS AHL

MODauN OF=T4



Figure 4. ,

biting seelites detect infeed radiation emitted
by Sovles ICDA i tome ‘elem
eered fatiantanconsly to ontrol ier
1a fe north ceadont saions. DetoSet Tog te,

location, divectic ravel and buraii
therasertats, rok Jey thee 100 of
above map indicat, probabil it} at least
ove MIDAS stellnc deeetr ot o Taaucb.

at ICBM lenuch. The based -

launch. These heures are OM g60.

metric considerations of the f ily tellites and
ions f family of satellites a

imately the sumber of missiles leunchee ed

ities of 1.00 indicate that wore than one
fect

1 be in position to dete

TECHNICAL HISTORY

The MIDAS infrared feconnaissance payload is engi-
Reered to use a standard launch vehicle configura-
fion, This consists of an ATLAS missile as the. first
stage and the AGENA vehicle, Powered by a Bell

Alrcraft rocket engine as the second, orbiting stage °

{Figure 1). The final configuration payload weight
will be @pproximately 1,000 pounds,

The first two of the fen R&D flights used the AGENA
“A and ATLAS “OD” vehicle Programmed to place
the payload in a cirevlar 261 nautical mile orbit,
Subsequent R&D flights will utilize the ATLAS “D7

‘WDLPM-4.245

AGENA “B" configuration which will be Programmed
{0 place the payload in a circular 2,000 nautical mile
polar orbit,

MIDAS |, launched in February 1960, did not attain
orbit because of @ failure during ATLAS/AGENA
separation,

MIDAS II, launched in May 1960, wos highly success-
ful, Performance with respect to Programmed orbital

Parameters was outstanding. Useful infrared data



landing at a Predetermined site. In Step I the glider
will be tested, using a more Powerful booster to
achieve orbital velocities. This phase may be
expanded into on interim operational weapon sys-
tem providing all-weather reconnaissance and satel-
lite interceptor capobilities. The objectives of Step Il
are to test vehicle performance between 19,000
fi/sec and orbital velocities; and to gather re-entry
data from various orbits. Step Ill will Provide an
Operational weapon system with @ vehicle that will
Operate primarily in a hypersonic glide, be able to
maneuver within the atmosphere, and be able to
make @ conventional landing at a Predetermined
site. The capability of DYNA SOAR type systems to
Perform these Programmed missions appears attrac-
five as a result of studies made to date, The missions
under study are: reconnaissance (manned and
unmanned); air and space defense; strategic
bombardment and logistics support. Manned and

unmanned versions cre being considered where
applicable, .

A. Altitude 250,000 feet
8. Boost Burnout Veloci
18,600 fps oeity

32

FUGHT ONE (Unmanned) TRAJECTORY

Flight Program—Step | includes
iched, manned flights with the
dropped from a 8-52, five unmar
Jounches, and eleven m:
the Atiantic Missile Re
launch is scheduled for
with a one and one-half
launches. The manned
grammed to stort in Sepi
month span between laun:
dover ‘AFB, Utah, to Edwar
instrumented for the tracki
during the air-taunched
glider. Instrumentation sil
will be located at Cape
Mayaguona, Antigua,
Instrumentation, track
Provided to supply additi
launches. landing facili

Fortaleza, Brazil; Santa Weia,
Mayaguana, Bahama Islands.

@

inge {AMR}.

tests of the DYNA SOAR
ites for the AMR launches
Canaveral, San Salvador,
Senta Lucia, and Fortaleza.
Gnd recovery ships will be
ional support for the AMR
ties will be provided at
Lesser Antilles; and

WDLPM-4-245

nineteen air-
glider being

inned booster
janned booster launches from
The first unmanned
t November 1963
month span between
booster flights are pro-
tember 1964 with a two
The range from Wen-



SPACE

SWVEDOUd 3SN3430 3Dvas



ts. Gathers payload data,

Measuremen:
telemetry and tracking data and transmits this data to the Satel-
enter.

station) lite Test Ci

Telemetry ships IKMS Ascent tracking and telemetry dota reception through AGENA
first burn period,

Vanidenberg AFB NO Provides ground radio guidance system for booster guidance
during the launch Phase,

Northeast Station CDEFHMPQR Provides orbital tracking. Gathers Payload data, telem: and

(New Boston, New tracking data and transmits this data to the Satellite Test Conse’

Hampshire)

Southeast Africa JKM To receive and record telemetry data and Provide limited track.

Station ing during the AGENA, second & burn period,

Kaena Point, HIKLMTU- Gathers supplemental Veriort tracking data during orbital Passes,

Oahu, Hawaii

Kodiak, Alaska HIKLMTU Gathers supplemental Verlort tracking data during orbital passes,

Point Mugu HI Ascent tracking for Fange safety; backup function,

Point Arguello v Mates vehicles, performs final system checkout, prepares vehicle
for launch and launches vehicte,

*Equicment

7 : u Met Boards for Radar ond TLM-18 Tracking Data

‘A. Model 1604 Computer M. Doppler Dota Gathering Equipment

8 Ground Pretentation Equipment N. AN/GQR-2 pxXA.2) Tracking and Menopvise Rador

C. Dota Distibution Equipment PICE) O. AN/GRS2 (KAA-2 Rate Mensuting Spite

©. Data Conversion Equipment Timing (WW) Equipment

E. UNF Tracking Equipment Q. VHF FM/EM Data Acquisition Equipment

F. UH Telemetry and Data Acquistion Equipment 8. VHF PAM/FM Dota Acquisition Equipment

G. UKE Command Antenna S. High Frequency Rodio Communications and Teletype Circuits

. He Ten (Mod fi) Rader T. Acquisition Programmer for pre-acquisition Divection of Antennas

|. Trishelix Anton 1. Conwersion Eavi ie TUM.

4 TUM Talamety Antanas | bong fee Vein oT

K. Telemetry Receiving ond Recording Equipment ¥. Complete Launch Facilities

GROUND supporr FACILITIES

WwoiPaeenes SCRE. BS


seereT-

HEADQUARTERS SH

AIR FORCE BALLISTIC MISSILE DIVISION (ARDC) |

UNITED STATES AIR ‘FORCE
Air Force Unit Post Office
Los Angeles 45, California

WDLPM.4 17 October 1960

FOREWorD

This report includes information on the three space vehicles launched by
the Air Force in September. DISCOVERER XV was launched from Van-
denberg Air Force Base on 13 September. At the Atlantic Missile Range
Project 609A Blue Scout, Jr., vehicle was flown on 21 September and



‘AL THIRD StAGE—x.248 (Allegany Gailistic Lab.) tT
Thrust at oltitede 3150 pounds A

Specific impulse (vac) 250 seconde a
Total impulse 116,400 Ibs/sec ‘
Burning Time 37.5 seconds :
Propellant Solid 8
5. SECOND STAGE— 4310-42 (Aerejet-General) Jj
Thevat at oltitede 7700 pounds
Specific impulse (vec) 271 seconds
Total impulse {ein} 870,000 Ibs /see
Burning time 115 seconds
Propellant liquid
€ FiRst Stact— THOR iRam
Thevat (5.1) 151,500 pounds c
Specific imputee (1) 248 seconds
Specific impules (voc) 287 seconds
Burning time 158 seconds
Propaliont Uiguid
Figure't, TRANSIT TA three stage Hight vebicle,

(ay)

The TRANSIT Program consists of the flight testing
of six vehicles to place 200-270-pound satellite pay-
loads into circular orbits of 400 to 500 nautical miles.
The program is designed to Provide extremely
accurate, world-wide, all-weather navigational infor.
mation for use by aircraft, surface and subsurface
vessels, Particularly in retation fo POLARIS missile
firings. The ARPA Order for TRANSIT 1A was initiated
in September 1958 and amended in April 1959 to

LAUNCHING SUPPORT TusE

melita A

ae sous cu
7 x

mexa.-casmun 91-3018 we

SASTERIEG #08 soLae.
Powne systam

-3906 witent
themaren MUNASH CABLE

Figure 2. Cutaway drawing of TRANSIT 1A payload (NAV 1).

WDLPM-4.245

TRANSIT 1A lexached from Atlantic Missile Range

add TRANSIT 1B, 24 and 28 flights. The TRANSIT
3A and 38 flights were initiated by a Navy MIPR,
dated 18 May 1960, Because of the successful
TRANSIT 2A launch and excellent Payload perform.
ance the Navy has slected to launch TRANSIT 3A
rather than 28. TRANSIT 2B was scheduled to carry
the same type payload as was carried on the 2A
flight.

assigned to the USN Bureau of Weapons, Applied
Physics Laboratory is the Payload contractor.

suensy e


“CONFIDENTIAL

The ABLE series of space probes was initiated with
the ABLE-] Program in March 1958, This Program,
undertaken by AFBMD under direction of the
Advanced Research Projects Agency, had as its
Over-all objective, the acquisition of data on the
extra-terrestrial space environment. The design and
construction of a four-stage space vehicle was initi-
ated. The vehicle, consisting of a THOR IRBM first
stage, on ABLE second stage, ABL-248 solid Propel.
lant third stage and the satellite vehicle fourth stage
was successfully demonstrated in the fall of 1958. In
October 1958, the National Aeronautics and Space
Administration, given cognizance over the space
exploration effort, authorized the ABLE-3 and ABLE-4
Programs. General objectives included the demon-
stration of vehicle and communications capability
‘and performance of scientific research experiments
over interplonetary distances. An extensive network
of ground support stations was simultaneously estab-
lished, the most powerful of which is the 250-foot
antenna at the Jodrel! Bank Experimental Station,
University of Manchester, England. Central control
and data computation is accomplished at the Space
Navigation Center, Los Angeles, California, with
other military and NASA centers assisting in
tracking and telemetry ‘according to the specific
requirements of each mission. The ABLE-4 Program
led to the development of a space booster utilizing
the ATLAS ICBM as the first stage, providing a
greatly increased payload capacity. A hydrazine
engine with multi-start capability was.developed for

Figure 2. ABLE-3 third stage
end besload (above) otis fe
let full €

"7 ely allipeical orb
of extremely elliptical orbiy
Shien by ABLES (EXPLORER

D2

the ATLAS boosted vehicles to permit mid-course
vernier control and to Provide controlled thrust to
inject the vehicle into orbit about another planet.
Under the ABLE-3 and 4 Programs, a solar cell power
supply system was developed and extensive original
design of satellite vehicle command, telemetry, and
communication equipment was ‘accomplished.
ABLE-1—The ABLE-1 program consisted of three
flights with the object of placing a Payload within
the moon's gravitational field. The ABLE.1 four-stage
vehicle consisted of three booster stages and a ter-
minal stage composed of eight vernier rockets,-an
orbit injection rocket (solid Propellant TX8-6) and a
Payload. The booster stages were THOR first stage,
Advanced Re-entry Test Vehicle (AJ10-101 engine)
second stage, and a third stage utilizing the ABLE
X-248-A3 solid Propeliant rocket engine. The first
lunar probe was launched on 17 August 1958, The
flight was normal until 73.6 Seconds after liftoff when
@ turbopump bearing failure caused the booster to
explode. The second tunar Probe was launched on
10 October 1958, Although the payload did not
reach the vicinity of the moon, @ maximum altitude.
of 71,700 statute mites was attained and useful sci-
entific data were obtained from the instrumentation.
The third lunar probe was launched on 8 November
1958. Because the third stage failed to ignite, the
maximum altitude attained was 970 statute miles.
The primary Program objectives, obtaining scientific
data in cislunar space, were achieved by the Octo-
ber flight,





“CONFIDENTIAL—

MONTHLY PROGRESS — Project MERCURY
Program Administration

© Amendment No, 9 to NASA work order HS-36
requesting two additional ATLAS Series “D" boosters
for Project MERCURY was received on 31 August.
This request increased the program to 16 boosters/
15 launches. The additional boosters have been
incorporated into AFBMD allocation and launch
schedules, and the 31 March MERCURY Development
Pian will be amended to reflect the program increase.
© The MA-1 Malfunction Analysis Panel {which
includes members of all agencies concerned with

" MERCURY/ATLAS fights) has been monitoring alt

MA-1 investigations and determining the precaution-
ary modification action necessary for follow-on
launches.

Flight Test Progress ~
© Continued investigations have not yet revealed
the specific cause of the 29 July MA-1 (ATLAS booster
500) malfunction, One of the initial theories for the
failure was eliminated during September when it
was determined that the failure of the booster LOX
boil-off valve assembly was subsequent to, and the
result of, the over-oll failure. It had been theorized
that the failure of this valve was a possible cause
since it was recovered near the capsule. Other early
indications seemed to substantiate the belief that the
valve had separated from the booster prior to the
over-all failure. -
© The trajectory pitch program will be revised fo.
minimize the ongle of attack during the period of
igh Q and thus reduce the vehicle bending loads.
Because of the MA-1 flight analysis and these trajec-
tory changes, It is anticipated that the MA-2 launch
tow scheduled for I November will be delayed at
least two weeks.
© A walkout of over 450 workers occurred on 12
September at the Atlantic Missile Range. Early reports
did not indicate that Project MERCURY Stand 14 had
been affected by this walkout. It has not yet been
determined whether the strike will have any effect
on the present MERCURY launch schedules.
© NASA capsule test objectives for the MA-2 flight
are:

1. Determine the integrity of the MERCURY struc-
ture, ablation shield, and afterbody shingles for a
re-entry associated with a critical abort.

2. Evaluate the performance of the operating sys-
tems during flight.

3. Determine the flight dynamic characteristics
and atfterbody heating rates during re-entry from a
criticat abort, ,

WDLPM-4-245

4, Evaluate the compatibility of the escape system
with the MERCURY/ATLAS system.

5. Establish the adequacy of the capsule recovery
system, the location of the recovery force and recov-
ery procedures,

6. Evaluate prelaunch, launch, and flight monitor-
ing procedures and facilities.
© ATLAS booster flight objectives for the MA-2
flight are:

1. Evaluate the closed-loop operation of the Abort
Sensing and implementation System.

2. Determine the ability of the ATLAS booster to
release the MERCURY capsule at the conditions of
position, attitude and velocity defined by the guid-
ance equations.

3. Obtain data on the repeatability of the per-
formance of all ATLAS booster and ground systems.

Technical Progress

* A vibration test program will be accomplished at
the McDonnell Aircraft facilities in St. Louis during
the first week of October, These tests will use a full
scale assembly composed of an ATLAS forward LOX
dome, the adapter, and a portion of the capsule.
These tests are designed to determine possible areas
of failure caused by vibrational loads. During this
some period a one-third scale model of the ATLAS
forward LOX dome, the adapter, and copsule will be
tested in the Amold Engineering and Development
Center wind tunnel, It is anticipated that the data
gained from these experiments will be sufficient to
determine the necessary modifications and/or con-
figuration changes necessary to gain reasonable
assurance for the success of follow-on MERCURY
flights,

© Additional instrumentation. requirements have
been established for the MA-2 flight as a result of
Malfunction Analysis Panel action. Additional instru-
mentation pickups for this flight will be located in
the adapter. and booster-capsule attach point areas.
In order to handle the additional inputs generated
by this instrumentation an extra telemetry package
will be installed in the ATLAS booster,

© The Factory Roil-Out Inspection for ATLAS 77D,
the booster for the fourth MERCURY flight, was held
on 23 and 26 September. The data review was com-
pleted on 23 September. An AFBMD inspection team
meeting was held on the moming of 26 September
to determine the status of inspection discreponcies.
The joint AFBMD/Convair-Astronautics meeting was
held in the afternoon, and the booster was accepted
with @ few non-operation shortages remaining.

CONFIDENTIAL cs



CONFIDENTIAL

vehicle subsystems, Analysis of the telemetry data

"indicates thet the first vernies firing of the hydrazine
engine was accomplished. Due fo the suborbital
velocity of the satellite vehicle at the time of firing,
the velocity gained did not significantly affect the
: ballistic trajectory, and the vehicle was destroyed
Upon re-entry into the atmosphere. Final details of
the flight will not be known until complete analysis
of the tape has been Performed,

Pre-Launch Progress

° Following the correction of the ATLAS 80D
contamination problem, the ABLE-5A booster was
erected on 2 September. Preparations for the Flight
Acceptance Composite Test (FACT) were inter-
rupted because of Hurricane “Donna.” The missile
was removed from the stand on 10 September and
returned on 11 September. The FACT was success-
tully completed on 14 September; a complete
Firing Readiness Demonstration was completed on
17 September. The second stage vehicle successfully
completed the Flight Systems Test on 7 September.
After the lifting of the hurricane alert the stage was

Following the receiving inspection and static and
dynamic balancing, it was mated to the second
stage on 22 September. The satellite vehicle was
delivered to AMR on 7 September and was attached
to the third stage on 23 September.

Technical Progress
First Stage

* ATLAS 91D, the booster for the ABLE-58 flight,
is Proceeding on schedule for delivery to AMR on
14 October. After completing the receiving inspec-

the normal tests, a thorough examination of all
booster systems is being accomplished to preclude
any possibility of contamination,

Second Stage

© The ABLE-5SB second stage vehicle is Progressing
satisfactorily toward an AMR delivery date of 28
October. Electronic equipment has been installed
‘and subsystem checkout: is in Progress,

° Vendor gyro deliveries were received in Sep-
tember alleviating the ABLE-5 second stage gyro

bio CONFIDENTIAL

shortage. This shortage has been a serious problem
in second stage deliveries.

Third Stage

© Three ABL-X248-A9 engines were static tested
in @ simulated high altitude environment at Arnold
Engineering Development Center to determine
internal ballistic Performance. Data obtained from
these tests indicated that outgassing following pro-
pellant burnout was excessive. The thrust developed
during this period was of sufficient duration and
character to necessitate a change in Payload

stage and the satellite vehicle after separation. A
weight attached to a cord is installed at the Stage
M/Stage tv interstage structure ond deployed
simultaneously with Stage IV Separation, The
momentum developed by the weight during deploy-
ment is used to de-spin the third stage and exert a
couple to rotate the longitudinal axis of the third
stage, assuring positive Separation.

© The. second flight engine was delivered to AMR
on 14 September, However, the stage was found to

weigh less than specifications permit and has been
rejected. The feplacement engine is scheduled for
delivery before 8 November,

foranres, Aatiteptic methods similar to thote med neat
is A l.
pecegbloed i somber hosel. Fhe

walikely event that the impacts on the moon.

WDLPM-4.245

lt

l


CONFIDENTIAL

MONTHLY PROGRESS — COURIER Program

Flight Test Progress

© The COURIER 1B satellite was launched from
Attantic Missile Range stond 178 at 0950 PST on 4
The countdown wos Interrupted twice by

minor equipment difficulties which delayed the
launch for Approximately 90 minutes. Liftoff was
smooth and stable, and the flight was normal. Per-
formance of the THOR booster and ABLE-STAR
(A510-104} second stage was excellent. The satellite
vehicle was injected into orbit by restart of the ABLE-
STAR stage engine at 1030 PST. The THOR opera-
tion verified the effectiveness of the hydraulic system
Figure 1. COURIER 1B load being mated

fie Ante an ies is stage (apt rieby .

tol Cal pecans lege i lay The

prot wot
from the upper aif of the . The alu-
is is visible inside fairing affords
om the beet ceases by 4 lends

fairia, .
visible inside the fairing on the payload equator,
Pre] the payload im kest: (ho .
a goo t Bet
a rs

irasimitier! on tbe sapt Commend “Senet
microwave receivers dransmitters, and bat-
series on the middle shelves; and data st

sults on the fower shel The COURIER 8

ike omer a
stat Pe mem ei

WDLPM-4-245,

~

i
—



CONFIDENTIAL

Figure 3. ABLE-4 AT! ‘LAS vebicle con.

ignration drawing end photo of vehicle
installed ow Atlantic Mich Rees
lenuch stand 12,

ABLE-3 — This four stage flight vehicle was launched
from the Atlantic Missile Range on 7 August 1959,
The vehicle consisted of a THOR booster, a second
stage using the AJI0-101A rocket engine, a third
stage powered by the ABL-248-A3 engine, and a
fourth stage consisting of the payload and an injec-
tion rocket. In addition to carrying a highty sophis-
ficated payload, the ABLE-3 (EXPLORER V1) flight was
used to demonstrate the validity of the ABLE-4 vehi
cle and component configurations. All phases of the
launching were successful and the advanced scien-
tific observatory satellite was placed in an extremely
elliptical. geocentric orbit, Trajectory and orbit were
essentially as predicted with deviations in apogee
and perigee well within the range of expected values,
. The payload was the most sophisticated to have
been placed in orbit by this nation at the time and
contained provisions for conducting 13 experiments
in space ‘environment and Propagation. A wealth of
valuable data was obtained from satellite telemetry
Until the last transmission was received on 6 October.
Among the significant achievements of EXPLORER
VI were:
1. The first comprehensive mapping of Van Allen |
radiation belts,

WDLPM-4.245

2. The first study of dumping and filling of outer
Van Allen radiation belts during a magnetic
storm,

3. The first still TV photo of earth from a satellite,

4. The first computer (Telebit} ‘operating in space
with instrumentation,

5. The first direct flux measurements of low-
energy electrons in the outer radiation belt,

6. Discovery of large electrical current system in
the outer atmosphere.

7. Discovery of betatron ‘acceleration in outer

It is believed that the satellite, white yet in orbit, is
incapable of generating sufficient power for trans-
mitting signals due to solar paddle damage suffered
during initial paddle extension and the resultant un-
favorable sun “look” angle,

ABLE-4 ATLAS—This vehicle differed from the
ABLE-3 Primarily in that an ATLAS ICBM was used as
the first stage instead of a THOR IRBM, permitting
installation of a hydrazine engine for midcourse
velocity corrections, and to accomplish the ejection

mately 48 seconds after launch. The ATLAS per.
formed as planned over its entire powered flight
trajectory, The trajectory of this flight, from the Atlan-
tic Missile Range to the Vicinity of the moon, was
established to achieve the tightest Possible circular
lunar orbit consistent with the highest Probability of
success. The final burnout conditions were to have
Provided an inertial velocity of 34,552 feet per

Figure f. PIONEER F atellite sebicle shown in

ition. This solar satellite was launched
“auleiie Mint Resge on 11 March 1960.

CONFIDENTIAL Da


oe ie ae cy

‘a

Fighte 1. vtitts conception o

MIDAS

satellite (right). Drawings below show

complete two-stage fight vebicle (right)
and AGENA "B" second stage rebicle

ef).

Inert
Poyload equipment
Orbital
Impulse Propellant:
* Fuel (UOMH)
Oxidizer (IRFNA)
Other

GROSS WEIGHT (Ibs.)

AGENA
aN

1,534

3,246
4780
6423

—
11,009

YAREI-80-5
45,400
a7

120
‘No

Hg Bottle (Propellant

Pressurization}

\ Bottle

bess

1763
1641
3406
12,950

758
72

NUR81-80.9
16,000
290

240
Yes

Hydraulic Package

VHF/UHF
Command Antenna

“S"" Band Beacon

Oxidizer Tank

/

‘

‘

a

5

bow Jet LL Solar Array

Main Engine

MIDAS, Configuration Il, AGENA “B Sotellite

“G" Payload
Infrared Sensor System

BOOSTER—ATLAS ICBM

‘Weight—Wer
Fuel, RP-+
‘Oxidizer (LOX)
GROSS WEIGHT (Ibs)
Engine—MA-2
‘Thrust (Ibs, voc.) Boos?
Sustoiner

Spec. Imp. (rec. vac.) Boost
Sustoiner

AGENA
VEHICLE

ATLAS
BOOSTE!

15,100
74,900
172,300
262,300

356,000
82,100
286
a0



SPACE

S¥3LSOO8 WYEDOdd 3DWES



WDLPM-4-245

CONFIDENTIAL

THIOKOL
SERGEANT

(uAPROVED

—— 31 inches

AEROJET
~~ “SENIOR

—— Winches

XRM-90
Blue Scout It

~N

TM

DERE
PROJECT 609A

Hyper-Environment Test System
peated ade

PROGRAM DESCRIPTION—The Hyper-Environment
Test Program {609A} is divided into R & D-and Opera-
Hional Phases. The R&D phase will be used to develop
and flight test vehicles capable of carrying 25 to
1,000 pound payloads to altitudes of 200 to 50,000
miles. The Operational phase will use these standard-
ized vehicles to permit the economical performance
of flight test experiments in support of scientific
research and advanced military space system
Programs,
Economy—Rellability—Versatifity—In this order
of emphosis are the three significant guides to pro-
gram accomplishment. ECONOMY is being achieved

TS 100A.
NO TM

AJ10-41 TM
(B0KS-8000)
X254-Al TM
=a]

aN

Figare 1. Three variations

of Project GO9A vebicle
demonstrate the mission.
versatility of the program.
XRM-89 N XRM-91
Blue Scout ! 4 vad af Blue Scout, Jr.

-CONFIDENTIAL— HI



“|

DEVELOPMENT PHASE

MONTHLY PROGRESS —Project 609A
Program Administration

© Headquarters USAF has assigned type designa-
tion and proper names to Project 609A vehicles.
Table 1 lists the old configuration designation
together with the new type number and name.

Old Type Proper
Contiguration Designation Name
1-2-3 XRM-B9 Blue Scout |
1-2-3-4 XRM-90 Blue Scout I!
2-3-5-6 XRM-91 Blue Scout Jr.
1-2-3-4s XRM-92 Scout

TABLE I. Old and New Project 609A
Vehicle Designations

WDLPM-4-245

© Because the 609A Operational Program has
not been funded, the DYNA SOAR Program has
requested that two development phase vehicles be
reallocated to support the DYNA SOAR Boost-glide
test schedule for June and September 1961. This
Proposal is highly undesirable since it would increase
costs and severely disrupt the development program.
A partial or complete release of Operational Pro-
gram funds will be recommended to Headquarters
USAF to permit procurement of vehicles in support
of the DYNA SOAR test program,

© The Test System 609A Development Plan dated
21 September 1960, submitted os a revision to the
Development Plan dated 1 June, has been deliv-
ered to Headquarters ARDC. This revision reflects
changes resulting from assignment of ARDC probe
Payload responsibility to the AFRD and includes the

Figure 3. View inside Aslantic
Mle Rage leach comple 1
use prior to the 21 Sep-
somber lawach, It it interesting to
note the simplicity of the launch
control panel. The solid propellant
motors do not } the complex
ibing required for liqni
vas, and consequently donor
weed all the monitorin,
equipment. This is one of sever.
vaasous for the economy realized
in the 609A Program.

-CONFIDENTIAL- Hs


SCANNING
[SYNCHRONIZER|

Shep id verion of groend
Simplified version oj sert~
sation system (left) for wile of
i recomnatssance data. The
data is displayed on 4 TV monitor
with a map overlay. The chart below
shows data flow from the readout
stations to dacition-makin, agencies.
The MIDAS Control Caner or
ied prota ached dip re

splay, cam
determine when an actual nach bas
been launched.

. MIDAS ALARM EMPLOYMENT
Ne PRESIDENT OF U.S.

DEPARTMENT OF DEFENSE

OTHER US |. —__ NORAD OTHER ALUED
GOVERNMENT AGENCIES MIDAS OPERATIONS CENTER] GOVERNMENTS

MIDAS TRACKING &
CONTROL CENTER

READOUT STATIONS

SPACE VEHICLE NETWORK

CONCEPT
The MIDAS system is designed to provide three strategically located readout stations.
continuous infrared reconnaissance of the The readout stations transmit the data

directly to the MIDAS Tracking and Con-

Soviet Union, Surveillance will be con-
mon Surveillance wi “ trol Center where it is procesied. It is then

ducted ial en, veces The ne, displayed and evaluated in the MIDAS
rately pos ‘one ts (Figure I. © oreo Operations Center {Figure 5). If an attack
under surveillgnce must be in line-of-sight is determined to be underway, the intelli-

view of the scanning satellite. Mission cape- gence is communicated to a central Depart-
bilities are shown in Figure 4. The system is ment of Defense Command Post for relay to
designed to accomplish instantaneous read- the President and all national retaliatory

out of acquired duta by at least one of and defense agencies,

SECRET woumis