teert 1,508 16s
Payload equipment 3058
Orbite! ang 4753

(mpube Propellants bast 12,950
Foot (UDMH)

om gn
GROSS WEIGHT (Ibe) 12H 18421

Engine VURI8eS XUN B09
Three, tes, frac.) 15.400 "6000
tener a
. PROGRAM HISTORY
Figure 1.

{iiss concept of SAMOS satellite, The SAMOS Program was included
Line drawing combine flight in Weopon System 1171 when
eeicle (ight and dtald le of WS 1171 was transferred to the
basic AGENA upper stage (lafs). Advonced Research Projects Agency
‘early in 1958. ARPA separated

WS 1171 into the DISCOVERER,

SAMOS ond MIDAS programs with

the SAMOS objectives based on a

‘NOSE CONE visual ond ferret Feconnalssance

system. On 17 November 1959

AGENA fesponsibility for this program was
franeferred from ARPA to the Air
Force by the Secretary of Defense,

PROGRAM MISSION
Cemzee The primary mission of the SAMOS advanced
TAK reconnaissance system is to provide visual and
SECTION electronic coverage of the USSR and its allied
nations. Efforts include development of hard-

wore to permit:

@. Determination of characteristics of enemy

PLANE electronic emissions,

. b. Verification of known targets, detection of
unknown targets,

. ¢. Location and evaluation of defenses,

d. Evaluation of military and industrial

strength.

e. Assessment of high-yield weapons damage.

f. Reconnoitering of troop movements.

9. Location of naval forces throughout the
world.

Bl



©. Satelite Vehicle
Grou Weight 71.6 tb
Gross Weight (Burnout) tb
Specific Impulse (vae) 230 sec
{vor} 63 b
© THAD STAGE ABL 248-a9
74 te
I aon mt
Specific tmpul 2505
Thevst trac) : 3100 tb
& SECOND STAGE As 10-101
Se pe me
igh? Bumout 1
Specific impulse {vac} 268 s0c
Thevst {vec} 7575 \b
A. FIRST STAGE ATLAS “Dp”
Grou Weight 266,390 tb.
Gross Weight {Bernout) 11,790 tb
Threat (8. L) 316.5 see
Specific Impulse (voc) Sustoiner 81,863 tb
speci Imps seer "ae
ic me
Specific Impulse (S. 1.} Booster M7707 I

Figure 3, ABLES vebicle- confgnration dreuie ation litt, Thind
me ber into lena orb

enration swing and specif
in on it dra mp gat eh). 1 4 7

Scientific experiments related to magnetic field and (>) EARTH aT Time

tadiation phenomenon in deep outer space. Also

‘OF AMR LAUNCH

included in the satellite is @ 150-watt transmitter

which is expected to

the satellite and earth over on Opproximately 90 \
‘N

million mile range.
ABLE-5

Program Objectives

1. Place a satellite into lunar orbit with an apogee
of 3,000 nautical miles end a Perigee of 2,000

nautical mites.

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

4. Successful conduct of Payload experiments.

E4

Permit communications between“

” LEGEND
— PATH OF MOON
—s——— ABLE-5 TRAJECTORY
wo == SATELLITE ORBIT OF MOON

WDLPM-4 212


S133f04d 3D vas

projects

COURIER
TROS
MERCURY
609A
DYNA SOAR



‘A THIRD STAGE X.248 (Allegeny Ballistic Leb.) —[————
Thrust at obtitude 3150 pounds A
Specific impulse (vec) 250 seconds
Total impulse 116,400 tos/see. i
a Burning Time 37.5 seconds
Propellant Solid 8
B. SECOND STAGE—AJ10-42 (Acrejet-Genera!) _ |
am Thrust at attitede 7700 pounds
Specific impulee (vo) 271 seconds
Totel lepulse (min) 870,000 Ibs/see
Bueniog time 115 veconds
> Propellant Liquid

FIRST STAGE—THOR REM

_ Thrvat (1)

151,500 pounds c

‘Specific impulse (s.1,) 248 seconds
Specific impulse (vac) 267 seconds

Burning thee
. Propellant

miCKEL-casmiom
TeaMES POR SoLae.
vowle Svstam

138 seconds
Liquid

ray)

Figare 1. TRANSIT 1A theee stage flight vebicle,

on
‘DATTERMS retamaren

Ofte werent
anwease cal

Figure 2. Cutcaway drawing of TRANSIT IA payload (NAV 1).

TRANSIT IA lansched from Atlantic Missile Resge

The TRANSIT Program consists of the flight testing of
four vehicles tp place 200-270-pound satellite pay-
loads into drcular orbits of 400 to 500 nautical
miles. The program Is designed to Provide extremely
Sccurate, world-wide, all-weather navigational infor-
tation for use by aircraft, surface and subsurface
vessels, porticularty in relation to POLARIS missile
firings. The ARPA Order for TRANSIT 1A was initiated
in September 1958 ond omended in April 1959 te
edd TRANSIT 1B, 2A and 28 flights. The program is
currently authorized by ARPA Order No. 97, which
assigns AFBMD responsibility for Providing the
booster vehicles, integrating payloads to the vehi-
des, and flight operations from launch through
attainment of orbit, including communications to the
tracking and data handling facilities. Payload and
tracking responsibility hes been assigned to the
USN Bureau of Ordnance. Applied Physics Labora-
tory is the payload contractor.

ns . Pl


| Powered Hight Trajectory foto Section, tar torent pine
¢ o d
i . 290

Schematic presentation of orbital trajectory following lewach
fr Cad atid ie rie Las
cach station and 4 listing of equipment used by each station,
is giren ow page Aes.

' RECOVERY CAPABILITY

This objective was added to the pro
de, the fri: legeh ecirad ehie
. it rai success
i I Sectudes the arieniion o the sae
be be it a recoverai tal
Be jected frome the ene nent
AGENA vehicle. Becton ipa ibs
40 occur on command on the 17th orbit,
for capsule impact within the presen
mined recovery arta somb of Hace,
Aircraft and surface vessels ae deplopi
within the area asa recovery force,

CAPSULE RECOVERY SEQUENCE

Caprale ejection command is sent to the satellite b the
Cinta, “Marke ‘aatacTM ey fem de, te, 2 The whicle
reorients its position (s00 inset) te berms fo glee to oe
On @ re-entry tory on £1 t. The recovery ca
sale berachata’ ts ectivated at about 96000" fone)

z wl aot ee a tg f

: The recovery force is deployed tn the rxcovery (hesbearh ee



Figure 2. Photos relayed to tracking stations by TIROS payload equipment.
Geographic areas are identified and keyed to the map for reference. The photos
were taken from @pproximately 400 miles altitude. The TIROS payload (left) is
shown mounted on the third stage.



f Pre-launch Tests
i

@ The pre-launch testing of the second and third

4 stages of the TIROS vehicle consisted of a series of
subsystem tests to determine Proper operation and
detailed performance Parameters. Following these
tests system tests were conducted for complete check-
out of the stages before shipment to the Atlantic
Missile Range (AMR). To Provide maximum assurance
that the flight test objectives would be met, the sys-
fem tests were repeated at AMR to determine that
damage to the equipment had not occurred during
transfer,

3
i
*{ @ A fight acceptance fest and composite system
test to insure proper first stage operation, were per-
i formed on the THOR after its erection on the test
stand. Following assembly of the complete vehicle,
subsystem and integrated system tests were per-
< formed on the second stage autopilot and guidance
“system. Ground slectrical power was provided for
these tests. The umbilical was connected to permit
monitoring, of system functions. After the radiation
and interference tests were completed an integrated
acceptance test of the entire vehicle was conducted,
During this test, the vehicle is powered by flight-type
batteries and the umbilical is removed so that date
is obtained only by telemetry ond visual Inspection.

@ A final check of the vehicle was performed dur-
ing the mock countdown one day prior te launch.
This countdown is also used to familiarize tounch
Personnel with the countdown procedures. The TIROS
mock countdown Proceeded smoothly. All engine
checks and electrical checks were completed satis-
+ factorily with the exception of the C-band beacon
+ check. The beacon check Proved unsatisfactory and
when attempts to correct the situation failed the
beacon was removed and reworked. The replace-
ment of two tubes improved the beacon sensitivity
approximately four decibels. No other vehicle prob-
lems'developed and the mock countdewn was com-
‘pleted after having continued 1 % hours longer than
scheduled,

Launch

© The launch countdown started on 31 March and
Proceeded with only minor vehicle problems until
0410 EST, 1 April when a programmed one hour
hold began. Terminal count {T-35 minutes) began at
0510 and proceeded without @ hold until T-2 min-
utes. At T-2 minutes a hold was initiated because of

Figure 1. TIROS vebicle dering liftof from Atlantic Missile
Range Stand 17A on 1 April

ae —€ONFIDENTIAL



NASA Responsibility -
Booster-Capsule integration
Capsule
Ground support
Recovery
| 2-12
|
NASA
Flight
cvoretery Capsules
evle (MeDonviell)
Re-entry
heating,
dynamics,
recovery

Range safety destruct time delay
|Abort-sensing system

Detects dangerous variations

Launch in tank pressures, fuel injector
Pressure, electrical power,
Unmanned non-orbital flights altitude and sustainer hydraulic
_. tanned ‘and unmanned orbital flights Pressure. Can initiate escape
toun AMR sequence
Earth track 33°N/33°S/Lat, (for orbital
flights)
on capability 28 hours Integrated countdown—inckiding pilot insertion
Orbit weight 2500 Ibs. and capsule countdown. AMR launch Stond 14—
- Orbit altitude 105-115 num, Oe ary Pilot and spe radioed to
manual bockyp ment wih Provide: (a) reai 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 212 ~ CONFIDENTIAL

13



| |

by long Tange 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 effect 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 nullitary experimental research
in support of all Air Force facilities, RELIABILITY will
be obtained by a twelve 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

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) batistic
missile trajectories; (d} downward boosted, high-
speed re-entry profiles, and {e) full orbit to approxi-

mate maximum of 400 miles with 150 Pound pay-
loads.

Program Manogement—An abbreviated devel-
Opment plan, covering the R&D phase only, was
Gpproved on 9 Janvary 1959. Funds in the amount
of $9,077,000 have 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
regulariy 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 faunch
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-
ficipate in the assembly, 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.



WDLPM-4 212

-CONFIDENTIAL

Monthly Progress— COURIER Program
Technical Progress

COURIER 1A

© The following modification and checks will be
‘Occomplished prior to the 22 June shipping date:
1, Telemetry channel modification

2. Weight and center of Gravity determination
checks

3. Leak checks

4, Post injection yaw Program insertion

@ = The Flight Test Working Group at AMR has
recommended that the launch date be rescheduled
from 15 July to 19 July.

© Checkout of the ABLE-STAR (A510-104) vehicle
through flight system test has been completed.
Re-allocation of telemetry channels has been made.
Transducers are being added to Provide nose fairing
Pressure and odditional staging information. A
C-Band battery modification to increase the battery
capacity has been completed. This will permit FPS-16
radar tracking from Vandenberg Air Force Base and
Holloman Alr Development Center.

@ Acrojet-Generat Corporation and Space Elec-
tronics Corporation ore continuing component and
subsystem fabrication based on a scheduled launch
date of 1 September.

@ The checkout van and associated test equipment
has been delivered to Aerojet-General Corpora-
tion for checkout of the ABLE-STAR vehicle for
CONVAIR 18,



ATLAS "D'7AGENA "A"

ATLAS “D'VAGENA "RB"

SAMOS Launch Schedule

Monthly Progress—SAMOS Program

Second Stage Vehicles

® System checks of the AGENA vehicle for the first
SAMOS flight are nearing completion with delivery
to Santa Cruz Test Base scheduled for 2 June.

© Final assembly of the third AGENA "A" vehicle
for the last of the SAMOS dual-payload flights was
completed and delivery to the Systems Test Area was
accomplished on 2 May.

© Subassembly of the first AGENA "B’” vehicle con-
tinues on schedule. -This vehicle is scheduled for
launch in April 1961 carrying an E-2 payload, This
is the first of the single-payload SAMOS vehicles
which will carry either an E-2 photo readout or an
F-2 ferret reconnaissance Payload.

Readout: 7

© £-1~Component Tes? Payloads
E-2—~Steerable Reconnaissance Payloads
(with 20-foot ground resolution)

Recovery:
© E-5—High Resolution, Steerable, Recoverable
Payload (with 5-foot ground resolution)

Payloads

© £E-1 Payloads— the third E-1 payload was
received from the contractor in mid-May.

© =E-2 Payloads—Testing and Gssembly of E-2
Payload components is continuing at the contractor's
facility. Functional evaluation of service test models
is in progress, Tests of the E-2 thermal model in the
high altitude temperature simulator indicated that a

© £5 Payloads—Design is continuing on the high
acuity panoramic camera to combine all camera
components as an integrated unit. The optical gloss
for two of the 66-inch, f/5 lenses has been delivered
from West Germany; The release of ‘engineering

hove been accomplished. Ballistic range test of the
recovery capsule configuration Indicate

copevie stability. Wind hunnel tests of the recovery
capsule configuration are being continued.

Ground Support Equipment

© Installation of the vacuum test chamber (for leak
testing E-1 and E-2 payloads Prior to launch) in the
missile assembly building at Vandenberg Air Force
Base is complate except for the electronics portion of
the chamber. Delivery of the electronic portion is

_ Scheduled for June. Delivery of the E-1/E.2 ground

reconstruction electronics equipment, Primary record
cameras, and operating consoles for the Vandenberg
Air Force Base tracking and acquisition station has

BS



WDLPM-4 212

Program Vehicle {see figure 5}

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

Second Stage—ABLE vehicle with Aerojet-General
AJTO-101A propulsion 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 capable 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 ceil paddies, and scientific equipment for con-
ducting the experiments. Satellite vehicle weight is
371.6 pounds.

Launch and Powered Flight

These vehicles will be launched from the Atlantic
Missile Range on a true azimuth of 92.5 degrees.
ATLAS performance parameters have been based
On results obtained from series D R&D flight tests.
Parameters for all four stages are shown on figure
. Final burnout is programmed to occur 23,290,000
feat from the center of the earth at an inertial
velocity of 34,552 ft./sec.

Orbital Characteristics

Major Axis .... + 0.209848 x 10° feet
Eccentricity . 0.245859 degree
Orbital period 765.4 minutes
Apolune . 4,303 nautical miles

+2,605 nautical miles
Duration of eclipses +++... less than 90 minutes

Payload Experiments {See table 3

Scintillation Counter and Pulse Height Analyzer—
measure electron energy (greater than 50Kev per
Particle) and proton energy (greater than 1.0Mev
Per particle),

Jon Chamber and Geiger-Muller Tube—flux and
tate data for electron particles (greater than 1.25
‘Mev per particle) and proton Particles (greater than
25 Mev per particle).

Proportional Counter Experiment—measure inte-
grated intensity of cosmic ray particles: electrons
{greater than 12 Mev per particle). ond portons
(greater than 70 Mev per particie).

Spin Search Coll Magnetometer and Phase Com-
Parator—map the magnetic field (normal to vehicle
spin axis) and investigate very low frequency secular
magnetic field variations. Phase comparator circuit

“uses Spin Search Coll and Flux Gate inputs to deter-

mine magnetic field direction relative to inertial
space.

Flux Gate Magnefometer—mecsure magnetic field
Paraliel to vehicle spin axis. -

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

Plasma Probes Experiment—measure the energy
and momentum of streams of protons having energies
Of the order of a few kilovolts per particle,

Ground Support Program

Ailantic Missile Range—track vehicle for first 14
hours after founch (except for a three hour period
starting a few minutes after liftoff, provide ATLAS
guidance, provide first vernier correction for payload
stage.

Manchester, England—track vehicle for 7 hours,
starting 13 minutes after launch, Provide second
vernier correction for payload stage (and additional
corrections as required).

South Point, Hawail—Transmission of commands,
including verier corrections as necessary,

Millstone Hill, Massachusetts—track vehicle for 7
hours, starting 13 minutes after liftoff.

Other support stations include, Singapore, Goldstone,
JPL and NASA stations, and the SPAN center at
Los Angeles.



Early in 1958, the decision to accelerate the national space effort was made effec-
tively possible only because of the availability of the THOR IRBM. THOR No. 127
was diverted from the R&D flight test program for use as the ABLE-1 space probe
first stage, With top national priority cssigned to the space research effort, THOR
No. 163 was used to boost the DISCOVERER | into orbit on 28 February 1959. Since
then, the THOR has become a reliable operational IRBM and highly reliable also os
@ booster for space vehicles. During 1959 all THOR boosted space flights achieved
completely successful first stage performance. THOR performance has been increased
through weight reduction modifications and ure of RJ-1 {instead of RP-1) fuel. in

April 1960 a modified THOR, designated DM-21, will be available, incorporating a
shortened guidance compartment and additional weight reduction

changes. In July
re ys

aa

1960 THOR thrust will be
increased to 167,000
pounds through installation
of the MB-3-Block Il engine;
The first DM-21 vehicle will
be used to boost DISCOV-
ERER XVII.

THE ATLAS ICBM, providing over twice the thrust of the THOR, will be used os
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
from the Atlantic Missile Range on 18 December 1958. Designated Project Score,
this vehicle (ATLAS 10B) successfully placed a communications Payload satellite
into orbit around the earth. In November 1959 the ABLE-4 space probe did not
attain orbit; however, the ATLAS first stage performance was entirely successful.
The first ATLAS-boosted flight test vehicle in Project Mercury was launched on
7 September with all objectives essentially achieved. ATLAS performance on both
the 26 February and 24 May MIDAS launches was exceptional. Future flights will
use modified ATLAS series “D* missiles to carry increased payload weights.
fo carry increased payload weights. ‘

Project Mercury boosters are being
modified also to include abort-sensing
and other pilot safety features. The suc-
cess of the first three ATLAS boosted
space flights, plus the increased Per-
formance and reliability being demon-
strated in the ATLAS R&D flight test
Program, lend confidence in this

booster as a means: of realizing
advanced space objectives.

SEGREF«



more odvanced phases was replaced by « single
integrated effort to which the code name ADVENT
wos applied. ADVENT calls for an R&D program for
@ 24-hour global communications satellite system.
The feasibility. of placing a'sateliite in @ predeter-
mined position in a 19,300 mile equatorial orbit must
be demonstrated. The satellite must be capable of
providing worldwide communications on a real time
basis at microwave frequencies with a high chonnel
wide bandwidth capacity. Amendment 5 also
requires the design of a single final stage vehicle for
microwave equipment compatible with launching by

either AGENA “BY or CENTAUR second stage
boosters,

The ADVENT program, as defined in amendment
5, wilt consist of the following flight tests;

@. Four ATLAS/AGENA “8” flights, nominal 5,600
nautical mile orbiis,

b. Seven ATLAS/CENTAUR flights, launched from
the Atfontic Missile Range into 19,000 mile
equatorial orbits.

©. Three flight tests, vsing payload space on
NASA ATLAS/CENTAUR R&D flights Number

4, 5, and 6.

Figure 2, Initial design of fual stage vehicle.

WDLPM-4 212



STATUTE mites)

ez

Figure 2, Typical SAMOS trajectory, lawnch- to-orbit.

Ferret Reconnaissance...



Fi, A, Artis# MID,
sane (righ). Drawiate fi Nias
aad ai nea fe hice fia)
sabicle (lef). vn

156 1763
Payload equipment 3,246 1441
3

i ‘ SS
i

+ Ortltat 4790 1404
Impoke Propelants- 6423 12,950
Feel (UDI)
Oxidizer (1RFNA)
. Other $06 758
GROSS WEIGHT ftbe.) 11,209 Wz
Engine VUREI-Bo-S  X1881-80-9
‘Thrwtt, Ibe, (voc) 15,600 16900
Spec. Imp., sec. frac) ELA 290
Bern Time, sec. 120 240
Restert Provisions No Yes

SOLAR
4 ARRAY
anreon a OESTRUCT

DATA LINK “NOSE CON!

i
§
i
i
1
‘
L
i
1
1
i

THERMAI TM EX! EQUI OXIDIZERFUEL
SHIELD ANTENNA = SEPARATION ANTENNA COMPT, TANK TANK pooster
NOTE: AQENA “A configoraton accept SOOSTER—ATLAS Ica
for solar paddies (AGENA “B only) Weight—Wet 15,100
Fuel, RP. 74,900
Oxidizer (LOX) 172,300
' GROSS WEIGHT (ibe.) 262,300
. Engine—MA-2
Thevst (Ibs. vac) Boost 356,000

. ‘Sustainer £2,100
Spec. Imp. (sec. vor) Boos 206
Susiainer 310

i y
B veuness SECRET



Figure 6. SAMOS concept, showing reception of commands and sransmission of data
between jt

satellite and grownd station; and subsystem

For economical testing of components @ dual.
capability visual ond ferret Payload will be used dur-
ing. the early development phase. On later flights
only a visual or ferret system Payload will be carried.
These payloads will be housed in the AGENA vehicle
(Figure 1). .

Data collected by the visual payloads will be elec-
tronically tronsmitted in the teadout system and
retrieved in the recovery system. Ferret data will be
transmitted electronically. These systems are com-
Posed of the AGENA vehicle, ATLAS booster, launch
facilities, tracking facilities, and a communications
and data processing network. The recovery system
fill alto include a re-entry copsule and a recovery
force. .

CONCEPT

ent upon the width of the area under surveillance.
Farly versions will have a useful life of approximately

functions (schematic),

ten days. The readout
of four months with
configurations of one
have a useful life of

systems will have a useful life
design objective in certain
year; recovery systems will
fifteen to thirty days.

ing developed. The E-1 pay-
ponent test payload which is
| ferret payload. The E-2 photo-
development by Eastman

load is a photo com
combined with the F-
Sraphic payload, wu:
Kodak Company, includes



WDLPM-4 212,

Monthly Progress—- COMMUNICATIONS
SATELLITE Program

Technical Progress

Microwave Communications Equipment

© Representatives of AFBMD, Space Technology
Laboratories (STL), and Army Signal Research and
Development Laboratory (USASRDL) attended o
coordination meeting on 10-12 Moy. Drafts of work
stolements were teviewed, satellite interface areas
involving the communication equipment were dis-
cussed, and consideration was given to contractor
relationships.

@ A microwave communication subsystem integra-
fion meeting was held on 25 May at USASRDL,
attended by General Electric, STL and AFBMD per-
sonnel, Present scheduling concepts were discussed
for compatibility with the Program. Critical interface
relationships requiring immediate resolution were
defined. Plons were formulated . for a USASRDL
antenna engineer to work direcily with G.E, vehicle
structure engineers in arriving at a firm configuration.
© Final specifications for ground antenna, ground
terminal and satellite terminal have been completed.
One contract will be placed for development, fabri-
cation and installation of the 60-foot automatic
tracking antenna system for the ground terminal
equipment. A second contract will be awarded for
the development, fabrication, testing and installation
of the microwave communications equipment for the
satellite and ground terminals, Work statements and
Specifications for the antenna were completed and
requests for proposals mailed on 24 May. It is
expected that requests for proposals on the com-
munications equiment will be mailed to bidders on
3 June,

© Procurement date is being processed for award
of @ contract to Varian Associates for the develop-
ment of a prototype high power X-band tube for the
ground terminal equipment.

Lawnch Vehicles

e A summary wos prepared for ARPA on the
ATLAS/CENTAUR capability to place a final stage
vehicle into a 24-hour circular equatorial orbit at
105 15 degrees west longitude assuming various
final stage vehicle Propulsion capabilities. Results
with propulsion capability of zero and 1000 feet per
second. are given in paragraphs } and 2, respectively,
@s follows:

1. Assuming a launch trajectory in which CENTAUR
second burn period occurs at the first northerly cross-
ing of the equator; and with zero velocity deficiency,
the ATLAS/CENTAUR combin

Pounds into orbi 3 II di success,
The estimated weight of an R&D final stage vehicle
with zero propellant for velocity deficiency, and with
nO capability for lunar perturbation compensation is
806 pounds. This system does not Provide an opera-
fional indexing capability,

2. Assuming a launch trajectory in which CENTAUR
second bum period occurs at the first southerly cross-
ing of the equator, and with 1000 feet per second
velocity deficiency at separation, this vehicle com-
bination can place 1170 Pounds into orbit with a
3-sigma certainty of success. The estimated_weight
ofan R&D final stage vehicle with propellant to make .
Up a velocity deficiency of 1000 feet per second,
and with no propellant for lunar or solar perturbo-
fion compensation is 988 Pounds. This system does
provide an operational indexing capability.

Final Stage Vehicle
e A work statement has been completed in rough
draft form to reorient the General Electric Company
final stage vehicle contract in accordance with the
24-hour mission defined in Amendment No. 5. The
draft has been coordinated informally with ARPA,
General Electric, USASRDL, ond AFBMD. Although
final coordination has not been accomplished, this
work statement and its annexes will require very
little revision when a development plan has been
approved, assuming no major reorientation of the
Program,
e A report has been completed on a feasible tech-
nique for attitude stabilization and earth reference
acquisition of the final stage vehicle following second
stage separation. The acquisition technique devel-
Oped in the report is being simulated on an analog
computer to analyze quantitatively the over-all sys-
tem behavior for variations in the filter characteristics
and in internal disturbances,
e A study has been completed and a report is
being prepared of the cumulative effects (stored
momentum per orbit} of solar radiation Pressure on
the final stage vehicle. Equations were derived both
in terms of body coordinates and internal coordi-
nates. The second approach yields a simpler expres-
sion, but still requires numerical integration for
quantitative results,

Ground Stations
© Site surveys have been initiated on the East and
West coasts of the United States to determine svit-
able locations for ADVENT ground stations. Topo-
graphical studies of the middie Atlantic area are
being made by air to insure meeting the line-of-sight
requirements.



indicate successful performance of the system.

Although the APL beacon is being displayed by o

, operational, Subsequent AGENA “A” DISCOVERER
vehicles will carry the Complete system.

DISCOVERER XH

e A flight readiness date for the launch of DIS-
COVERER XII depends upon the installation of the
diagnostic payload and completion of the recovery
System fest program. A re-disposition of the recovery
forces is being effected for this flight. Telemetry
receiving equipment is being installed on Christmas
istond in the South Pacific to Provide telemetry
reception in the event the actual te-entry trajectory
Carries the capsule beyond the planned recovery
range . Ground tracking stations having telemetry
receiving equipment are located at Kodiak, Alaska,
Kaena Point, South Point, and Barking Sands,
Howall. Five C-54 aircraft will provide telemetry
reception in addition to telemetry on three surface
vessels, the Pvt Joe E. Mann, the Dalton Victory, and
the Halti Victory. Additional instrumentation ond

A?



WDLPM-4 212

—CONFIDENTIAL

Monthly Progress—Project MERCURY

Flight Test Progress

@ During May the ATLAS booster and the
‘MERCURY capsule for the second flight test (MA-1)
were delivered to AMR and are undergoing pre-
launch hangar checks. The ATLAS 50D booster and
the capsule will be mated in mid-June for the sched-
uled mid-July launch. Launch will be made from
Atlantic Missile Range Complex 14 with trajectory
Parameters and test objectives as ovilined in the
April report. An ATLAS R&D missile is presently
erected on stand 14 and will be launched prior to
MA-1, Present stand loading has another ATLAS
R&D missile scheduled for launch from stand 14
between the second and third MERCURY flights.

@ The capsule for the third MERCURY flight (MA-2)

will be a McDonnell full scale production mode! with ~

live escope system, live posigrade rockets and
dummy retrorockets. The capsule will incorporate all
six primary capsule systems;

1, Communications system

2. Automatic stabilization and control system
3. Automatic reaction control system

4. Environmental control system

5. Electrical power supply system

6. Landing and recovery system

©@ The primary copsule test objectives for the MA-2
flight are:

1. Recover capsula

2. Determine the integrity of the MERCURY cap-
sule structure, ablation shield, and afterbody shingles
during a simulated normal re-entry from orbit.

3. Determine the capsule full-scale motions and
afterbody heating rates during a simulated normal
re-entry from orbit.

4. Evaluate the performance of the operating
capsule systems during the entire flight.

5. Evaluate the compatibility of the capsule escape
system with the ATLAS/MERCURY system.

@ The secondary capsule test objectives for the
MA-2 flight are:

1, Establish the adequacy of ‘the focation and
recovery procedures.

2. Establish prelaunch, launch, monitoring, and
“recovery procedures for operation personnel.

e The primary booster test objectives for the MA-2
flight are:

1. Determine the ability of the ATLAS booster to >
release the MERCURY capsule at the position, alti-
tude, and velocity defined by the guidance equations.

2. Determine the dosed-loop performance of the
Abort Sensing and Implementation System.

@ A secondary booster test objective for the MA-2
flight is to obtain data on the repeatibility of the
Performance of all ATLAS missile ond ground systems.

CONFIDENTIAL 1s



ALTITUDE-——NAUTICAL MILES

e000 T T T to } i
voco }— ATLAS/AGENA “A” and “B" “T ATLAS/AJ10-104/ABL 248 —|
600
oo} ‘ §
3 eco |:
zTM wo N\
io 2 IN
i ‘\
t000 3
ae q ad Fs
< 600 &
=
“00 ua as ae 40 3
ad T T 1
200 ATLAS/AJ10-101/ABL 248 —
1 2 3 4 5 400 3
: 4 g
ATLAS/MERCURY
1000) 5
400 N
800 N
600;
«o IN
200 10 IN
100 a4 NX

PAYLOAD WEIGHT x 1000 POUNDS

1. AGENA “A"— Polar Orbit
2. AGENA “B"— Polar Orbit
3. AMR—90 degrees

WDLPM-4 212

BURNOUT VELOCITY—FPS x

4. Lunar Probe
5. Venus Probe

1000



© Initial design of the advanced Presentation unit
for infrared payload ground display continued at
General Eleciric. The first unit is scheduled for deliv-
ery in May 1963.

Communications and Control

@ Procurement has been authorized for a third
Programmable Integrated Control Equipment (PICE)
unit for installation in December os part of the
interim MIDAS equipment at the New Boston, New
Hampshire tracking station. This unit will be identical
to the units at the Satellite Test Center (STC) and
Vandenberg Air Force Base except for a smaller
memory unit and fewer access registers. Commands
from the STC to the satellite, orbital predictions and
other data are transmitted through the STC PICE to
the tracking station PICE for distribution in the station
or transmission to the satellite. Tracking, payload

data and other date are returned through PICE to
the STC for computation, display, or storage.

Facilities

Atlantic Station—Studies cre being con-
tinued to locate a svitable site for this station.

@ Vandenberg Air Force Base—Work on the
modification to the data acquisition and Processing
building to accommodate a revised computer con-
figuration started on 9 May. Completion is sched-
uled for 16 July.

C7



~ CONFIDENTIAL

_ Monthly Progress-——DYNA SOAR Program

Program Administration

_— e The DYNA SOAR Program is still in the prelim:
inary planning stage and it will be'some time before
the assembly of hardware begins and component

of the Step I contract including design trade studies
ond booster hardware program planning. On 20

Company and booster engine program planning. A
_ systems engineering and technical direction con-

tractor for the booster system is presently being

selected. Specific areos of Progress include:

- 1. Statements-of-work for the associate contrac:
tors (Martin Company and Aerojet-General Corpora-
fion} have been prepared and approved.

7 2. The booster performance specification has
been prepared and approval is expected in July.

3. The detailed programs for carrying out the
design trade studies have been established.

4. The contractors have organized the adminis-
trative and engineering staffs tequired to support
the DYNA SOAR Program,

@ During the design competition the contractors
completed many Preliminary design studies to sup-
Port their proposals, With the selection of contractors
‘essentially completed, design data is being ex-
changed and a high degree of cooperation in solv-
ing interface problems has been exhibited. Design
trade studies are being conducted in many areas,
among them ore studies to determine optimum
booster fin configuration, booster structural rein-
forcement, staging methods, and booster-glider
interface. Many of the studies will be completed
within 90 days and summary reports, including
Fecommendations, will be submitted to BMD/WADD
Ot that time. These reports will become part of the
Preliminary design data for the selected design.

WDLPM4 212 —CONFIDENTIAE is



WDLPM-4 212

ADVANCED SYSTEMS STUDIES

1. The Advanced Systems Studies Division has sev.
eral space studies in Progress. The purpose of these
studies is to determine the military missions and
mode of operation in spoce, For the purpose of
study, space has been divided into three broad
Greas; earth orbital, Wnor, interplanetary. Studies
In the lunar and interplanetary area ore being man-
aged and directed at AFBMD. There are two studies
in the Lunar area: SR 192 (U} Strategic Lunar Sys-
fem, and SR 183 (U) Lunar Observatory. There is one
study in the interplanetary area: SR 182 (U) Strategic
Interplanetary System.

2. The objective of SR 192 is to determine a military
Posture in the lunar area which is defined as the
surface of the moon ond the area in its surrounding
Gravitational field. This is a broad conceptual type
study which will examine all facets of military opera-
tions such as Offensive, defensive, and supporting
systems. This study was funded with $600,000 in
Fiscot Year 1959 and final reports from the con-
tractors are due at AFBMD by February 1960. in
addition to the three funded contractors working on
this study, there ore three voluntary. contractors.
Consequently, the total effort being applied is esti-
mated as equivalent to one million dollars,

3. An obvious military requirement in the lunar area
will be a surveillance and intelligence collection sys-
tem. Therefore, SR 183 {U) Lunar Observatory was
initiated to examine this problem. The objective of
this study requirement is to determine @ sound and

logical approach for establishing a manned intelli-
Gence observatory on the moon from which the
entire earth and its surrounding area can be kept
under continuous surveillance. Ail ecrth orbital sys-
tems can be monitored and enemy activities in space
and on the lunar surfoce can also be watched, All
Possible types of sensors and their probable ranges
will be examined. This study will also include the
‘means of logistically supporting and establishing the
lunar base. This study was funded with $420,000 in
Fiscal Year 1959. Three contractors were funded
and three additional contractors are Performing the
study on a voluntary basis, Consequently, it is esti-
mated that this study has the equivalent of $1.5
millions being applied to it,

4. The interplanetary area is being studied under
SR 182 (U) Strategic Interplanetary System. The
objective of this study is to determine the possible
mallitary missions and the type of equipment neces-
sary for operations in the interplanetary area. This
area Is being studied separately from the lunar area
because the operational Problems involved appear
to be somewhat different, the distances are much
Greater; our present knowledge of the area is lim-
ited, therefore, special types of navigational and
Propulsion systems will be required. This study was
funded with $285,000 in Fiscal Year 1959 which
has been distributed among three contractors. Con-
tractors’ final reports are due at AFBMD in Feb-
ruary 1960.

M-1



DISTRIBUTION

Headquarters, 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

Amold Engineering Development Center
Air Proving Ground Center

Air Defense Command

Air Training Command

Alr Photo and Charting Service

Air Force Missile Test Center

United States Air Force Academy

Air Technical Intelligence Center

6555th Test Wing (Development)

Air Force Ballistic Missile Division (ARDC)
Ballistic Missiles Center (AMC)

Assistant CINCSAC [SAC MIKE)
Aeronautical Chart and Information Center
Rand Corporation

San Bernardino Air Materiel Area

6594 Test Wing (Satellite)

1002 Insp. Gen. Group

3415 Technicat Training Group

Tactical Air Command

32

Sem neers rwauuuune =

ry

~=-nNnowog

WDLPM-4 212

@EReT



CONCEPT .

The MIDAS system is designed to provide
continuous infrared reconnaissance of the
Soviet Union, Surveillance will be con-

ducted by eight satellite vehicles in accu-
rately Positioned orbits (Figure 3). The area
under surveillance must be in line-of-sight
view of the scanning satellite. Mission capa-
bilities are shown in Figure 4. The system is
designed to accomplish instantaneous read-
out of acquired dota by at least one of

three strategically located readout stations.
The readout stations transmit the data
directly to the MIDAS Control Center where
it ts processed, displayed, and evaluated
(Figure 5.) Hf an attack is determined to
be underway, the Intetligence is communi-
cated to a central Department of Defense
Command Post for relay to the President
and ali national retaliatory and defense
agencies.



ABLE Vehicle

The ABLE upper-stage vehicle has been flight tested suc-
cessfully as the second stage on THOR re-entry vehicle
tests, ABLE Projects and TRANSIT 1A. The vehicle uses
AJ10-42 of AJI0-101 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 burning. Vehicles using the

‘Contractor:

Aerolet-General Corp.

Helge 18 feet 7 inches
Diameter 4 fet 8 Inches:
‘Weight

As10-42 4622 pounds
10-101 4178 pounds
Poot

Unsymmetrical Dimethyl Hydrazine

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
odvanced solid propellant engine of its
size available at the time. Since the
engine had not been qualification of
flight tested, test firings were conducted
in a vacuum chamber simutating approxi-
mately 100,000 feet altitude. Design
modifications involving the igniter,
Rozzle, and internal insulation we
found to be required. The modified
engine performed with complete satis-
faction on the successful flight of ABLE-1

and subsequently on ABLE-3 and ABLE.4
THOR.

Ss

“dina BT

AJ10-101 system are spun with the third stage and Pay-
load prior to second stage engine bumout to provide spin
stabilization of the unguided third stage and payload.
On flight vehicles 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 separation Plone. Only minor
differences exist between the two Propulsion systems,

Oxidiner
Inhibited White Fuming Nitric Acid

Guidance

AJ10.42

Redio-inertiol (871)
Ad10-101

Advosced Guid, Syxt. (sty
‘Computer (hurroughs J-1)

Used as second stage fer:
AN0-42 — TRANSIT 1A, TIROS
AS10-101 — ABLE 3 and 4

ABL 248
Vehicle

Contractor:
Allegany Ballistic Laborotery
Height 4 feet 10 inches
Dlameter 1 toot 6 inches
Woigkt 515 pounds
Fool Solid
Used es third stege on:
ABLE 3 and 4
TRANSIT 1A, TIROS

wand A

ae WDLPM-4 212



ui , : °
Although originally designed os the basic sat-
ellite vehicle for the Advanced Military Satellite
Programs, flight testing of the AGENA was accel.

AGENA

erated when the DISCOVERER Program was Uaciboed Mts ond Space Dison
created, using the THOR/AGENA combination, Engl tector
Because of its @vailability, the Bell Aircraft Bell Aircraft’ Corp,

(R81-Ba-3 rocket engine was selected for AGENA
Propulsion, and later modified to use unsymmet-
tical_di-methy! hydrazine instead of JP-4 fuel.
Subsequent modifications resulted in the AGENA
“Be contiguration, in which Propellant tank
capacity wos doubled and the engine modified ,
fo provide single restart and extended burn 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 control wos
developed to meet the critical orbital eccentricity

length

“A” version 14 foot

“B" version 19.5 feat*
21 feet**

Diameter @inches

‘Weight
“AM version 7,987 pounds
“B" version 14,800 ponds

tngine
“AN version Yuna 20.5
“8" version XLR81-80-7°

XURB1-B0.9°*
and attitude requirements for the programs in- vow
volved. Gas jets and reaction wheels ore used bed en
to control attitude. Payloads may be installed '
on the forward equipment rack or distributed Gedenee ——_optcaL int
throughout the vehicle, The flight test program Used as second stage ter:

also has been used to develop a recovery capa- DISCOVERER (XVI! & subs)
bility for @ payload capsule which is ejected MOAB fines ean
from the orbiting satellite,

ABLE-STAR Vehicle |

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

ing systems. Propeilants are fed to the thrust chamber by a high pressure helium Height 14 feat 3 inches
Ges system, The thrust chamber Is gimbalied by electrical signals to provide pitch
and -yaw control during powered flight. Roll control during powered flight is Diameter 4 test 7 inches
achieved by ‘expelling nitrogen through a system of Nozzles in response to elec- wn
trical signals. Roll contro! during coast periods uses a parallel circult at lower thrust, Weight Poweds
Attitude controt for coast Periods up to one-half hour Provided in the current design Engl As10-104
can be extended by increasing the nitrogen sup l. with Restort Capability
Neczle Expansion Rotio—40.1
Fuet
Untymmetrical Dimethy| Hydrazine
Cxidizer
Inhibited Red Fuming Nitric Acid
- Qvidence
‘STL Advanced Guidance System
Rorroughs J-1 Computer
Used as second stege fort
TRANSIT 1B, 2A, 28

COURIER TA, 18



telemetry will transmit all phases of the DISCOVERER
XII payload recovery sequence from ejection through
‘parachute deployment,

Techalea! Progress

Second Stage Vehicles

Differences in DISCOVERER vehicle configurations
Gre defined on page A-5.

© The third AGENA “BY vehicle {XLR-81Ba-7
engine) underwent hot firing tests on 3 May at the
Santa Cruz Test Bose. The first and third vehicles .
have been retumed to the Systems Test Area for
rework ond a second systems check prior to Air
Force acceptance. The second vehicle is in storage
following Air Force acceptance on 3 May.

© The Preliminary Fight Rating Tests (PFRT} for the
XLR-81Ba-7 engine were rerun because of the gas
Generator propetiont valve malfunction during fast
month's tests. Safe functioning of the engine after
simultaneous. firing of both starter Propellant charges
was demonstrated. The modifications made to the
90s Generator propellant valve have solved the valve
binding problem,

© Evalation of Zirconia thrust chamber coating
was continued during the month. Tests of modified
injectors for the XLR-81Ba-9 engine indicate a suc-
cessful remedy for thrust chamber erosion problems
may be found In this change. Informal component
level PFRT type tesis of the XLR-81Ba-9 engine

began during May. Engine level tests are scheduled
to begin in dune using existing thrust chambers. An
extension of the PFRT program will be conducted to
Prove the reliability of the thrust chamber modifica-
tion prior to the first launch,

e Testing of the XLR-81Ba-9 engine with 45:1 area
ratio nozzles continued at Amold Engineering Devei-
opment Center. A test series wos initiated on 6 May
Including sfarts and restorts at temperatures of plus
20 and minus 10 degrees F.

Blomedical Capsele

e Delivery of the test capsule {USE-77) to be used
in the specialized biomedical environmental testing
of Mark I flight components has been delayed until
August. Upon arrival a series of vibration, centrifuge,
and impact tests will be conducted fo assure reliable

flight operation. - /

NS

e The conversion of launch pad 5 at Vandenberg
Air Force Base to AGENA “B" copability has been
started. AN ground handling and service equipment
necessary to make the change has been shipped to
the site. Included is the new mast extension required
fo accommodate the greater length of the AGENA
“BY vehicle. Changes are also being incorporated
into the propellant loading system which will Permit
two acid trucks to load propeliant into the vehicle.

Figure 3. Model XLR-61Ba-9 engine

with titeninm 43:1 area ratio-nozile exten.

sion as the right, The dual sherter cans are mounied on the upper left

AS

WDLPM-4 212



Performance Graphs — 23.2.5

THOR/AIIO-42/AB 248 3000 THOR/ASTO-I01 /ABL. 248
2000
i 1000
Bre
800
600
<f ! [ !
400
L ) L S
200
A 1 1 A ' f A F 1 F : A
2 4 6 6 10 12 2 4 é 8 it) 12
THOR/AJIO-104. 3000 " THOR/AGENA “A” ond “BTM
2000
j -
3b [ ?
200
5 oF ;
B 600
L 1 L
400
L 2 L
3
200
4 i 1 1. i L L 4. 1 7% 1 i
2 a 6 8 10 2 2 4 6 8 10 12
Paylood Weight x 100 pounds Poyload Weight x 100 pounds
1, Polar——-AMR or VAFB 4. VAFB—AGENA "B” (XLR81-Ba-7)
2. AMR—90 degrees 5. VAPB—AGENA “B” (XiR81-Ba-9)

3. VAFB—AGENA “A“

6 steer : | WDLPM4 212


Ferret Reconnaissance System
© Ferret reconnaissance system payloads ore
being developed in a minimum number of contigura-
tions, The designation and purpose of each con-
figuration is as follows:
© F-I—R&D Test Payloads
F-2—Digito! General Coverage Payloads
F-3~ Specific Mission Payloads—Analog
Presentation .
© F4—Techaical Analysis (study stoge only)

Payloads

© F-1 Payloads—the third F-1 Payload was: re-
ceived from Airborne Instruments Laboratory on 27
May,

"© F2 Payleads—Testing and assembly of F-2
Payload components is continuing at the contractor's
Tacility. Results of the F-2 thermal control for all
Orbital conditions are satisfactory. Functionol evalve-
fion of service test models is in progress,

Ground Support Equipment

° Instollation and prelieinary functional testing of
the F.1 data conversion equipment in the interim
Grea of the Satellite Test Center ware completed
during the report period.

Facilities

e Point Arguello—Equipmeit installation for Pad 1
|s essentially complete, and systems tests of these
equipments in the launch and operations building
and service building were underway at the close of
the report period. Final inspection of launch stand 2
was held on 12 May. All deficiencies are in the
Process of correction and will be completed earty in

Pig 7. Over-all vie Pad 1 at Point As ywello, Installatie Leaanch mositoris tontrol, and
_ “we "roo beatae ale etal of each, ma od

WDLPM-4 212





Flight Time Inertial Speed Downrange Altitude
Point (seconds) Comments (ft/sec) Distance (n.mJ (n.mJ
2-A is vehi 18 2A 1B 2A 1-A 2A
1B 28 Transit vehicles 28 28 28
1 10 10 End of vertical rise 1,346 1,346 ) ° 0.077 0.077
2 17 167 . First stage burnout 13611 12,929 752 797 M2 B83
End of second stage
3 442 448 first burning period 24,539 24376 785.5 778.0 200.1 203.0
4 1489 1,447 pace a tecond siege 27496 27 42502 40800 5000 00.0
5 1,504 1,462 Injection into orbit 24,258 24259 4416.3 4,130.0 500.0 500.0

FLIGHT TRAJECTORY —TRANSIT 18, 2A ond 28

Orbital Performance Achievement of program
objectives is based primarily on measuring the
doppler shift of satellite trensmitted 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 relationship
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 iwo 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 any point in the orbit
should be known, Using known orbital positions,

ships and aircraft can then use satellite signals to
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
will be provided by the Alfantic Missile Range. A
mobile tracking and telemetry van will be located in
Germany for TRANSIT 1B and South America for
TRANSITS 2A ond 26. These locations were selected
as the closest. sites possible to the orbit injection
point.

Fg



The’ DISCOVERER Program consists of the design,
development and flight testing of 33 two-stage
vehicles, ‘using the THOR IRBM as the first stage
booster and the AGENA as the second stage, satellite
vehicle. The program was established early in 1958
under direction of the Advanced Research Project's
Agency, with technical management assigned to
AFBMD. On 14 November 1959, program respon-
sibility was transferred from ARPA to the Air Force
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-
noissance satelite Programs,

PROGRAM OBJECTIVES

to) Flight test of the satellite vehicle airframe, pro-
Pultion, guidance and contro! systems, auxiliary
Power supply, and telemetry, tracking and com-
mond equipment,

lb) Attaining satellite stabilization in orbit.
{c) Obtaining satetiite internal thermal environment
data.

td) Testing of techniques for recovery of a capsule
jected from the orbiting satellite.

fe} Testing of ground support equipment and devel-
pment of personnel Proficiency.

{f} Conducting bio-medical experiments with mice
Gnd small primates, including injection into orbit,
re-entry and recovery.

PROGRAM SUMMARY

Early launches confirmed vehicle flight and satellite

orbit copobilities, developed system reliability, and

established ground support, tracking and data acqui-

sition requirements. Later in the program, biomedical
and advanced engineering Payloads will be flight

Tracking and command functions are performed by
the stations listed in the Table on page A-d. A history
Of DISCOVERER fight to date Is given on page A-5

e
|
56.9 teat
r
td
SECOND STAGE “an ba iad
Weight
taoet taer laze 1346
Payload equipacet Eid a4 915
1739 2218 2216
Impulse propelionts 6,525 12,990 12,980
7a ill su
TOTAL WEIGHT $562 18476 15722
Engine Model VARS XURBI-Bo-7 — XLRG1-a-9
Thresi-tbs., vec, 15,400 13,600 16,000

109,000

167,900



SW3LSAS 3D vdS

sysfems.

COMMUNICATIONS
SATELLITE

DISCOVERER
SAMOS
MIDAS



PROJECT MERCURY

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

Design, engineering studies Launch support

Equipment modification Trejectory deta

Hardware fabrication Missile allocation
Flight scheduling

. Provide fourteen (14) Modify boosters for NASA prelim. Launch, control and define trajectories
boos

ATLAS ters. inary research and manned orbital of booster-capsule vehicle up to, and
filght and safety objectives. Induding, injection into orbit.

Table 2, AFBMD responsibilities ie support of PROJECT MERCURY.

Project MERCURY Launch Schedule

CONFIDENTIAL WOLPM4 212


WDLPM-4 212

‘CONFIDENTIAL

toined exposure in the low-temperature environment,
On completion of the test, it wos noted that some
cracking of the filter glass occurred because of the
low temperature. Although these cracks have little
effect on the conversion efficiency, improvement of
the adhesive which will eliminate this problem is
underway. In addition, intemal failure of the solar
cells as © result of the sustained exposure to low
temperature has been observed. This known charac-
teristic of the solar cells has resulted In selection of
© lunar orbit which will minimize the duration of
eclipses,

© Sonotone hos delivered one hundred cells for
the poyload batteries. These cells have been graded
on the basis of results obtained in two charge-
discharge tests. The batteries for the type-test pay-
load have been fabricated and were delivered for
installation in the Rayload. A general evalvation
test plan, modified as a result of the PIONEER V
battery performance data, has been Prepared to
determine the degradation effect on nickel-cadmium
batteries of vacuum, temperature, eycling and over-
charging. A battery is being prepared for use in a
thermally controlled vacuum test duplicating the
‘octual PIONEER V duty cycles, The balance of the
Cells for the ABLE-5 batteries has been ordered,

@ A test program for the temperature control units
has been established and is reflected in the speci-
fication for these units. Rework of rejected temper-
cture contro! units can be accomplished without
significantly affecting the fabrication of complete
temperature control systems.

e The problem of payload antennas heating dur-
ing operation of the vernier or injection motors has
made a redesign of the Payload antenna system
Necessary. The ontennas will now consist of nickel-
plated stainiess steel. Delivery of this new antenna
will not delay payload assembly and test.

@ ABLE-4 command receivers were converted to
the ABLE-5 configuration and have completed envi-
ronmental qualification tests, Work has continued on
the 2-wait transmitter for ABLE-5 and six units are
now ready for environmental tests. Modulation and
frequency stability problems discovered during early
testing have been remedied.

two flight units ore undergoing acceptance testing
Gt this time. Three No. 2 converters have been deliv.
ered to the transmitter group for detailed electrical
tests,

@ the type-test digital decoder, which was con-
structed from spare ABLE-3/-4 components, has been

e {t has been decided to incorporate a 2,000 psi
nitrogen boitle into the payload Propulsion system.
Lead time on Procurement of this bottle requires that
@ dummy be wiilized in the type-test payload, No

A surge chamber has been incorporated into the
Conax vaive clusters. Five complete tesis of the four
start engine system and six tests of the two start
system have been completed without failure. Addi-
tional tests are planned.

© Vibration tests of the ABLE-4 spare payload
structure, reworked to an approximate ABLE-5 con-
figuration, were conducted to confirm the suitability
of the ABLE-5. payload structural modifications under
vibratory loads. A test wos made to determine effec-
fiveness of Aqua Plaz (a Paintike coating) in reduc-
ing high frequency vibration levels at the equipment
shelf. Some reduction was experienced and use with
type-test and flight payloads will be considered. A
soft interstage joint which performed satisfactorily
in cartier tests also ts under consideration.

© Errors arising during the uncontrolled portion of
the trajectory have been reevaluated for the ABLE-5
configuration. To reduce this source of error to a
Practical minimum, if any changes are made to the
Payload following the Preacceptance test balance
Operation, it is planned to rebalance the payload
Prior to launch,

e The sequence of payload release from the third
stage was reevaluated resulting in the recommenda-
fion thet payload separation be accomplished as
close to third stage bumout as possible, The present
filght sequence has been modified and payload
Separation is programmed to occur fifteen seconds
atter third stage burnout. A zero “g" experiment to
observe the motion of the third stage and connected
Payload after third stage burnout is being consid-
ered. This test, if conducted would Provide additional
confidence that the selected Payload separation
time is suitable.



PARAMaTER PROGRAMMED == ACTUAL
Apoges 262 N. ML 280 N. Mi,
Perigee 262 N. Mi, 254M. Ml.
Perted 94.1 Min, 94.44 Min,
inclination Angle 32.64° 33.04°
Eccentricity 0.0003 0.0025 -
Injection Velocity 25,023 fps 25,052 fps
Sotellite Life 40 months
Active {battery} Lite 28 dey

TABLE 2, ORBITAL PARAMETERS

© Real-time display at Vandenberg Air Force Base
during the first pass indicated satisfactory operation
of the Aerojet-General payload. The data recordings
of the first two passes, which total approximately
thirty minutes of readout time, indicate o consider-
able amount of infrared background data. This data,
unavailable until this flight, on the various levels of
natural infrared radiation background will be most
beneficial to the design of later vehicles which must
identify rocket exhaust temperatures. Payload data
recordings have been received from subsequent
vehicle passes, are being reduced, and will be ana-
lyzed. These results will be reported in next month's
report.

Technical Progress

Second Stage Vehicle

@ Fabrication of the AGENA “'B" vehicle for the
third MIDAS flight is behind schedule for a December
1960 launch date. Present work schedules indicate
@ February 1961 launch for MIDAS Ill. A review is
being conducted to determine if an eariler launch
date is possible.

Infrared Scanner Units

Infrared scanner units for flights 3, 4, and 5 ore
being manufactured by Baird-Atomic, Inc.

@ = The prototype Baird-Atomic infrared scanner (a
flight retrofitable unit) is undergoing the shock and
vibration tests portion of the acceptance test cycle
at Avco. Delivery of this unit to LMSD is expected to
be delayed until mid-July.

@ Aircraft radiometer design modifications to pro-
vide more general information on background radi-
ation continued at Boird-Atomic.

Figure 6, Second MIDAS flight s01t vebicle following « suc-
cessful Launch from Aslentic Missile Range Stand 14.

WDLPM-4 212

+


Time

(sec) Stage Event
x+o0 | Lioff switch activates X +2300 il _Jettlson nose faking

Programmer starts Times varyin Il ‘Stop pitch Progrom

Gyres uncaged ‘accord, with Pitch command

 Umbilicals eject trajectory. Yaw command

‘Arm destruct initiator X— 49.0 Il _ Stop pitch progrom
X42 | Roll program initioted X-415 il __Engine cut-off signal
X+9 | Roll program complete Switch pneumatic coast control
x+10 1 Pitch program initiated System on pitch, yaw and roll

Wat ep pitch vate As egured X= 410 _ Tunolf hydraulic power
X+25 | 2nd step pitch rate for trajectory X~ #00 Initiate coast phase pitch program
X+70 | “3rd step pitch rate and detoiled in X~ 10368 _II_Stop coast phase pitch program
xX+90 | “th step pitch rate DTO X— 1458.6 {1 Start hydraulic power

Tatopilt gain change X— 1488.6 ll Engine restart fire signal

Programmer armed Uncoge accelerometer

x4 190 | Pitch program complete X— 14916 {t Cage coast pneumatic contro! system
x+ 182 1 _ Main engine cut-olf (MECO) X= 15001 _Aew TPS cutoff probe (back

Circvitry armed Arm oxidizer probe (back-up)
X+1@5 1 MECO backup onmed Arm spin and separation mechonism
ta @a MEO X—15040 ll Engine cut-off signal
X+1670 ll Start programmer Uncage coast preumatic control system
X+1700 il Engine fire signal Stert spin table

Uncage tires chanbor ‘Start timer on spin table

in pitch and yaw X= 15060 ll __Engine cut-off (backup)

Uncage high thrust roll jets Start spin table (back-up)

Uneage gyros X — 1507.0 Il Remove spin table bolt power
X+ 17085 Hf Blow separation bolts X— 15260 Il__Blow separation bolts
X+1760 Il Start pitch program Activate separation actuators

Sequence of Events—TRANSIT 18, 2A and 28

Payload separation occurs

ee

F4

‘WDLPM-4 212



MIDAS Launch Schedule

Monthly Progress—MIDAS Program

Flight Test Progress

© The second MIDAS flight test vehicle was
launched from Pad 14, Atlantic Missile Range, at
1036 hours, PST, on 24 May. The countdown pro-
ceeded smoothly except for minor holds. Perform-
ance with respect to Programmed orbital parameters
was outstanding. Acquisition was Gccomplished by
every station, ©

© The high’ degree of success achieved in the
launch phase is demonstrated by the comparison of

ee

Programmed actual figures for ascent and orbital
Parameters given in Tables 1 and 2.

PARAMETIR PROGRAMMED = ACTUAL
Booster Cutoff 148.8 146.8
Sustainer Cutoft 238.9 238.5
Vernier Cutott 256.7 257.6
AGENA Ignition 551.6 551.1
AGENA Cutoff 661.1 660.0

TABLE 1. ASCENT PARAMETERS
(Times shown are in seconds)



Step one includes twenty manned flights with the Fecovery ships will be provided fo supply additional
glider being dropped from a 8-52, five unmanned Support for the AMR launches. Landing facilities will
launches, and eleven manned launches from the be provided: at Fortaleza, Brazil; Santa lucia, Wind.
Atlantic Missiie Range (AMR). The first unmanned ward Islands; and Mayaguana, Bahama islands.

launch is scheduled for September 1963 with one Steps one and two of the DYNA SOAR program
ond one-half month span between launches. The” are to be conducted by the USAF and NASA partic-
manned flights are Programmed to start in mid-1964 Ipation, USAF will provide the over-all program
with a two-month span between launches. management and technical direction, with WADD

having responsibility for over-all system manage-
The range from Wendover AFB, Utah, to Edwards ment. AFBMD is responsible for the booster, booster
AFB is adequate instrumented for the tracking and subsystems, ground support equipment and booster
telemetry required during the air launched tests of requirements of the launch complex. WADD will have
the DYNA SOAR glider. Instrumentation sites for the responsibility for glider and subsystem development.
AMR launches will be located at Cape Canaveral, NASA will provide technical support in the design
San Salvador, Mayaguana, Antigua, Santa Lucia, and operation of the Glider in obtaining basic Gero-
and Fortaleza. Instrumentation, tracking, and nautical and space design information.

CAPE CANAVERAL
od

BRAZIL

FORTALEZA

Leer 2, DYNA SOAR tracking suations and lending sites for
lentches from the AGA, tacking Range. a ser |



THOR a sw7s  Mlpm21 ATLAS @....

F
1
Weight—dry 7,746 6,510 | Weight—wet 15,100 9
Fuel 30,500 33,695 Fuel 74,900 ii
Oxidizer 68,300 68,190 Onxidizer 172300 i
TOTAL WEIGHT 106,546 108,395 | TOTAL WEIGHT 262,300
Thrust-tbs,, S.L, 152,000 167,000 | Thrustibs,, S.L. s
Spec. Imp.sec, 246.42 248.3 Boost 356,000 fig
Burn Time—sec, © 163.59 148.0 Sustainer 82,100 A
Spec. Imp.-sec. G
Boost 26
Sustoiner 310
NOTES AGENA Da tages s
E
© Payload weighs not included. Engine Model MiRsi-Bo-S | XUR8I-Bo-7® | 1881-80-90 JM
Does i guid.
ance, APU and residual pro- | OWeight—inert 1,155 1,370 1,400 °
pellants, Impulse propellants 6,550 13,100 13,100 N
@® Docs not include THOR Pyrotechnics 7 108 108 d
adapter (225 (225 ts). or ATLAS TOTAL WEIGHT 7772 14,578 14,608 s
rf) .
Separation Weight 7,746 14,552 14,582 T
@ Single restart capability. A
Dual bur Thrust-ibs., vac. 15,500 15,500 16,000 ¢
® TM operation, Spec. Imp.-sec., vae. 7 27, 290
© Allegany Ballistic Laboratory. Burn Tima—sec. 120 2408 2400 E
ar ‘Asi0-104
AEROJET-GEMERAL AY ¢/, EN %, Mac a “ABL 248
E
Weight—wet 1,247.1 79 1,297 c 59.5
Fuel 875.1 869.0 2,247 ° 455.5
Oxidizer 2,499.6 2,461.0 6,227 N (solid)
TOTAL WEIGHT 4,621.8 41779 27 iad 515
Burnout Weight 1,308.6 944.1 1419 ; 50.5
Thrustbs., vac, 7,670 7,720 7,900 3 3,100
Spec. Imp.-see., vac 267 267 278 E 250.5
p Vehicle Combinations

DISCOVERER (1 thry 16}......A-D MIDAS (1 and 2).............0-D
DISCOVERER (16 thry 21). . vee CF
DISCOVERER (21 thru 29).



US.SR.

Figure 5,
The saisial visual rec

WDLPM4 212

‘Omnaisteuce program will use con-

stations thru a data link. Grownd electronics will recon-
vers she signal into photo image form, with « capability

Figure 3.
Se ic of SAMOS system
in operational orbit, When the

ite is over the area of
interest the sensin i
ete, ee

. # leaves

the paige) interest the sens-

of resolving objects 20 feat im length.



~ CONFIDENTIAL

Project MERCURY represents ihe transitional threshold viding 14 ATLAS boosters modified in accordance
this nation’s cumulative Gchievements in space with program objectives and pilot safety factors, and
fesearch and the beginning of actual space travel by (b) determination of trajectories and the launching
man. The primary program objective is to place a and contro! of vehicles through injection into orbit.
manned satellite into orbit about the earth, and to The division of tesponsibilities for this Program is given
effect a controlled re-entry and successful recovery In Table 1. Specific details of AFBMD support are given
of the man and Sapsule (Figure 1). Unmanned ICBM in Table 2,
trajectory ond near-orbital flights, and unmanned : .
orbiting flights will be used to verify the effectiveness Major contractors Participating in the AFBMD. Portion
nd reliability of an extensive research program Prior of this program include: Space Technology Labora-
fo manned orbital flights (Figure 2). The program will tories, systems engineering and technical direction;
be conducted over a Period of nearly two years, The Convair-Astronauties, modified ATLAS boosters; a
initiol R&D flight test was Accomplished successfully GE/Burroughs, ATLAS guidance equipment; and Rock-
in September 1959. The total Program accomplish- etdyne, engines. All of these companies also provide
ment is under the direction of NASA. The primary special studies and engineering efforts peculiar to
responsibility of AFBMD to date Consists of: (a) pro- Meeting Project MERCURY requirements,

LEGEND
RESPONSIBILITY:
AFBMD me
NASA

I
ESCAPE 1 v
ROCKET . | /
1 / -
WH CAPSULE i /
i / @)BALLIstic TRAJECTORY
BACLISTIC_TRAVJECTORY
ATLAS / J TO SIMULATE REENTRY CONDITIONS
U vA
BOOSTER } if NEAR ORBITAL WSERTION, MMEDIATE
/ / REORIENTATION, DECELERATION, REENTRY
i ATLANTIC RECOVERY

FULL ORBIT 3-18 ORBITS 105-115 N.M.
© WEST COAST REENTRY ATLANTIC RECOVERY

Figure 2. Hisghs tose srajectories for Project MERCURY, defaing specific objectives, Trajectory C
tidal ropes pcos Sete) Hab The pis ube ATOM wed ae ea,

is

a “CONFIDENTIAL WDLPM4 212


Of the Aerojet-General SENIOR motor for the 1-2-3-4
configuration has been scheduled at Edwards Air

@ The first launch of an unguided, 2-3-5-6 con-

are provided. Aeronutronic will furnish the dispersion
data by 10 June ond trajectory data by 17 June.
Vehicle components and Ground support equipment
for this fight are arriving at AMR on schedule.

@ Additional development testing of 609A rocket
motors has been conducted. A successful test was
completed at Amold Engineering Development Cen-
fer (AEDC) on an ABL-X254 to verify corrective
action taken to solve nozzle blistering problems, A

test is scheduled for 10 June at AEDC on a unit com-
Posed’ of an ABL-X254 motor, section "C"" airframe,
and peroxide contro! system. This test will provide
information on peroxide contro! system operation in
@ low density tmosphere and vibration information
about the motor.

@ An Aerojet-General SENIOR motor was success-
fully fired after completing an aging and cycling test
at Sacramento,

Facilities

@ The Architect-Engineer Evaluation Board has
selected a contractor to design additional facilities
at AMR for the 609A Program. The de-
sign is scheduled for 31 August completion, with the
construction contract to be issued on 1 October.
Beneficial occupancy date for the first assembly
building is 1 February 1961,

WDLPM-4 212



—CONFIDENTIAL

Flight tests of the three ABLE-1 vehicles in 1958 con-
firmed the feasibility of using this three stage vehicle
fo launch satellite Payloads on interplaneary space
Probe missions. Objectives of the ABLE program
Were further defined in AFBMD Proposals submitted
to NASA and ARPA late in 1958. In October 1958
NASA, given cognizance over the effort, requested
AFBMD to proceed with the ABLE-3 and two ABLE
Projects. In February 1960 NASA authorized the
two-flight ABLE-5 (ATLAS Program. The
lunar satellites will be launched late in 1960. Gen-
eral objectives included demonstration of vehicle and
communications capability and performance of scien-
tific research experiments over interplanetary dis-
tances. A four stage vehicle wos selected consisting
of a THOR or ATLAS first stage, an ABLE second
stage, ABL 248 solid Propellant third stage and the
satellite vehicle fourth stage. A hydrazine engine
with multi-start capability was developed for the
ATLAS boosted vehicles to permit midcourse vernier
control and to provide controlled thrust to inject the
vehicle into orbit about another planet. Solar cell
auxiliary power equipment was developed with a
useful life period in excess of one year. An extensive
network of ground support stations was established,
the most powerful of which Is the 250-foot antenria
at the Jodrell Bank Experimental Station, University
of Manchester, England. Central control and data
computation is accomplished at the Space Naviga-

fion Center, Los Angeles, California, with other mili-
tary and NASA centers assisting In tracking and
telemetry according to the ‘specific requirements of
‘each mission. The flight histories of ABLE-1, ABLE-3,
ABLE-4 ATLAS and ABLE-4 THOR are summarized in

‘the following Paragraphs, followed by a description

of the ABLE-5 projects,

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 AJIO-101A rocket engine, a third
stage powered by the ABL-248 A3 engine, and a
fourth stage consisting of the payloed and an injec-
tion rocket. In addition to careying @ highly sophisti-
cated payload, the ABLE-3 flight was used to
demonstrate the validity of the ABLE-4 vehicle and
component configurations. All Phases of the launch-
ing were successful and the advanced scientific
observatory satellite was Placed in an extremely
elliptical geocentric orbit about the earth. Trajectory
and orbit were essentially as predicted with devia-
tions in apogee and Perigee occurring on the more
than nominal side. The Payload was the most sophis-
ficated to have been placed in orbit by this nation
at the time and contained Provisions for conducting
13 experimenis in space environment.and Propaga-
ton. A wealth of valuable data was obtained from



transmit crude television Images of the far side of
the moon. This was the first flight in which an ATLAS
ICBM was used as the booster for a mulfi-tage
space flight.

ABLE-4 THOR vehicle was lounched on 11 March
from the Atlantic Missile Range and succeeded in
Placing the PIONEER V satelite into a solar orbit.
At its closest approach to the sun, the satellite wil
Pass near the orbit of Venus, and return fo intersect
the orbit of earth at its grectest distance from the
sun. The vehicle consisted of a THOR first stage,
ABLE second stage with AJ10-101 liquid fueled pro-
pulsion system and an STL guidance system, and an
ABL248A-3, solid fuel third stage. The 95 pound
Payload contains instrumentation for conducting

Fi . AT ic is rboto
ee iy sn a a

- satellite telemetry until the last transmission was
teceived on 6 October. it is betieved.that the satel-
lite, while yet in orbit, is incapable of
sufficint power for transmitting signals due to solar
Paddle damage suffered during initial paddle exten-
sion and the resultant unfavorable sun “look” angle.

ABLE~4 ATLAS— This vehicle differed from the 4
ABLE-3 only in that on ATLAS ICBM was used as the
first stage instead of a THOR IRBM. The unsuccessful
Jaunch of the ABLE-4 ATLAS Occurred on 26 Novem-
ber 1959. Structural breakup resulted in the third
stage and payload Parting from the vehicle approx.
—_ imately 48 seconds after launch. The ATLAS per-
formed as planned over its entire powered flight
trajectory. The trajectory of this flight, from ‘the
Atlantic Missile Range to the vicinity of the moon,
was established to achieve the tightest possible cir-
cular lunar. orbit consistent with the highest proba-
bility of success. The final burnout conditions were
- to have provided an inertial velocity of 34,552 feet

Per second. The payload wes designed to investigate Figure 4. PIONBER V satellite ve
space environment and Propagation effects and to pat ee

WOLPM.4 212 “CONFIDENTIAL Bs

thicle shown in orbit ighs
soler satellite was ‘lanached from Ane 71




I
i
i
i
!
i

cenit

ENTER ELLIPTICAL ORBIT
PERIGEE OF

COAST ELLIPSE “
¢
AGENA \ Ye
1ST. BURN.
\ 150 N, Mi,

SEPARATION @
‘J wm T COAST
| a,

BOOST:
Figure 2, attitude reference. Also governs velocity magnitude and
Leeach-so-orbis srajectory for flights 3 and subse direction by inertial guidance system monitored by horizon

. Opti- sys
mum ATLAS boost, guided by tadio-inertiat system. Scanner. Orbital attitude maintained by reaction wheel and
AGENA ascent (coast, arm, coast, second burn) provides

Figure 3.

Proposed MIDAS system. Four satellises spaced equidistons in each of
1a gon ln 200 nm. altitude. Provides maximum cov-
erage 0} i

PROGRAM HISTORY

The MIDAS Progrom was included in Weapon
System 1171 when WS 1171 was transferred
to 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. An
ARDC development plan for a ten flight R&D
Program has been approved. This R&D pro-
gram. should make possible the achievement
of an operational system by 1963,

c2

ISSR with minimum number of — y



ROLL JETS

ESCAPE ROCKET

~ ESCAPE ROCKET.

“WEIGHT AT SEPARAT
ORBITAL. ALTITUDE
ORBITAL CYCLES

ENTRANCE HATCH

HORIZON SCANNER
PITCH & YAW JETS

Q
ae 6 -
nOCKE? I

RETROGRADE:

ION APPROX. 2500 LBS

ORBIT INCLINATION 33 DEGREES
ses MILES (n)
3-1

HEAT SHIELD ABLATIVE
RECOVERY WATER OR LAND

(bem ee) ease ee ab ite) with slits salad op ATLAS booze, Manned ssi
(bottom view) caper et Miah poston, and dea inet of rire mad ponies etter cenit
safety systems escape rockets,

WDLPM-4 212

—€ONFIDENTIAL

ADE

Fl

———__


DYNA SOAR

The DYNA SOAR Program will explore the possibili-
ties of manned flight in the hypersonic and orbital
realms. The program will Proceed in three major
steps from a research and test Phase to an opera-
tional military system. In step one, a full scale, mini-
mum sized manned glider will be developed. A
modified version of the TITAN ICBM will boost the
lider into hypersonic flight at velocities up to 22,000
ft/sec. In step two the glider will be tested, using a
more powerful booster to achieve orbital velocities.
This phase may be expanded into an interim opera-
tional weapon system Providing all-weather recon-

7

naissance and satellite interceptor capabilities. The
objectives of step two are to test vehicle performance
between 22,000 ft/sec and orbital velocities; and
fo gather re-entry data from various orbits. Step
three will provide an operational weapon system
with a vehicle that will operate primarily in a hyper-
sonic glide, be able to maneuver within the atmos-
Phere, and be able to make a conventional landing
ata Predetermined site. The capability of DYNA
SOAR type systems to perform these programmed
missions appears attractive os @ result of studies
made to date.

eee “7
A 34's"
A. GLIDER 39"
Weight 9,500 toe.
Wing Area 3205g. fH,
5. TITAN SECOND stage
Threst (bs, vac.) 90,000
Initial Weight 45,700.
Bernout Weight 4A
* Be man mast stage tau
Thrust (ibs, sea level) 300,000 u53
Initial Weight 117,800
Burnout Weight 9.251
(<_ e [ay
FIRST STAGE MODIFICATIONS
© Stabilizing Fins Added
© Skirt Section and intertonk
Section Modified ond Strengthened

c SECOND STAGE MODIFICATIONS

© Ignition Prior to Separation
© Propellant Tonks Capacity Increosed
© Intertonk Section Strengthened 6q'4"

Figure 1. DYNA SOAR ticle as atio:
| rowing nd ipciicaion Tents onbteration
—__L

SECRET u



spuug UENTIAL
Program BOOSTERS

Planning time schedules for the accomplishment of Space Program
missions is based largely, at present, on the of booster

vehicles. IRBM, ICBM, and upper stage development programs must
be closely monitored, As ore i

|. As modifications into these
Programs: reducing weight, increasing thrust, lengthening burning
Periods, using improved fuels; in short, any change which
overall the use of the vehicle must te re-evaluated in

ber of experiments within @ given Poyload becomes very complex.
Among other factors, solving this problem involves the selection of
the most effective booster combination, the maximum use of booster

and the maximum use of existing ground tracking and
support facilities and equipment.

Because of its signal success in Providing the nation with an opera-
fional THOR IRBM and ATLAS ICBM within an

Period of time, as well as for its advanced work in TITAN tnd
MINUTEMAN programs, AFBMD Possesses a distinct advantage in
eroluating booster capability in terms of specitic space payloads
or missions, The following pages ore devoted to a brief presenta-
fion of the various boosters currently being used fo support NASA .
and Department 8



rh { UPPER PAYLOAD *
8 \ PAYLOAD
4 A. SECOND sTAGs—anuL-staR {AJ10-104) TT} (36-INCH DIAMETER)
Thr oltitude 9030 as
h Sent impohe (vor) mm pees se PAYLOAD
Totol impelse (min) 2.3 X 10° tha/sec rok SEPERATION PLANE
Borning time 294 seconds aH
Propeliant ‘PAYLOAD
| 8 _ mon _ 222s SPIN MECHANISM
met ea ee pounds EQUIPMENT
‘Specific impulse (s. 1.) 248 seconds aa + ~ COMPARTMENT
' oe Heitdited in seconde | PROPULSION SYSTEM
Propeliont Uquid To ‘54.79 DIAMETER
A Ady GIMBAL &
4 =
hstase 1
ay SEPARATION PL ANE
‘ =aee STAGE I/I ADAPTER
H bit ‘STAGE I
t GUIDANCE COMPARTMENT
H TRANSIT 18, 2A and 28

A % 20 INCH DIAMETER
TRANSIT 24 & 2B ONLY

4

Powered Flight Trajectory The ‘Powered flight
Program Objectives trajectory for TRANSITS 18, 2A and 28 is shown and
|. Provide accurate navigational reference informa- described in Figure. The sequence of events
tion for POLARIS launches. from launch through payload separation for TRAN-

2. Precise determination of satellite position by SIT 18 Is given in Table 1.
measuring the doppler shift of satellite transmitted Payload Description ‘The spherical payloads are
radio signals, approximately 36 inches in diameter and weigh
3. Investigate the refractive effect of the lonosphere between 200 and 270 pounds. Payload equipment
on radio transmissions. ineades on transmitters (on kervences of 54, 108,
162 and 2: 6 megacycles), two rec 1, and a gate
one precon Mackey of en seomreptia which permits the insertion of data only when the
. ° Gate has been opened at a previously scheduled
Tight Vehicles TRANSIT 14 consisted of three time. Power for the first five months will be supplied
stages as shown in Figure + TRANSIT 1B, 24 by batteries, recharged by solar cells located in a
ond 28 ore two-sige vehicles ax shown in Figure 12-inch band around the sphere. The TRANSIT 1B
Launch Plans All vehicles will be launched from Payload will also contain an infrared scanner which
Atlantic Missile Range pad 17A or 178, Lounch will operate for the first four days of orbit. On TRAN-
azimuth for TRANSITS 14 and 1B is 44.5 degrees SITS 2A and 28 a 20-inch sphere, mounted on top
and for TRANSITS 24 and 2B, 140 degrees. of the 36-inch sphere, will contain instrumentation
for studying solar emissions. The payloads will be

spi

bilized In orbit,
F2



Ground Support Equipment

© The ground station
essentially the some

Punches and improvem
digital telemetry.

@ The design of Test Van No. 4 is Opproximately © Two sets of guidance
90-percent complete. The chassis and body of the during the month, except
van have been delivered, The electrical equipment covering the ATLAS sus
racks are currently being installed. The design of ‘constants selected by the end of June.
ABLE-5 power contro! ‘ond monitor equipment for the set of guidance equations coverin,
van subsystem panels is approximately 90-percent will have all constants selected by

“CONFIDENTIAL

equipment for ABLE-5 remains ment is in progress. Ch

ent of threshold Sensitivity for
‘Guidance Equations

complete. Modifications to

existing ABLE-4 equip-
eckout has started on Primary
units consisting of Jaunch control panel, relay drawer
ot AME except for replace ‘and van distribution rack.
Punches with more reliable

equations were completed
for constants. The first set
tainer phase will have all
The second
9 the ABLE stage
the end of July.

WDLPM-4 212


S3IGNLS 3Dvas


" ae " . 7
: Facility Equipment Flight Function

Satellite A cad un nme ee se snap
Test Center and generale subsequent ides issue acquisition to trocki
stotions for subsequent asses, predict recovery area,
Vandenberg AFB SCDEFGHUK Lounch, ascent and orbital tracking, telemetry reception, trajectory meas-
' urements including time to ignite ‘second Sage.
. Point Mugu BCDEFGHIJKL Ascent tracking ond telemetry data reception, transmits command to
ignite ond shut down AGENA ivia guidance computer).
Telemetry Ship OF Final stage oscent tracking and telemetry data reception.
(Pvt. Joe E, Mann)
s. Annette islond, Adiivity at this station terminated 1 December 1959 due to fund limitations,
Alaska Itrocking
station)
Cape Chiniak, BOEFGHUK. Orbital tracking and telemetry data reception, including first poss acquisi:
Aleska ing : tion, recovery capsule jection ond impact prediction.
= station)
Kaena Point, BCOEFGHIK Orbital tracking ond telemetry dato reception,
Ochv, i
(tracking station)
Hickam AFB Over-ail direction of copsule recovery operations,

he Plot boords for radar and TUM-18 tracking dote
. b. VERLORT (Modified Mod iN} redor i
“6 . ¢. TLM-I8 selt-trocking telemetering antenna
d. Trishelix ontenao
*. Doppler range detection equipment
4. Telemetry tape secording equipment
9 Telemetry decommutotors for real ime doto presentotion

GROUND SUPPORT FACILITIES

ar

WDLPM44 212



CONFIDENTIAL

WDLPM-4 212

; THIRD STAOL—X-248 (Allegany Balllatic Lob.)

H Thrust at attitude 3150 pounds
Specific impulve (vac) 250 seconds
Toto! impvise 116,400 Iba/see
Berning Time 37-5 seconds
Propetiont Solid
SECOND STAGE—As10-42 (Aarojet-Generel)
Thewst at altitude 7700 pownds
Specific impule (voc) 271 second
Total impulse (min) 870,000 the/s0e
Burning time 115 seconds
Propeticat Liquid
FIRST StAGE—THOR InBM
Thevst (2.1) 151,500 pounds
Specific impule (1.1) 248 seconds
Specific impule (voc) 287 seconds
Burning thwe 158 seconds
Propellant Liquid

fay)

difficulties encountered with the C-band beacon.
During the hold, three LOX topping valves became
inoperative. These problems were resolved and the
countdown was recycled to T-15 minutes. The launch
Proceeded smoothly to liftoff which occurred at
0640:09.021,

Hight Vehicle

@ The first stage was o modified THOR intermedi-
ate range ballistic missile with the inertial guidance
system removed. The second stage utilized an
Aerojet-General (AJ10-42) Propulsion system and a
Bell Telephone Laboratories guidance system which
was also used for guidance during first stage flight.
An Allegany Ballistics Laboratory X-248 solid Pro-
Pellant engine was used for the third stage.

Payload

@ The 270 Pound, cylindrical payload is 42 inches
in diameter and 17 inches high. Payload equipment
includes two television cameras designed to observe,
Fecord and transmit weather data, Power sources
include sixty 20-volt nickel-cadmium chemical bat-
teries and 9,260 solar cells to recharge the batteries,
The solar celts, installed in the top and cylindrical

side walls of the satellite will furnish an average
output of 13 watts for the first 140 days of satellite
life, Two beacon transmitters Gre installed in the
satellite to facilitate tracking.

Operation

©@ Once during each orbit the satellite is interro-
gated and re-programmed from a ground station.
The Fort ‘Monmouth, New Jersey, and Kaena Point,
Hawaii stations are tracking, commanding and
receiving data from the TIROS Satellite, Use of the
Air Force facitity will benefit the SAMOS and MIDAS
Programs by attaining an early buildup of experi-
enced personnel,

@ The two television cameras have different reso-
lution capabilities and coverage pattems to permit
observation of a wide Variety of cloud patterns. Two
modes of TV system peration are possible. When
the satellite is within radio Communications range of
@ ground station, pictures may be taken on command
and transmitted directly to earth. When the satellite
is beyond the radio communication range, camera

- peration is controlled by a clock and Programming

circuits ond the images recorded on magnetic tape
for readout during the next Pass over a ground
station,

Accomplishments :
@ This fight has Proved the feasibility of using an
sarth satellite to provide information for more accu.
rate long-range weather forecasting. Information
received indicates the following successes have been
accomplished by this satellite,

1. High quality pictures taken by the wide angle
Camera are being réceived on both the direct
and delayed readout modes.

High quality Pictures taken by the narrow
angle camera have been received on the direct
and delayed readout modes. The delayed
feadout mode resumed ©peration on 2 May
Gtter failing to resporid since 2 April, the day
after launch. It is believed that a soldered
foint in the timing mechanism Opened at low
temperatures. “Soaking” in sunlight may have
dosed the joint and reestablished contact,

3. All tracking command, and dato readout trans-
milters are Operating satisfactorily.

4. The solar cell recharging rate is higher than
anticipated indicating that the payload will be

Operational throughout its Programmed useful
life of five months.

»

CONFIDENTIAL Bs

a



77 ABL X248 AG
M20, JETS

7 ABL X254 A2-
H202 JETS

— 30"

THIOKOL
SERGEANT
(IMPROVED)
XM33E5
(ALT. NOZZLE)
Hy Oo, JETS

— 3"

SENIOR

33KS 120,000
JET VANES AND
AERO FINS

I-2-3-4

CONFIGURATION

WDLPM-4 212

NOTS aa:
Aulo-41

(OKS-8000)-—

xe54-Al—~

mau

——
PROJECT 609A
——$—
Hyper-Environment Test System

tzed vehicle to permit the economical performance
Of flight test experiments in Support of scientific
research and advanced nilitary space system
Programs,

Economy—Reliability—Versatility — in this order
of emphasis are the three significant guides:to pro-
gram eccomplishment. ECONOMY is being achieved

{oa

/

y

demonstrate the mission-
versatility of the brogram.

1-2-3" CONFIGURATION EN...

CONFIDENTIAL Kl



This program is designed to gather information from
which correctives will be made fo assure maximum

Probability of recovery on subsequent DISCOVERER
flights,

© Telemetry dota on the DISCOVERER xi flight indi-
cate that the recovery capsule was ejected on the
17th orbit as planned. A good track of the copeule
telemetry transmitter was obtained by the Kaena
Point station which showed that the predicted re-entry
trajectory did not occur. Capsule separation and
Fetro-rocket firing were verified. However, spin rocket
firing was not verified. Data evaluation indicated
that resultant velocity magnitude and direction were
incorrect and, asa result, recovery wos not effected,

e As part of the diagnostic program a more com-
plete “blossom telemetry Package is being installed
to monitor the DISCOVERER XII Payload

sequence. This package will Provide information on
all phases of capsule election including retro, spin,

‘and de-spin rocket separation and parachute deploy.
ment,

“@ An intensive Fecovery system test program is
being conducted at two sites:

L Sante Cruz Test Base— Spin rocket firings have
been checked in a series of capsule drop tects.
While the test capsule was in free fall from a
tower, various firing combinations of spin rock-
ott were cttempted and the effects on the cop-
sule recorded.

2. Holloman Air Force Base—Functional phases
Of the recovery System (including rocket firings
and parachute deployment) are being tested in *
@ series of balloon drop tests,

© DISCOVERER Xx! was the first orbiting AGENA to
Carry the dual-frequency doppler beacon (APL) and
four optical tracking tights, Satisfactory tracking of
both systems was achieved t stations in the United
. States and abroed. Sufficient data were received to

Figure 1, Spin rocket Brings at Saute Crm Test Base. Cap.
sale is dropped from tower fapper photo), serious combi.
nations of shia rockets are fired, and the results are recorded.
Capsule is caught in the wet ow the lower left. Spin rockets
being replaced (lower) after capsule drop test,

AS



t

@ foreword fo...

FOREWORD


Figure 1. ABLE-3 flight sess vebicle being lawnched from Atlantic.
(ets) of four-stage ABLE-3 vehicle.



June. Installation of the Pad 2 launch monitoring con-
trol system and ground handling and service equip-
ment is in progress.

@ New Beston, New Hampshire, Tracking ond
Data Acquisition Station— Design of support facili-

ties for the station has been completed and the
Project is being advertised for bid. Completion of
the support focifiies is scheduled for December,
with the exception of the radome structure for the
UHF antenna receiver No. 2, which is scheduled for
completion in August 1961,

Figure 8. Mockap of the ATLAS booster being mated to the lexnchey at Pad 1.

B7



WDLPM-4 30 May 1960

FOREWORD

Programs must be sufficiently flexible to Permit continuous and effective
integration of rapidly occurring advances in the state-of-the-art.

This month's report includes information on the highly successful MIDAS II
launch on 24 May. Performance with regard to planned orbital Poram-
eters was outstanding. This flight is a significant milestone in the MIDAS.
Program.

The successful TIROS launch on 1 April marked the end of AFBMD‘s
Perticipation in this program. This report reviews the program ond the
launch and concludes the reporting on this program.



‘WDLPM-4 212

“CONFIDENTIAL

Monthly Progress—TRANSIT Program
Flight Test Progress

TRANSIT 1B

@ Data reduction of a TRANSIT 1B experiment is
being accomplished and the results will be reported
in next month's report.

Technical Progress

TRANSIT 2A

© The Flight System Test (FST) was successfully
completed ot the Atlantic Missile Range during the
report period. The vehicle is currently sealed in a
nitrogen gas atmosphere for Protection. On 6 June
the vehicle will be removed from storage and the
guidance ond contro! subsystem tests and the FST
will be repeated. The following additional checks
and modifications will be accomplished in time to
insure meeting the 21 June launch date:

1. Leak checks

2. Weight and center of gravity determination
checks

3. Equipment compartment vent modifications

4. C-Band beacon battery modifications will per-
mit FPS-16 radar tracking from Vandenberg
Air Force Base and Holloman Air Development
Center.

5. Re-allocation of telemetry channels to provide
‘additional staging information,

@ = The ground guidance modification is Proceeding
on schedule. The first interconnection test between
the ground guidance system and the FPS-16 radar
Is scheduled for 10 June. Missile-ground guidance
compatibility checks are scheduled for 13 June.

TRANSIT 2B

© The project schedule has been revised to reflect
a hardware availability for launch date on 1 Novem-
ber. Aerojet-General Corporation and Space Elec-
tronics Corporation are working to meet this revised
schedule,

@ The AJ10-104 propulsion and force control sys-
tem was acceptance fired at Sacramento during the |
month. This unit Is scheduled for delivery to the Air
Force early in June.

TRANSIT 2A PAYLOAD...

The 20-inch upper sphere contains
instrumentation for studying solar
emissions. The solar calls and broad
band antennas {spiral stripes) can
be seen on the 36-inch sphere.

CONFIDENTIAL Fs



WDLPM-4 212

The Communications Satellite Program will investi-
gate the feasibility of using synchronously spaced
satellites as instantaneous repecters for radio com-
munications. Under ARPA Order No. 54, as
amended, AFBMD is responsible for the design,
development, and flight testing of the complete
system, including launch, satellite tracking and con-
trol, and necessary support facilities and ground
equipment. The Army Signal Research and Develop-
ment Laboratory has been delegated development
management responsibility for the microwave com-
munications subsystem as directed by ARPA Order
54, :

The Communications Satellite Program is currently
being conducted in accordance with amendment 5,
{dated 11 April 1960) to ARPA Order No. 54. Under
this amendment the previous method of ‘accomplish-
ing the program objectives in three Progressively

Figure 1. Proposed satellite with jattisonable

dairing mounted on AGENA second. stage.

Communications
Satellite

YETTISONABLE
NOSE FAIRING

}+-— PAYLOAD MAXIMUM
ENVELOPE

| SOLAR PADDLE

i AGENA STAGE

DI



“CONFIDENTIAL

Monthly Progress— ABLE Projects
ABLE-4 THOR (PIONEER V SATELLITE)

The PIONEER V satelite was placed into an elliptical
solar orbit on 11 March o8 soon as it escaped from
the earth's gravitational pull, On 25 May, the satel-
lite was 11,919,700 miles from earth and was travel.
ing at @ velocity (relative fo the earth) of 11,380

averaging 10 to 15 minutes Per period, at a rate of
1 pulse per second.

@ As of 25 May, PIONEER V has been in space
for 1810 hours. The 5-watt transmitter had been
Operated for a total of 123 hours and the 150-watt
transmitter for Gpproximately 15 minutes. The 150-
walt transmitter will be commanded “ON” when
reception at Manchester from the 5-wait transmitter
is no longer usable,

one minute in order to be certain that it was the
undervottage relay ‘peration and not a component
failure that stopped transmission. This brief tracking
exercise presages tracking conditions of the future
since the “OFF command was sent before the
Fesponse to the “ON” command was heard,

Solar Flare Activity

@ On 28 April, the Enrico Fermi Institute of the
University of Chicago alerted the SpaN Network to
the existence of ‘extroordinary solar flare activity in
outer space. The transmission schedule for PIONEER V

Be —CONFIDENTIAL

was oltered to permit this solar phenomena to be
examined in maximum detail. Since the satellite was
4 million miles closer to the sun than was the earth
ot that time, it is anticipated that much valvable
information will be obtained from telemetry during
this period.

ABLE-5
First Stage

e The tentative acceptance date for ATLAS 80D is
6 July. Although this date represents a three week
slippage in schedule, it is compatible with program
requirements. ATLAS 91D is in the initia! stages of
fabrication,

Second Stage

e Fabrication of the relay junction box type-test
unit and first Aight unit is. 75 and 50 percent com-
Plete, respectively. The first fight hamess ls 60

Third Stage

@ Ata meeting of representatives from

AFBMD/NASA and Space Technology Laboratories °

the over-all Performance of the ABL X248 was
reviewed. As a result of this mesting the specification
for the X248A-9 engine was revised to require that
the propellant charges be manufectured from a
single lot of casting powder and that tighter controls
be maintained on the Costing powder temperature
during the engine monufacturing process. Te further
assure reproducibility of the flight ‘engine, AFBMD
‘was requested to procure two additional engines for
quality assurance and Performance evaluation tests
at Arnold Engineering Development Center {AEDC),

©@ A list of procedures required for the ABLE-5
field operation has been Prepared ond published.

ork is progressing en the ovar-all systems test pro-
cedure for ABLE-5. included Gre the flight systems
test and the guidance-link loop test.

e The first control compartment has been deliv.
ered and is being assembled as a structural test unit.
Delivery is expected in one week.


gare 4,

titted’ by Soviet chats powered flight.
ta telemetered instantansons;

WDLPM-4 212

ection of travel and ing characteris.
‘ Map ee shows itty of at least
e i ee, et tect an ICBM
inch in eacl pgments

USSR Ther probes cement of

are based on

TECHNICAL HISTORY
The MIDAS infrared reconnaissance payload

is engineered to use a standard launch
vehicle configuration. This consists of a“D"
Series ATLAS missile as the first stage ond the
AGENA vehicle, bowered by « Bell Aircraft
rocket engine as the second, orbiting stage
(Figure 1). The totat payload weight is
Gpproximately 1,000 pounds,

The first two of the ten R&D flights used the
AGENA "A" vehicle programmed to ploce
the payload in a circular 261 nautical mile
orbit. Subsequent flights will lle the ATLAS/
AGENA “B" configuration which will be pro-
grammed to place the payload in a circulor
2,000 nautical mile polar orbit.



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 edditionol objective of this program is

Techniques have been developed for oerial recovery
by C-119 olrcraft and for sea recovery by Navy
surface vessels. The recovery phase of the program
has provided advances in Fe-entry vehicle technol-
Ogy. This information will be used in support of more
advanced projects, including the return of a manned
satellite from orbit,

FLIGHT VEHICLE

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

AGENA VEHICLE DEVELOPMENT

Ihe AGENA vehicle was originally designed by the
Air Force as the basic satellite vehicle for Advanced
Military Reconnaissance Satellite Systems Programs,
Basic design was based on use of the ATLAS ICBM
08 the first stage. ATLAS trajectory characteristics and
the stringent eccentricity requirements of the
advanced programs led 0 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

C)
YS
auriTupe AY
os DEGREE . waa PATH

ACA OR”

Las.
aK
{ SECTION

PLANE

Jum
SPHERES

'ULLAGE ROCKETS

‘SPHERE (UOMH)

Ges jet system for orbital attitude control. An urgent
need for attaining higher altitude orbits resuited in
development of the AGENA “B"” versions. The YLR81
Ba-5 version. of the LR81-Ba-3 engine (Bell Hustler
engine developed for 3-58 gircraft) is used on
AGENA “A” vehicles. The YLR@1-Ba-5 version of this
engine was developed to provide increased Perform.
ance through the use of unsymmetrical di-methyi
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 “8”
vehicles will use the XLR81-Ba-9 ‘engine incorporating
@ nozzle expansion ratic of 45:1, and Providing o
further increase in performance capability including
engine restart and extended burn capability,

OISCOVERER/AGENA

vw

, LINES OF SIGHT—HORIZON SENSING i
a wou



WDLPM-4 212

DEVELOPMENT PHASE

eee

Project 609A Launch Schedule

Monthly Progress—Project 609A
Program Admisistration

©@ The new 609A Development Plan was submitted
to Headquarters ARDC. Included is a revised devel-
opment and test program reoriented to adjust for
delays in NASA SCOUT development and permit the
Air Force to provide reliable vehicles in support of
the Navy TRANSIT Program on o timely basis. Also
indluded is a proposed follow-on Program providing
609A support of the ARDC applied research pro-
gram. Approximately thirty lounches are Program-
med for CY 61 at a cost of $19 million.

@ A new program plan, outlining a reoriented
development and test Program, in support of the new
Development Plan has been submitted by Aeronau-
fics. The new plan proposes two orbital launches
during December.

© Complete responsibility for the TRANSIT Pro-
gram has been transferred to the Navy by ARPA.
AFBMD is now providing THOR/ABLE-STAR vehicles
fo support the TRANSIT Program. Later, the size of
the satellite will be reduced and 609A/SCOUT
Vehicles will be provided for launch support.

© A request for $1,060,000 was submitted to
Headquarters ARDC for design and construction of
cdditional facilities at the Atlantic Missile Range to
support the follow-on ARDC operational Program,
Approval was received for expenditure of $60,000
for design of facilities with indications that the one
milfion dollars for construction would be made avail-
able later.

@ Because of increased hardware and systems
management costs, a request for additional FY 60
funds of $1,043,000 was made to Headquorters
ARDC. AFBMD was requested to determine the abso-
lute minimum amount required to support the devel-
opment and test program up to 1 July without
serious detriment to the program. Following NASA‘s
agreement to defer its requirement until July,
$223,000 was still required to fund the Aeronu-
tronic Contract through June. This minimum funding
for the 609A Project has been promised; however,
@ program funding deficiency of $1,043,000 still
exists,

© Purchase requests totaling $587,000 for rocket
motors, transtainers, and airframes to be procured
through the NASA has been initiated. Purchase re-
‘quests for $728,000 were initiated for procurement
of payload carrier and systems integration from
Aeronutronics.

Technical Progress

© The first full-scale guided SCOUT launch by
NASA is scheduled for 18 June. An apparent solu-
fion of the hydrogen-peroxide second stage control
system problems permitied the launch date to be
moved up one week.

© Successful rocket motor destruct tests have been
conducted using XM-33 and ABL-X254 motors for
the 2-3-5-6 configuration vehicle. These tests were
performed to meet Range Safety requirements at the
Atlantic Missile Range. A linear charge: destruct test

CONFIDENTIAL Ks



“CONFIDENTIAL

The ARPA COURIER Program consists of two flight
vehicles to be launched from the Allontic Missile
Range. The program objective is to fest delayed
fepeater 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 (A}10-104) second stage
vehicle. The program Is being conducted under ARPA
Order No. 98, dated } duly 1959 (Project Code No.
2200}. AFBMD responsibility includes development
of the launch vehicle, Payload integration, launch,
injection of payload into orbit, and verification of
orbital perometers at injection. The Army Signal
Research and Development Laboratory wilt design,
develop and fabricate the Payload, and will be re-
sponsible for world-wide ground station requirements.
Primary payload contractor is Phiico Corporation,
Vehicle Description—The two-stage COURIER vehicle
Consists of a THOR booster, an ABLE-STAR (AJ10-104)
second stage and a 500 pound COURIER payload.
Booster flight control is exercised by @ gyro platform
and a programmer. The second stage is controlled by
© gyro uted to govern engine gimballing during Pow-
ered flight, Stobility during second stage coast is
Provided by the “on-off” operation of jet nozzles
operating from a dry nitrogen supply. The second
stage propellants are inhibited red fuming nitire acid
and unsymmetrical dimethyl hydrazine. The engine
will have a restart copabitity. The 500 pound COURIER
Payload is a 60-inch sphere, containing radio repect-
rs, storage ond memory equipment, and a battery
Power source, .
Flight Description—Both vehicles are to be launched
from the Atlantic Missile Range. After first stage burn-
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 nav-
fical mile orbital altitude and the ABLE-STAR engine
reignited to attain orbital velocity. The orbital ‘angle
of 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,
to each of thres ground stations; as well as e:
ing “real time” information when the satellite is within
line-of-sight of two ground stations. During these peri-
ods a ground station can relay messages direct to the
next ground station, through the satellite simplex
repeoter equipment.
Ground Support Stations—These stations will be
located at Camp Selinas, Puerto Rico; Terrejon Air
Force Base, Madrid, Spain; and Halemano, Hawai,
Station design and development is under contract to
‘International Telephone and Telegraph Corporation,

79.3!

[ [¢ [o [a]

[9]:

|

[

stconp STAQE—ABLE-STAR {A310-104)

Thrust ot altitude 9030 posnds
Specitic Impetse (vee) 278 seconds
Tote! imputse {min} 2.3 X 10" tbs /r0c
Burning time 294 seconds
Propetiant quid

FIRST STAOE—THOR am

Thever (3.1) 151,500 pounds

‘Specific impulse fs. 1) 248 seconds
Specific impulse (vos) 287 seconds
Serning time 158 seconds
Propelieat Uquid

WDLPM4 212 —CONFIDENTIAL a



= a ee te =

= - a ae a ee oe ‘ep

~ CONFIDENTIAL

Tir

Program Administration.

e With the successful launch and orbit of the
TIROS: payload on 1 April, AFBMD's responsibility
in the program ended. The National ‘Aeronautic
and Space Administration was the Primary program

* agency. AFBMD was responsible for the launch

vehicle, integrating the. payload to the launch vehicle,
and providing communications to the tracking and
data-handling agencies from launch through attain-
ment of orbit, Payload design, fabrication and test-
ing were accomplished by the Radio Corporation of
America for NASA, NASA retained cognizance for
operating, tracking, and recording and Processing
of satellite data.

Flight Test Progress

© The TIROS satellite was launched from stand
17A, Alfantic Missile Range, at 0640:09 EST, on
1 April. The three stage THOR-boosted flight vehicle

os

Placed the TIROS payload into the most perfect
tricular orbit achieved by this nation up to that time
{the recent MIDAS orbit is only .00278 off a perfect
circle). For the nominal end acival Powered Trajec-
tory Flight Plan refer to Table 1. Table 2 presents a
comparison of nomined predicted orbital Parameters
with those actually achieved by the satellite.

PARAMETER NOMINAL ACTUAL
Apogee SOS 408.8 NM
Periges S70. 78.3NM
Pertod 99.67 Min, 99.17 Min,
Latitude of injection 42.336" N. 42277" N.
Longitude ot injection 56.90° W, 57.048" w.
inclination angle 48.330" 48.359°
Payleod spin rate 12 0pm 100pm

fin orbiny

Table 2. Orbital Parameters

NOMINAL ACTUAL
vet (Time in Seconds) | (Time in Seconds)
Vertical iift-off - 0 °
Bell Telephone Laboratories (BTL) guidance begins Stage | 90 90
closed-loop steering

End Stage i pitch program 130 129.55
MECO—Stage | main engine cutoft 158.5 160.80
Stage II separation and ignition; begin Stage Il pitch program 162.3 164.70
BTL guidance begins Stage I! closed-loop steering 172.3 175.80
BIL guidance ends Stage Ii closed-loop steering 253.9 250.90
BTL discrete ends Stage It pitch program 255.5 252.80
BTL discrete spins up third stage and payload—120 rpm 268.6 265.70
Stage Il cutoff—SECO; begin coast period 270.6 267.70
Stage II-I!! separation; start Stage itt 272.1 269.20
Fire Stage Ill rocket 662.89 664.0
Injection into orbit 700.31 699.0

WDLPM-4 212

Table 1. Powered Trajectory Plight Plan

CONFIDENTIAL



A. THOR—DM-18 / AGENA “ar

B. THOR—DM-21 / AGENA "BY C. THOR—DM-21 / AGENA "B”
MB-3 Block 1 / XLR81-Ba-7 MB-3 Block 2 XLR81-Ba-9
teey

Flight a

DISCOVERER AGINA THOR
No. Ne. Ne. Flight Date Remarks
o 1019 160 21 FENA
Jenvary SHON soars (aateartion on pal
i} 1022 163 28 Feb 1959 fey ficined orbis successfully, Telemetry received for 314 seconds after
il 1018 170 3 orbit 17% orbit
Ao ett, Rem tl a 74
m 1020 174 ‘3 June Launch, toast and orbital boost Failed
10 alee ori bree of tos perf sea ie
WV 1023 179 25 June Same as DISCOVERER III.
v 1029 192 13 Au
gust ibiectines seccessfally achicoad except capsule recovery efter
vi 1028 200 19 August Same «s DISCOVERER V.
vu 1051 206 7 November ined orbit . Lack
Fp ors bas aap aly. La of 400-¢ycle power prevented sia-
vint 1050 212 20 November ined orbit, ep AGENA
a a i Mt mt Gt
ix 1052 218 4 THOR shat down pr rile cord mast did wet retract.
Febrvary Quick disconnect falod, canvang tom of belinm pressure.
x 1054 223 19 February THOR deuveyd aT plat 36st by RengeSehy Offer
xt 1055 234 15 April Attained orbit ee sietsid capsale ejected om 17% orbit

pa ttt recovered, "AN ob ifectives except recovery successfully

AS