43 4733
6492 12,950
6 Als
than 18421
‘YURs1-Be-5 —-XLRB1-Ba-9
15400 16,900
a7 290
120 240
Figure 1.
feapon System 1
Artists’ concept of SAMOS satellite. in We ’ 171 when

Line drawing of complete flight WS 1171 was iransferred to the
vebicle (right) and detailed view of
basic AGENA upper stage (left). early in 1958. ARPA seporated
WS 1171 into the DISCOVERER,
SAMOS and MIDAS programs with
the SAMOS objectives based on a
visual ond ferret reconnaissance
system. On 17 November 1959
responsibility for this program was
Wwonsferred from ARPA to the Air

Force by the Secretary of Defense.

PROGRAM MISSION

The primary mission of the SAMOS advanced
reconnaissance system is to provide visual and
electronic reconnaissance of the USSR and its
allied nations. Efforts include development of
hardware to permit:

“a. Determination of characteristics of enemy

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,



CONFIDENTIAL

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 multi-stage
space flight.

ABLE-4 THOR vehicle was lounched on 11 March
from the Atlantic Missile Range and succeeded in
placing the PIONEER V satellite into a solor orbit.
At its closest approach to the sun, the satellite will
Pass near the orbit of Venus, and return to intersect
the orbit of earth at its greatest distance from the
sun. The vehicle consisted of a THOR first stage,
ABLE second stage with AJI0-101 liquid fueled pro-
pulsion system and an STL guidance system, and on
ABL248A-3, solid fuel third stage. The 95 pound
Payload contains instrumentation for conducting

-_ Fi 5. ABLE-4 ATLAS vehicle drawing and
are vebicleinsallad on AMR levech pth = “ad POote of

satellite telemetry until the last transmission was
' received on 6 October. It is belleved.that the satel:
lite, while yet in orbit, is incapable of generating

4 sufficint power for transmitting signals due to solar
a Paddle damage suffered during initial paddle exten-
sion and the resultant unfavorable sun “fook” angle.

: ABLE-4 ATLAS— This vehicle differed from the
~ ABLE-3 only in that an 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 @pprox-

_ imately 48 seconds after launch. The ATLAS per-
formed as planned over its entire powered flight

trajectory. The trajectory of this flight, from ‘the

4 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 inertiat velocity of 34,552 feet

per second. The payload was designed fo investigate Figure 4, PIONEER V saellite vebicle shown in orbital ight

space environment and propagation effects and to Nereb ingot "0 Swellte was launched from AMR’ on ‘11

WDLPM-4 205 CONFIDENTIAL By



4. The same propulsion system will require less
Propellant to accomplish orbital Injection.

5. Internal structure and Packaging will require
redesign for the new mission,

6 The 6-hour orbit is feasible. A final stage

velocity of 1085 ft/sec is required to complete the
launch trajectory and to perform Post orbital cor-
rections.

@ Vacuum bearing tests, radiation effects on mate-
tial studies ‘and other test programs for acquiring
design data are being continued.

‘SECREW WLP a



Station Nr, of Exercises Hours of Operation
AMR T 0.5
Manchester 132 46.6
Singepore 4 15
Hawaii 146 60.4
Satellite Sensor Telemetry

e This Information is tronsmitted by “word 7 of
the seven word Telebit System and includes the sub-
commutated values of eight satellite condition sen-
sors. These values become meaningless when
information received indicates a condition which is
known to be impossible {e.g. battery voltage level
too low to operate the transmitter at the time the
transmitter is operating). Such a condition resulted
from analysis of the telemetry received on 16 April.
During the next five days a thorough analysis of
“word 7” data was made by Space Technology
Laboratories personnel. This effort confirmed the
existence of a single open diode in the Telebit unit
which was causing the logic of the circuitry to be
altered. Since the alteration to the logic was constant
and consistent, STL was able to break the new code
and prepare a translation table which permitted
“word 7” values to be interperted correctly.

Experiments

Magnetometer
@ Magnetic field measurements performed by this

experiment have had significant value in the follow-
ing three areas;

1 Verified the existence of a magnetic ring cur-
fent surrounding the earth at an altitude of Sto 7
times the earth's radius. First observed by EXPLORER
VI (ABLE-3), this ring is believed fo have an inter-
relationship with the polar aurorae. Information ob-
tained, therefore, is of great value in the study of
interruption of polar communications.

2. Verified PIONEER discovery of extensive mag-
netic field disturbonces between 10 and 14 earth's
radii, establishing the existence of @ constant solar
wind of protons which produce a turbulence at the
fringes of the earth's atmosphere. This data lend
credence to theories connecting solar winds with
ionospheric disturbances,

Be CONFIDENTIAL

3. Discovery of a significant ionized gas activity,
adding. support to the belief that earth's magnetic
disturbances, plasma phenomena and cosmic ray
miodulations are interrelated. The experiment con-
tinves to operate successfully.

Proportional Counter Telescope

@ This University of Chicago developed experiment
is providing excellent measurements of both primary
cosmic ray and low energy background radiation,
EXPLORER VI data hos been verified. The experiment
also confirmed the belief that the electromagnetic
disturbance which Gccompanies sudden decreases in
cosmic ray intensity is not coused by factors related
to the earth.

ABLE-5

Program Administration

©@ Specifications, Funding, Test Objectives and
Technical Direction requirements were in the Process
of being established and defined during the report-
ing period. The Detailed Test Objectives document
for the first flight will be published in May. Technical
Direction meetings were held ‘mong representatives
of AFBMD, Convair, Aerojel-General Corporation
and NASA,

Technical Progress

Flight Parameters

@ = The nominal trajectory was established during
April,

e A study was completed of the feasibility of pro-
viding attitude stabilization to minimize fipott velocity
errors experienced on prior ABLE Program lounches.
Study-results are being evaluated.

© Preliminary weight and performance data have
been released.

Communication System

e The spare receiver for the ABLE-4 THOR is being
Converted for use on the ABLE-5. The signal condi-
tioner design is essentially complete. Construction
‘and test of the 2-watt transmitters are on schedule.

e The digital decoder has been assembled from
spare ABLE-3 and ABLE-4 components and is under-
going environmental test prior to delivery as a type
{est item. The ABLE-4 ATLAS digital telemetry unit
has been modified.to the ABLE-5 configuration and

WDLPM-4 205



ENS nee

' ¢ ° 1. First Stage Powered Flight—2.5 minutes
Powered Flight Trajectory derotion, 78 num. dewnronge, geided by wre,
P grammed ovte pile.
fc 2. Coast Poried—2.4 minwtes duration, to 380 _
a.m, downcongas guided ond attitude contolled
by inettil. reference programmer, horizon scar
et, gos reaction jett. Receives AGENA time to
fire’ ond velocity 10 be goined commonde,
2 Secand Powered Hight—2 minutes
ducton to Te nee renee Gudea
controled by inertial reference programmer, hori:
Fon sconner, gor reaction jety (oll) gimbal
engine, accelerometer, ee
4. Vehicle Beestents te Nese Aft—2 minutes

is 20 4.8, downnge Geided ond
5. tw-Qrbtt—Grided and controlied {came os 4)

ee

fF  @ |e

Orbital Trajectory

Schematic presentation of orbital trajectory following laxach
from Vaderbere Air tome Base. Fancitons perfon by
gach station and a listing of equipment used by each stetion,
is given on page Acd,

! RECOVERY CAPABILITY

This objective was added 10 she program
de, ihe, fet aah wird le
it e453} f.
H theeides the orientation | the satellite
to permit a recoveral sapsale to
be ejected from the wore secine ofS
AGENA vebicle. Ejection is programmed
40 oscar on command on the 17th orbit,
for capsule impact within the bredeter-
mined recovery area south of Hawaii,
Aircraft and surface vessels ave deployed

within the area as a recovery force.

CAPSULE RECOVERY SEQUENCE

‘jection command ts sext to the sai 7, the
Chiniak, Alaska station on the 16th orbit. The vebicle
seorients its position (see ise He berm it i ic
ou a ree ont 1. The rece
sale bute te wtlnaed gt shout 30,000 oat, wad the

fapoude beacon trantmits a radio sigual for tracking’ purposes.
mnt The recovery force it deployed in the recovery (impact) area,



SGREEP CONF ENTIAL

ADVANCED SYSTEMS STUDIES

1 The Advanced Systems Studies Division has seve
eral space studies in Progress. The purpose of these
studies is to determine the military missions and
mode of operation, in space. For the purpose of
study, space has been divided into three broad
Greas; earth orbital, lunar, interplanetary. Studies
in the lunar and interplanetary area are being man-
aged and directed at AFBMD. There are two studies
in the Lunor 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 lnar area which is defined as the
surfoce of the moon and the Grea in its surrounding
Gravitational field. This is a broad conceptual type
study which will examine alt focets of military opera-
tions such as offensive, defensive, and supporting
systems. This study wos funded with $600,000 in
Fiscal 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 orea
will be a surveillance and intelligence collection syt-
tem. Therefore, SR 183 (U) Lunar Observatory was
initiated to examine this Problem, The objective of
this study requirement is to determine a sound and

logical approach for establishing @ manned intelli-
Gence observatory on the moon from. which the
entire earth and its surrounding area can be kept
under continous surveillance, All earth orbital sys-
tems can be monitored and enemy activities in space
and on the lunar surface can also be watched, Alf
Possible types of sensors and their probable ranges
will be examined. This study will olso include the
supporting and establishing the
lunar base. This study was funded with $420,000 in
Fiscal Yeor 1959, Three contractors were funded
Gnd three additional contractors Gre performing the
study on a voluntary basis. Consequentty, it is esti-
mated that this study has the equivalent of $1.5
millions being applied to it. .

4, The area is being studied under
SR 182 (U) Strategic Interplanetary System. The
objective of this study is to determine the possible
military missions and the type of equipment nec:
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 Gre much
greater; our present knowledge of the area Is lim-
ited, therefore, special types of navigational ond
Propulsion systems will be tequired. This study was
funded with $285,000 in Fiseal Year 1959 which
has been distributed ‘among three contractors. Con-
tractors’ final reports are due at AFBMD in Feb-
ruary 1960,

M-1


‘CONFIDENTIAL

Monthly Progress—TiROS Program
Flight Test Progress

© Information on the successful TIROS launch from
Atlantic Missile Range stand 17A on 1 April was
Included in last month's report. The three-stage
THOR-boosted flight vehicle placed the TIROS pay-
loud into the most perfect circular orbit achieved by
this nation to date. Only a 0.3 sigma deviation
occurred between the programmed and actual orbit,
The two payload cameras have provided excellent
photographs of weather conditions Ground the earth,
These and other data objcined will add immeasur-
ably to our knowledge of Meteorological phenomena.

@ Table | presents a comparison of nominal Pre-
dicted orbital Parameters with those actually

Achieved by the satellite. As cf the end of this report-
ing period, TIROS. continues to function excellently,
both in vehicle orbital performance and payload

operation.

Paremeter Nominal Aded
Apogee 381.5 NMI. 406.8 N.MI.
Perigee 379.8 N.Mi. 376.3 NMI.
Period 98.67 Min. 99.17 Min.
Latitude at injection = -42.336°N--42.277°N
Longitude at injection 56.90°W = 57.045°W
Inclination angle 48.330° 48.359°
Payload spin rate 12 rpm 10 cpm

{in orbit)

TABLE 1. ORBITAL PARAMETERS

Figare 1.

. Pi
satellite ooking towend the wets from over 400 ales ne

H2

rpote of the Strais o

WDLPM-4 205


WDLPM4 205

CONFIDENTIAL

Monthly Progress—COURIER Program
Technical Progress
COURIER 1A

@ The AJ10-104 Propulsion system was delivered
fo the Space Technology Laboratories hangar on
12 April, one month behind schedule. This delay
hos made necessary extensive revision of checkout
vans used in both COURIER and TRANSIT Programs.

Checkout of COURIER 1A, using Van #2, will be
completed as rapidly os Possible to alleviate this
silvation. The launch date remains 15 July.

COURIER 1B

© Aerojet-Genesal Corporation and Space Elec-
tronics Corporation are continuing component ond
subsystem fabrication based on a scheduled launch

date of 1 September. No slippage in the launch date
because of vehicle design changes is anticipated.


Final Systems Checks

Systems checkout of the ABLE-STAR
vehicle at the Atlantic Missile Range.
Photo above shows vehicle in verticle

position, checkout console in fore-
ground, and mobile checkout vans in
background. Closeup (upper right)
during engine checks. Photo at right
shows complete test layout.

WDLPMA 205 CONFIDENTIAL



ROLL JETS HEAT SHIELD

ENTRANCE HATCH —,

HORIZON SCANNER ~

ESCAPE ROCKET. PITCH @ YAW JETS : \
PARACHUTE
Q
aur $6 —
_ ROGKe Peat

ROCKET
RET ROGRADE-

WEIGHT AT SEPARATION APPROX 25 LBS

ORBIT INCLINATION 33 DEGREES
ORBITAL ALTITUDE, (05-115 MILES (n) HEAT SHIELD ABLATIVE
ORBITAL CYCLES 3-18 RECOVERY WATER OR LAND

Fianre 1. Complete vehicle (top view) with satellve inated om ATLAS booster, Manned satellite
(bottom view) Dowie piltt Nigh povtion, end deta viaws of sara and posigrade rocker wed rice
safety system escape rockets,

WDLPM4 205 -CONFIDENFIAL Kl


WDLPM-4 205

“CONFIDENTIAL

Monthly Progress—TRANSIT PROGRAM
Flight Test Progress
TRANSIT 1B

@ As reported last month, a very successful
TRANSIT 1A launch was made from the Atiantic
Missile Range at 0702 hours, EST, on 13 April.

Parameter Newinat Actual
Apogee SOONMi. 408.64 NLMi.
Perigee 500N.Mi. 175.38 N.Mi.
Period 103 Min, 95.25 Min.

Inclination Angle —45.95° 51.28°

TABLE 1, ORBITAL PARAMETERS

@ As shown in Table 1, the guidance system did
Not perform as expected and caused an elliptical
orbit rather than the expected circular orbit. The
guidance system obtains angular velocity data by
doppler measurement and integrates this informa-
tion to provide the required position data, During
launch, a sufifcient amount of rate information was
lost to cause the resultant error in position data.
This esror occurred during first stage flight which,

; becouse of the TRANSIT trajectory, is the most critical,

TRANSIT 2A

@. the TRANSIT 24 flight test has been rescheduled
to 21 June. Analysis of TRANSIT 1B guidance data
will result in the following change being made. The
FPS-16 radar anguler dato will be used by the
guidance system from liftoff through the first twenty

seconds of second stage flight. From this point on
the guidance system will use its internal data. This
change assures the capability of meeting orbital
specifications. No modification to airborne equip-
ment is required. The five week delay will be used
fo adapt the FPS-16 radar data to the guidance
computer end to change the computer program to
‘accept this date.

Technical Progress
TRANSIT 2A

e Assembly and checkout of the second stage was
completed and the vehicle was shipped to the
Atlantic Missile Range on 21 April. The AMR check-

out is proceeding satisfactorily with all subsystem
fests having been accomplished.

@ Wind tunnel tests indicated that a transonic
velocities pressures on the nose fairing had a tend-
ency to separate the fairing valves. The addition of
two explosive bolts will prevent Premature separation
Of the nose fairing.

TRANSIT 2B

©@ No design or assembly Problems effecting the
TRANSIT 28 vehicie have been encountered.

Ground Support Facilities

© The mobile downrange telemetry and tracking
von has been shipped from Germany to Punta
Arenas, Chile, and checkout is being accomplished.



Monthly Progress—SAMOS Program
Second Stage Vehicles

© The AGENA vehicle for the first SAMOS flight
Is undergoing system checks in the System Test Area.
Late delivery of airborne communications equipment,
vehicle wiring changes and problems encountered in
completion of the systems checkout complex has
caused c one-month delay. The wiring changes were
completed on 6 April, the UHF narrow band trans-
mitter was delivered on 14 April. The systems check-
out complex is complete except for equipment to
check out the UHF wide band transmitter. Completion
of systems tests and shipment to Santa Cruz Test Base
for hot firings is schedule! for mid-May.

e The second AGENA flight vehicle was delivered
to the System Test Area on] April. Vehicle wiring
changes caused a two-week delay in delivery.

© Final assembly of the third and last AGENA
“A" vehicle is in progress. This vehicle will be
delivered to the Systems Test Area on schedule.

e Design efforts for the first of seven AGENA "BY
vehicles scheduled to carry the recoverable payload
{E-5) are proceeding on schedule.

© Visual Reconnaissance System Poyloads are
being developed in a minimum number of configura-
tions to attain readout and Fecovery mission
objectives. The design and purpose of each configu-
tation is as follows;
Readout:
E-1—Component Test Payloads
£.2—Steerable Reconnaissance Payloads
(with 20-foot ground resolution)
2
ee oh Resolution, Steerable, Recoverable
Payload {with 5-foot ground resolution)

Payloads

© —E-] Payloads—Operational tests of the second
E-1 payload were successfully completed and the
Payload was accepted at Eastman Kedak on 14
April, The tests were of 19 and 48 hours duration.
The payload is being prepared for subsystem testing
Gnd installation in the vehicle. A thermal model of
the E-1 Payload also was delivered during the month,
This model will be used for additional environmental
testing. Modification and checkout of the third E-1
Payload is continuing.

Figure 7. The fest SAMOS/AGENA vebicle during chechont iz the Systems Test Area. The E-1 and
. F the forwmerd bendliog Kater. °

«1 payloads are mounted on



Grom Weight (Bumout)
Specific Impulse frac)
Theat (voc)

THIRD STAGE ABL 248-A9
Gross Weight
Specter
Theust (woe)

SECOND STAGE AJ 10-101
Grom Weight
ace

impulse (vax)
‘Threst (vac)
FIRST STAGE ATLAS “D”
Gross We

Specific Impulse (voc) Sestainer
Spectic Impule (5 Ly Booster

scientific experiments related to magnetic field and
radiation phenomenon in deep outer space. Also
included in the satellite is a 150-watt transmitter

Figure 3, ABLE- vebicle con, ”

own cog thleoge” (e

EARTH AT TiME
“OF AMR LAUNCH

which is expected to permit communications between

the satellite ond earth over an Gpproximately 90
million mile range.

ABLE-5

The ABLE-5 program provides for launch of two
ATLAS-ABLE vehicles to Place satellites into tunar
orbits late in 1960. A Proposed ATLAS/ABLE lunar
Program was submitted to AFBMD by NASA on 4
Februrary 1960, following discussions between
AFBMD and the NASA Goddard Space Flight Center
in January.

Program Objectives

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

2. Maintain adequate earth-satellite communica-
tions and establish communications parameters for
future space probes.

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

4. Successful conduct of payload experiments.

mo ~CONFIDENTIAL

\
\

,
drawing and ification list. Third
i). rfecoly of ABEL S te ft, Thind

LEGEND
—————~ PATH OF MOON
wo wom ABLE-5 TRAVECTORY
~~ = SATELLITE ORBIT OF MOON

WDLPM-. 205


S3IGNIS IDves



Rocketdyne Div., North
American Aviction
Height tet

Diameter 10 feet
Weight 261,206 pounds

SerlesDATLAS = MA-2

Oxidizer tox

Quidence — Radio-inestiod
General Blectric (redex)
Burroughs Corp. {computer}

Used os first shege fer:

Early in 1958, the decision to accelerate ihe national space effort was made effec-
tively posible only because of the availability of the THOR IRBM. THOR No. 127
wos diverted from the RD flight test program for use as the ABLE-1 space probe
first stage. With top national priority assigned fo the space research effort, THOR
No. 163 was used to boost the DISCOVERER I into orbit on 28 Febcuary 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 hes been increased
through weight reduction modifications and use of RJ-1 {instead of RP-1) fuel. In
April 1960 4 modified THOR, designated DM-21, will be available, incorporating a
1900 Toe hens can uemmmumamml iat reducon chow In Juty
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 as
the first stage booster for the three Advanced Militory Scteliite 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 108) successfully placed @ 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. flight test vehicle in Project Mercury was launched on 7 September with
Ol objectives essentially achieved and excellent ATLAS booster performance
realized. Future flights will use modified ATLAS series “D* missiles to carry
increased payload weights. Project = F

Mercury boosters are being modified
also to Indude cbort-sensing and
other pilot safety features. The success
of the first three ATLAS boosted space
flights, plus the increased perform-
ance and reliability being demon- ‘
strated in the ATLAS R&D flight test
Program, lend confidence in this
booster as a means of realizing

lings FONT



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

Arnold Engineering Development Center

Air Proving Ground Center

Air Defense Command

Air Training Command

Air 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 Semardino Air Materiel Area

6594 Test Wing (Satellite)

1002 Insp. Gen. Group

3415 Technical Training Group

Tactical Air Command

CO HOLE Ed.

WDLPM-4 205

am

32

-o

~---8 sw wa

a nada Se Se oe CaS


more.advanced phases was replaced by a 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 ‘satellite in a predeter-
mined position ina 19,300 mile equatorial orbit must
be demonstrated. The satellite must be capable of
Providing worldwide communications on a real time
basis ot microwave frequencies with a high channel
wide bandwidth capacity. Amendment 5 also
requires the design of a single final stage vehicle for
microwave equipment compatible with launching by

either AGENA “B" or.CENTAUR second stage
boosters.

The ADVENT program, as defined in amendment
5, will consist of the following fight tests:

a. Four ATLAS/AGENA "BY filghts, nominal 5,600
nautical mile orbits,

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

a Three flight tests, using poyload space on

NASA ATLAS/CENTAUR RED flights Number
4, 5, and 6,

Figure 2. Artist's concept of proposed microwave communications.

‘WDLPM-4 205


rRORIA | PLATFORM
msRTIAL PLAT § Compuren
COMPUTER GUABALLED

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

- Ferret Reconnaissance...

Figure 4. The Fervet reconnaissance system will gather date from electronic emissions over areas of interest,

age eee eee ee ee ee ee ee ee



AQENA
“4
SOLAR
ARRAY
BEACON DESTRUCT
ANTENNA: CHARGE
.
| THERMAL/DATA LINK LNOSE CONE~-TM EXIP—EQUIA~-OXIDIZERTM-FUEL
SHIELD ANTENNA SEPARATION ANTENNA COMPT. TANK TANK sooaten
NOTE: AGENA “A” configuration except AS icant
for solar poddlen (AGENA “®” only) Weight—Wet 18,100
Fuel, RP-1 74,900
Oxidtzer 10%) 172.300
GROSS WEIGHT (be) 262,200
: Engine—MA2
4 ‘Thrvst (ibs. voc) Bos! 356,000
. ‘Sestainer 42,100
| Spec. Imp. (sec. vec.) Boost m5
Sustoiner 310



ewe ele, we

Figure 6. SAMOS concept, showing reception of commands and bransmission of data
Or acon satellite and ground Sitoke and Linen fanctions (schematic).

For economical testing of components a dual-
capability visual and 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 transmitted in the readout 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 © communications
and data processing network. The Fecovery system

will also indude a re-entry capsule and a recovery
force.

CONCEPT

ATLAS Series D missiles tounched from VAFB will
boost the AGENA vehicle into polar orbits. Injection
into near-circular orbits {Figure 2) will be accom-
plished by the AGENA vehicle rocket engine. A self-
contained guidance system Using @ horizon reference
scanner will provide altitude stabilization. As the
satellite travels in an orbit essentially fixed in space
the earth rotates inside the orbit (Figure 3). Each
successive orbit is displaced laterally @pproximately
23% degrees at the equator, Permitting one vehicle
to observe the entire earth in o time Period depend-
ent upon the width of the area under surveillance.
Early versions will have a useful life of approximately

ten days. The readout systems will have a useful life
of four months with a design objective in certain
configurations of one year; recovery systems will
have a useful life of fifteen to thirty days.

TECHNICAL DESCRIPTION

Visual Program—Payload camera, film processor
and electronics readout equipment are being devel-
oped by Eastman Kodak Co. Cameras having a
36-inch focal length ore being used. The Payload
equipment includes automatic film Processing, film
transport and take-up, electronic Feadout and tem-
Perature controls. The recoverable system will retain

both the exposed film and the 66-inch local length
camera, .

Ferret Program—Ferret Payloads are being devel-
oped on a pi more advanced basis from
R&D (F-1) to advanced systems (F-4). The F-2 all-
digital, generat coverage payload will use super-
heterodyne scanning receivers in conjunction with
directional antennas, an analog to digital converter
and tape recorders (for storageh A progrommer will
be used to controf read-in over areas of interest and
readout over tracking stations. The F-3 payload will
use similar receivers with stop-scan capability and
controliable antennas added, Recording of the actual
signal intercepted {rather than the digital represen-
tation) will be possible with a bandwidth Up to é6me.
A complex programmer will Permit satellite search
of a given area or frequency range.


‘WDLPM-4 205

Monthly Progress—
COMMUUNICATIONS SATELLITE Program

Program Administration

e Two development plans have been prepared by
AFBMD in compliance with Amendment 5'(dated 11
April 1960} to ARPA Order No. 54, The first plan
includes four ATLAS/AGENA launches early in the
Program. The second development plan is identical
except that the four early launches are eliminated.
The principle program objectives could be more ade-
Quately supported if the funds for the ATLAS/AGENA
haunches were made available for ATLAS/CENTAUR

* launches later in the program.

Technical Progress
UHF Communications Equipment

@ Aphesing-out Program for the UHF communica-
tions equipment has been started, calling for com-
Pletion of at least three satellite repeater units and
@ minimum amount of test equipment. These units
will be delivered to WADD where reliability life tests
Gnd simulated system evaluation tests will be con-
ducted,

Mkrowave Communications Equipment
@ Draft specifications for the ground antenna,
ground stations, and the satellite package were com-

pleted by the United States Army Signal Research’

and Development Laboratory and reviewed by the
Air Force Ballistic Missile Division on 20-22 April.

e The ‘test report from Varian Associates on the
high power, 8000 mec klystron tube will be delivered
on 15 May.

launch Vehicles

" @ "A study ‘hos been performed to determine the

modifications required .and the Payload capability
increase that would result from using the “E” series
ATLAS booster instead of the “D" series. Results of
the study indicate greater reliability for the “D'
series and an increased payload weight capability
of 90 pounds for the "E” series.

@ The use of various amounts of liquid fluorine in
combination with the oxidizer (LOX) on both the
ATLAS and CENTAUR stages was investigated.
Results show that a 20 percent fluorine-LOX mixture
in the ATLAS increases the final stage vehicle Pay-
load capability by 220 Pounds and an additional
120 pounds by using the same mixture in the CEN-
TAUR. Further studies will be made to:

CREE

1, Determine the toxicity and resulting hazard
of fluorine exhaust gases.

2. Evaluate the material compatibility of com-
Ponents with fivorine.

3. Resolve thrust chamber cooling problems.

4. Determine ground support, handling, storage |
and mixing methods for fluorine.

@ A review of CENTAUR static.tests indicates that
the estimated nominal specific impulse of 420 sec-
onds is correct. Several static tests have indicated a
specific impulse of 428 seconds, further develop-
ment and testing is required before this higher value
can be assured for all engines.

© A study of increases possible in Payload weight
sepability by using 24-hour inclined orbits rather
than 24-hour equatorial orbits was ‘completed. The
Payload weight capability for the ATLAS/CENTAUR
configuration increases from 1100 to 1600 pounds
when the orbit is inclined ot 28.5 degrees to the
‘equator. As the angle of inclination increases, the
weight capability decreases and at 40 degrees is
1550 Pounds. Trajectory studies also were made of
24-hour polar orbits, launched from the Atlantic
Missile Range.

Final Stage Vehicle

@ General Electric Missile and Space Vehicle
Department is making the transition from designing
the final stage vehicle for the UHF mission to that of
the microwave version. Previous studies are being
adapted to the new program. Vehicle analysis,
based on the equatorial Program description, is
being accomplished, Configuration, internal arrange-
ments, a new external environment specification, and
test planning are In process,

© A series of studies has been completed to deter-
mine the modifications required io make the 24-hour
final stage vehicle compatible with a é-hour orbit
inclined at 34.2 degrees. These ATLAS/AGENA
flights would be founched from the Atlantic Missile
Range. Results of the studies include:

1. The communications antenna must be tede-
signed to increase the radiation beam width,

2. Temperature control and electrical power sub-
systems are more than adequate.

3. Modification of both the attitude and orbital
control subsystems will be required to maintain
antenna and solar array orientations.



CON oT

@ The AGENA “B” vehicles (XLR-81Ba-7 engine)
for DISCOVERER flights XVI and XVIII underwent hot
firing tests on 1 April and 19 April, respectively, at
the Santa Cruz Test Base. The vehicle for flight XVI
has been returned to the System Test Area for rework
‘and a second system check prior to Alr Force accept-
ance. Additional hot firing tests of this vehicle will
not be required.

@ = Pretiminary Flight Rating Tests (PFRT) of two
XLR-81Ba-7 engines were completed during the
month at the manufacturer’s plant. The gas generator
propellant valve malfunctioned during the tests and
will be redesigned and retested.

© Testing of nozzle extensions for the XLR-81Ba-9
‘engine continued at Bell Aircraft and Amold Engi-
neering Development Center (AEDC). All tests of the
45:1 area ratio titanium nozzles have been success-
ful. This nozzle has been released to production and
will be used on flight vehicles. However, develop-
ment of an uncooled nozzle which will provide a
weight savings of five to ten pounds and simplify
fabrication Is continuing.

@ Acceptance tests of the XLR-81Ba-9 engine at
the engine contractor's facility revealed erosion of
the thrust chamber throat. UMSD propulsion system
representatives reviewed the problem with Bell Air-
craft engineers and a program which provides for
tighter control and acceptance testing of engine
components is being established. A procedure for
coating the thrust chamber with Zirconia is being
instituted and injection modifications are being made
which should reduce the omount of thrust chamber
throat erosion.

©@ The Preliminary Fight Rating Test (PFRT) pro-
gram for the XLR-81Ba-9 engine is scheduled to
start 15 May using the existing thrust chambers.
An additional PFRT program will be conducted to
Prove the realiability of the thrust chamber modifica-
fions prior te the first launch.

Antennas

© Type testing of the transistorized S-band beacon
was accomplished during the month, The successful
completion of these tests qualifies these weight sav-
ing beacons for use in the AGENA "8" vehiicle. One

Figure 2, First. DISCOVERER/AGENA "B" sebicle bein;
installed i in test stand 2 a3 Santa Cruz Test ‘Bare Tht webs
will be used on the DISCOVERED XVI flight.

A-7



Ready for Launch

Photo below shows TRANSIT 1B
vehicle on launch Stand 17B, AMR.
Service tower is on the right.
Closeup (left) of ABLE-STAR and
Payload. Electrical umbilical on top
of ABLE-STAR provides power

and signals for guidance equip-
ment. Service leads for the
Propulsion system are attached to
the rear of the vehicle.

WDLPM-4 205 —CONFIDENTIAL 1s



~ Performance Graphs — Boostss

10000 T T T 800 ry 7 T
‘9000 [— ATLAS/AGENA “A” and “B" 4 xi ATLAS/AJ10-104/ABL 248 +
_ sco =
600 5
. re 00
= 400 =
3 2 IN
_ E 2000 SI
de !
E 800 7 200 z
< 600 . FS
=
“ a 6 3e 40 5
~ “ T T 4
200 ATLAS/AJ10-101/ABL 248 — !
_ 1 2 3 4 6 600] g
: 4 &
P TLAS/ MERCURY
1000)
- = _ 5
3. L
_ 3 so
| 400 NY
~ B os 200 N
5 3 NN
= 109} pe
PAYLOAD WEIGHT x 1000 POUNDS BURNOUT VELOCITY—FPS x 1000
1. AGENA “A"— Polar Orbit 4. Lunar Probe
2. AGENA “B"— Polar Orbit . 5. Venus Probe

3. AMR—90 degrees

+


Facilities Oo © Construction of the North Pacific station techni-
Z facilities at Donnelly Flats, Alaska, and the support
facilities at Fort Greely, Alaska, were resumed on 1
April. Facilities are scheduled for completion on an
incremental basis from July through October.

@ Surveys are being continued to locate a 5 le
site for the North Atlantic station.

‘WDLPM-4 205



“CONFIDENTIAL

f ~ THIOKOL

(IMPROVED.
XM33E5

31"

| ~ AEROVET
"SENIOR

77 ABL X248 A6
20 JETS

SERGEANT

(ALT. NOZZLE)
Ho 05 JETS

33KS 120,000
YET VANES AND 3}
AERO FINS = &

pee
PROJECT 609A
————
Hyper-Environment Test System
a anannt ecirtie

PROGRAM DESCRIPTION—The Hyper-Environment
Test Program (609A) is divided into R&D and Opera-
tonal Phases. The R&D phase wil be used to davelop
and filght test vehicles copable of carrying 50 to
1,000 pound payloads to altitudes of 200 to 7,000

HoO JETS miles. The Operational phase will use this standard.
ane ized vehicle to permit the economical performance
te 30" Of flight test experiments in support of scientific

research and advanced military space system
Programs.
Reliability—Versatitity— in this order

Economy—
of emphaais are the three significant guides to pro-
gram accomplishment, ECONOMY is being achieved

NOTS I00A-
AJIO-41 :

BOKS-B000}—

)

X254-AI— |

2

meee

I-2-3" CONFIGURATION SN

~~ CONFIDENTIAL ay


DEVELOPMENT PHASE

Launch Schedule

Monthly Progress—Project 609A

Program Administration

© A conference was held with representatives of
the Dyna-Soar Weapon System Project Office con-
ceming the flight testing of Dyna-Soar models with
S09A vehicles. Four tweive-foot models will be
launched by 1-2-3 configuration vehicles (Figure 1)
starting in June 1961.

e A request has been sent to ARDC requesting
additional FY 60 (P620} funding of $1,043,000 for
the Development Test Portion of the program.
Increased costs of hardware and systems manage-
ment made this request necessary. Additional
information requested by Hq AROC will be Provided
in May.

@ Funding for design and construction of addi-
tional facilities required at AMR was requested. An
Odditional $1,060,000 (300 series) will be required
fo support the follow-on program.

@ The delays in the NASA program, combined
with the firm Hq USAF commitment for 609A ‘sup-
Port of the Navy TRANSIT Program have necessi-
fated program reorientation. Aeronutronic has been
requested to submit recommendations for back-up
develépments, studies, and supplemental tests re-

+ quired to permit the Air Force to proceed on its own

Program in case NASA cannot resolve these devel.
opment problems. This information will be included
in the revised 609A Development Pian being pre-
Pored by AFBMD for submission to Hq ARDC in May.

Technical Progress

@ A reguiar monthly technical coordination meet-
ing hes been established. During this month's meet-

Figure 3. Moci load carrier with jettisonable
ayr0 reference package (center), Typical payload
are mounted

ponent the oasibmest racks, This
connor can be installed ‘on either ae es ‘or the 1-2-3-4

Se: i



ing @ discussion was held regarding NASA difficul-
fies in assembling the first SCOUT vehicle. A require-
ment was estublished for a complete ‘assembly and
fit check of the first 609A guided vehicle at Change-
Vought prior to shipment to AMR for launch. Tech-
nical difficulties ond these new requirements have
caused a three week delay in the launch of this
vehicle. Launch is now scheduled for 11 August.

© Simulated high altitude tests Of the ABLE X-254
‘engine conducted at Arnold Engineering Develop-
ment Center in Aprit tevealed nozzle liner blistering
Problems. Corrective measures have been taken and
additional tests are planned. NASA will use the first
SOPA flight engine for the test and replace it with
one from later production. This has delayed the
launch of the first 609A (unguided) vehicle until
8 June,

@ Prior to approving 609A launch operations
Range Safety at AMR has requested that tests of
the destruct system be performed using fully opera-
tional engines. Procedures for these tests were estab-

ai HOLE TAC

lished at AFBMD on 28 April and a test directive is
being prepared. A rejected X-254 engine will be
tested at Edwards AFB during mid-May ond a re-
lected Aerojet Senior engine will be tested early in
June to satisfy the AMR requirements.

e A modified SCOUT vehicle was launched on an
unguided flight on 18 April. This vehicle consisted of
live first ond third stages, a dummy second stage,
and an inert nose cap. This was the first flight Test
of the SCOUT first and third stages. The first stage
Performed satisfactorily, but prior to burnout, oscil-
lations developed and the vehicle forward section
broke off. Anolysis of flight data indicate that the
breakup was caused by the vehicle spin rate. Since
the guided version of the SCOUT does not include a
spin requirement, these stresses will have no effect
on guided flights,

e ‘The first full scale SCOUT missile has been
essembled at Wallops Island and final checkout is
being accomplished. NASA has scheduled this launch
for earfy in June,

WDLPM-4 20°


VERIFIED

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 data by at least one of

secon ——— iam, ise arith de on

The MIDAS Control Center, or
Ied grotad nailed tiple vox
}, Catt
deters ebee a nd ea attach bas
been launched. The decision to
Seaneraitech is made by the Presi-
fy affected agencies react-

ing as preplanned.

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



a
AY

ABLE Vehicle

‘The ABLE upper-stage vehicle has been flight tested suc-
Cessfully as the second stuge on THOR re-entry vehicle
fests, ABLE Projects and TRANSIT 1A. The vehicle uses
AJ10-42 of AJ10-101 propulsion systems {improved
versions of systems used originally on the Vanguard
Program), guidance systems, and electronic and instru-
mentation equipment. The ABLE vehicles are guided
during second stage engine burning. Vehicles using the

Contractor:

Acrojet-General Comp.

Height 18 feet 7 inches
Diameter 4 feet 8 laches
Weight

ANo42 4622 pounds
ANI0-101 4178 pounds
Fool

Unsymmetzical Dimethyl Hydrazine

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

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

AJI0-101 system are spun with the third stage and pay-
load prior to second stage engine bumout to provide spin
stabilization of the Unguided third stoge 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 plane. Only minor
differences exist between the two propulsion systems,

Oxidizer
Inhibited White Poming Nitric Acid

Cvidence

ano42

Nedio-inertial (BTL)
ANO-10t

Advanced Guid, Syst, (STL)
Computer (Bueroophs J-1)

Used as second stage for:
AN10-42 — TRANSIT 1A, TIROS
AJIO-1O1 — ABLE 3 ond 4

ABL 248
Vehicle

Contractor:

Allegany Sollistic Leboratory
Height 4 feet 10 inches
Diameter 1 foot 6 inches
Weight 515 pounds
fuel Solid

Used os third stage on:
ABE 3 ond 4

TRANSIT 14, TROS:



Although originally designed

cs the basic sat.

elite vehicle for the Advanced Military Satellite
Programs, flight testing of the AGENA was accel-
erated when the DISCOVERER Program was

ereated, using the. THOR/AGI
Because of its availability,

ENA combination,
the Bell Aircraft

URB1-Ba-3 rocket engine was selected for AGENA

Propulsion, and later modified

to use unsymmet-

tical di-methyl hydrazine instead of JP-4 fuel,
Subsequent modifications resulted in the AGENA.

“Be

configuration, in which Propellant tank

capacity was doubled ond the engine modified
0 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 ond orbital attitude control was

developed to meet the critical
‘and attitude requirements for

orbital eccentricity
‘the programs in-

volved. Gos jets and reaction wheels are used

to control attitude. Payloads

may be installed

‘on the forward equipment rack or distributed

“8” version XLR81-0-7°

XURB1-B0-9°*
Feet vOMH
‘Oxidizer IRENA
Geidanee optealinertiol
Used es second stege for:
DISCOVERER CVI & vba)

SAMOS (fight 4 end she)
MIDAS (Fight 3 ond sube)

- ABLE-STAR Vehicle

The ABLE-STAR upper stage vehicle contains an AJ10-
is an advanced version of earlier
increased

Heighe 14 feet 3 inches
Olemeter 4 feet 7 inches
Weight 9772 pounds

Engine AJ10-106
with Restort Capability
Noxale Exponsioa Ralio—40.1 .

Peel
Uneymmetrical Dimethyl Hydrazine

Oxtdizer
lahibited Red Fuming Nitric Acid

Guidance
STL Advanced Guidance System
Berroughs J-1 Computer

Used es second stage for:
TRANSIT .1B, 2A, 2B
COURIER TA, 1B


le, — CONRDENHAL

of the beacons is undergoing compatibitity tests at
Vandenberg Alr Force Base. The first flight beacon
has been delivered to LMSD for Instaliction in the
AGENA “B” vehicis.

Biomedical Capsules

e Upon arrival at LMSD in May of the test capsule,

——IUSEZZ). specialized biomedical environmental test-
ing of flight components will begin. Vibration:

and impact tests designed fo as
aii tapos sas

Ground Support Equipmeat

@ Two new pleces of ground handling equipment
for the AGENA “B” vehicle are now in use. The first

is a ground handling dolly adaptable for either

AGENA “A” or “BY configurations. The vehicle will
be mounted in this stand during assembly and check-
out. The other piece of equipment is the vehicle
transporter. This trailer will be used to transport the
AGENA “8 vehicle between LMSD, Santo Cruz Test
Base and Vandenberg Air Force Base.

© An AGENA “B” facilities checkout vehicle for
use ot Vendenberg Alr Force Base was completed
during late April. This vehide is copable of facilities
checkout for the DISCOVERER, SAMOS and MIDAS
Programs,

Facitities

© = The construction controct for the Vandenberg
Air Force Base propellant storage and disposal
facility hes been awarded with completion scheduled
for September.



Performance Graphs — 1.2.5

THOR/ATTO-2/A8L 248 3000 4 THOR/ALTO-IO1 /aBl 248
2000
i 1000
j wo
600
be 1 1
400
L ? )
200
A ‘ f A i ' F . A ' 1
2 4 é 8 10 12 2 4 ry 8 to 12
T 7 7 : :
THOR/AITO-104 3000 THOR/AGENA “A” ond “8”.
2000
i 1000
r 4
800
eo 5
L 1
400
L 2
3
200
! 1 ' f 1 ' A 1 1 1
2 4 é 8 10 12 2 4 6 8 10 12
Paylood Weight x 100 pounds Payload Weight x 100 pounds

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

4.. VAFB—AGENA “S" (XLR81-Ba-7)
5. VAFB—AGENA “8” (XLR81-Ba-9)



© _E-5 Payloads—the basic design approach was
established and Preliminary interface problems
involving the E-5 recovery Payload were resolved
during this report period.

Grovad Support Equipment

e The vacuum test chamber for use in leak testing
E-1 and E-2 payloads prior to launch and the E-1
test console was shipped fo the Missile Assembly
Building at Vandenberg Air Force Base during the
first week in April. Installation and alignment of the
E-1 collimator ond checkout of the E-1 7-2 ground
reconstruction electronics equipment at the Missile
Assembly Building are nearing completion. Delivery
of the operating console and the ground reconstruc-
tion electronics equipment with repeater kinescope
for the Vandenberg tracking and acquisition station
is scheduled during May.

Ferrett Reconnaissance System
© = Ferrett Reconnaissance System poyloads are
being developed in a minimum number of configura-
tions. The designation and Purpose of each
configuration is as follows:

F-1—R&D Test Payloads

F-2—Digital General Coverage Payloads

F.3—Specific Mission Payloads—Analog

Presentation
F-4—Technical Analysis {study stage only)

Payloads

© F-1. Payloads— Significant refinements were
made in F-1 payload design during the report period.
Circuitry improvements being tested on an F-1 service
test model at Alrbome Instruments Laboratory indi-
cate a potential increase of approximately 5 db
Pulse width measurement sensitivity.

© F-2 Payloads — Environmental test of the F.2
thermal mockup were conducted in the high altitude
temperature simulator early in April. Preliminary
analysis of the test results indicate that the use. of
surface coatings will provide the required thermal
control for all orbital conditions,

Ground Support Equipment

© Installation of the F-1 data conversion equip-
ment at the Satellite Test Center was completed
ahead of schedule. This equipment converts the F-1
Payload digital data for dato Processing. Checkout
‘and preliminary system testing will start soon.

. ee ee

Communications and Control Equipment

© The first of the three AN/GPS-TIA calibration
vans was received at LMSD on 8 April. These vans
will be used to transmit calibrated signals to F-1 ond
initial F:2 payloads in orbit. The first van will be used
for crew training ond will then be transported to its
assigned station along U.S. Highway 30. Vans 2 and
3 will be placed at 400 mile intervals along this
highway. These vans are scheduled to be delivered
during May.

© Seventy percent of the UHF ground system
equipment has been delivered to Vandenberg Air
Force Base ond installation has been started. The
majority of angle tracker ranging system and data
tecelving equipment components fincluding the 60-
foot tracking and acquisition antenna) are on the
site. The command transmitter antenna also has
arrived at Vandenberg Air Force Base.

© The shortage of acceptable magnetron tubes for
the narrow band transmitters may result in the substi-
tution of a transmitter manufactured by General
Gectronics Laboratories on early SAMOS flights.
Because of the tight delivery. schedule, installation of
the transmitter will be accomplished at Vandenberg
Air Force Base on early SAMOS vehicles.

© Installation of the first Model 1604 computer
and most of its support equipment in the Satellite
Test Center was accomplished on time. Acceptance
tests, which Include 72 hours of computer operation
using programs and operations with known results,
were completed late in April,

Figure 8, The vacuum test chamber prior to installation ix
the Maite Aucmily Beddingar Poobeteie Seen it



DOWNGRADED, AT 12 YEAR
INTERVALS, NOT. AUTOMATICALLY
i DECLASSIFIED, DOD DIR 5200.10



_ oO: TARO STAOE—X-268 (Allegany Beilistc Lab.) —[———
Threst at alttrude 3150 pounds A
Specific impulve (voc) 250 seconds i
Total impeise 116,400 lba/see : r
- Burning Time 37.3 seconds :
Propellant Solid B
& MCOND STAOL—As10-42 (Aerojet-cenerel) _ | .
- Thrust ot oltitvde 7700 pounds q
Specific impulse (vac) 271 seconds
Total bmpulee (nin) £70,000 the/v0e
Burning time 115 seconds
Propellant Liquid
© FIRST STAGE—THOR RE n
‘Thrvat {s.1.) 151,500 pounds c
Specific impulse (1) 248 seconds
Specific impulse (voe) 287 seconds
Berning time 158 seconds
Propellant Uguid

ay)

Figure 1. TRANSIT 1A three stage Hight sebicle,

TRANSIT 1A lasnched feom Aslansic Missile Range

The TRANSIT Program consists of the flight testing of
four vehicles to place 200-270-pound satellite pay-
loads into circular orbits of 400 to 500 noutical

snyanzine ‘firings. The ARPA Order for TRANSIT 1A was initiated

tcuat-capmive
BATTEAINS ton sotas.

owen SvsvEM sn cana essigns AFBMD esponsibility for Providing the

WrLon Lacine " booster vehicles, integrating payloads to the vehi.

courts ane aca cles, and flight Operations from launch through

(ACIS Ue vee. ime po bari wear attainment of orbit, Including communications to the

. ne HSGL, maanduurree —thessten tracking ond data handling faciiifies. Payload and

tracking fesponsibility has been assigned to the

Figure 2. Cutaway drawing of TRANSIT IA payload (NAV 1), USN Bureau of Ordnance. ipplied Physics Labora-
WDLPM-4 205



“TNESENE

The DISCOVERER Program consists of the design,
development ond flight testing of 29 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-
Raissance satellite. Programs,

ii ee a i)

PROGRAM OBJECTIVES
fa) Flight test of the satellite vehicle airframe, pro-
Bulsion, guidance and control systems, auxiliary
Power supply, and telemetry, tracking and com-
* mand equipment.
(b) Attaining satellite stabilization in orbit.

~ {) Obtaining sateliite internal thermal environment
data,

.

(d) Testing of techniques for Fecovery of a capsule
elected from the orbiting satellite.

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

{f] Conducting bio-medical experiments with mice
and small primates, Including injection into orbit,
Te-entry and recovery.

PROGRAM SUMMARY

Early launches confirmed vehicle flight and satellite
orbit capabilities, 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
tested to obtain support data for more advanced
space systems progroms. DISCOVERER vehides are
launched from Vandenberg Air Force Base, with
overall operational contro! exercised by the Satellite
Test Center, Pato Alto, California.

Tracking and command functions are. performed by
the stations listed inthe Table on Page A-4. A history
of DISCOVERER flight to date is given on page A-5.

vouneSBAE PENTA

@i¢€liola

SECOND STAGE
Weight

Inert

Payload equipmeat

Orbe!

Impulse propellants
Other

TOTAL WEIGHT
Engine Model

Thrwat-lbe., vac.

Spee. Imptec., vac,

Burn time-sec.
THOR sOOstER

Weight—Dry

Fuel

‘Oxidizer (LOX)

GROSS WEIGHT (tba)
Engine

Thrst, tbe, ($.L)
Spec. Imp., sec. (S.L)
ture Time, sec.

1.262 +28 1346
497 a7 915
We 2215 2.216
6525 12,950 12,950
7 5 en
6562 18,676 15722
YUBIHoS  XURI-Bo7 — XUR81-80-9
15,400 15,600 16000
a a 290
120 240 40
Deis Beat
6,930 5,950
33,750 33,790
$4300 $400
109,000 108,000
‘MBS MBS
Block 1 Block 2
452,000 167,900
78 247.8

163


SW3ISAS 3DvdS

systems

DISCOVERER

SAMOS

COMMUNICATIONS
SATELLITE

MIDAS



Installation of ABLE-STAR

Delivered to gantry {above}... vehicle in gantry
being moved to launch pad {above left)... being
lowered into position (bottom left}... mating with
THOR



—CONFIDENTIAL

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

injected into solar orbit on 11 March by the ABLE-4
THOR flight test vehicle, the PIONEER V satellite con-
inves ts record breaking trajectory toward its first
Pass around the sun. On 1 May, the satellite was
6,795,334 statue miles from earth nd was traveling
at a velocity (relative to the earth) of 6,569 miles per
hour. The relative speed will remain fairly constant
for some time, Ail systems were functioning normally
except the sub-commutated vehicle condition. This
Problem is discussed fully in a subsequent paragraph.

Powered Flight Evaluation

“© Anolysis of the powered flight performance of

the ABLE-4 THOR vehicle is nearing completion.
Part | of this report will be published in May. Dis.
¢repancies noted in roll attitude offset during second
stage operation and the angular rates developed
during second stage engine shutdown are being
investigated closely. Although not significant in rela-
ion to ABLE-4 THOR flight performance, these con-
ditions are important in relation to future flights,

Orbital Evaiwation

@ The PIONEER V orbit has been projected through
September 1967, including orbital perterbations from
the earth-moon system, Venus and Jupiter. The satel-
lite will continue to recede from the earth until
December 1960, at which time the distance will be
87 million miles. The Payload will then approach
within 80 million miles of earth (February 1961),
recede to 183 million miles (September 1962), and
return to within 16 million miles of earth (4 Novem-
ber 1965). The eccentricity of the orbit will cause
the second approach to earth (April 1966) to be
15.6 milfion miles, This Pattern will be repeated every
5.8 years. in 1989, the satellite will close to within
2 million mites of earth,

@ Trajectory determinations established by SpaN
Center from tracking data for the first 16 hours after
launch ‘have not required revision. since that time,
due to the abundance of high quatity initial informa.
fion. At present, the position of PIONEER V is accu-
rate within 300 miles and velocity within 1.5 ft./sec.
A later computation is planned which will refine these
‘accuracies to within 20 miles and 0,1 ft./sec., respec-
tively. Distance from earth at that time (20 million
miles} will be known Gccurately to within 0.00001
Percent,

zs CONFIDENTIAL

Telemetry

e On 7 April, the SpoN Center ordered the dis-
charge of payload batteries io the minimum to check
the operation of the automatic undervoltage cutoff
‘equipment. Communications with the satellite were
terminated by inadequate battery voltage, The pay-
load was commanded "ON" a few minutes later to
verify that the cutoff had been caused by under-
voltage. The Occurrence of undervoltage cutoff was
within one minute of the predicted time.

© On 16 April, the Manchester station transmitted
for the first time the payload “ON command at the
lowest information rate (1 bit/sec.). Five hours later
Manchester switched the payload receiver from the
wideband to the narrowband sweep frequency (18 ke
frequency at 40 [ps effective noise bandwidth). The
command Is irrevocable.

e Since the time of launch, only the 5-watt trans-
mitter has been used to send Information to earth.
Reception rates at South Point, Hawaii, and Man-
chester have been dosely monitored in relation to
estabilshing the most desirable time for commanding
the 150-walt transmitter into operation. Late in April,
it was determined that the timing of this event would
be based on the following criteria:

\
1 Distance from earth of 10 million miles, or

2. South Point unable to command satellite bat-
tery discharge twice in succession, or

3. Manchester signal strength less than —155
dbm,

e On 7 May, because of reduced quality of Man-
chester reception at the 1 bit/sec. rate, the 150-watt
transmitter was commanded “ON by the 250-foot
radio telescope. On this date, the satellite was

Figure 6. The 150-watt trantmitter which was turaed on 8
Ue is anticipated thet acrepiable covemanicatenn aa je
oR Rake Maer al

WDLPM-4 205



— RR cope

e A program has been developed to test the struc-
tural design of the solar ‘auxiliary power array. Two
types of tests have been Proposed: static—to subject
the array to torsion and compression loads; and
dynamic—to subject the @rray to vibrational forces.
This program is intended to simulate the orbital con-
ditions which will be experienced by the solar array.

Infrared Scannes Units

Infrared scanner units for the first two MIDAS flights
‘ore being manufactured by Aerojet-Generai Corpo-
tation, and for flights 3, 4, and 5 by Baird-Atamic,

@ Acceptance of the first Baird-Atomic scanner has
been delayed unti! 22 May. The binding of the turret
bearing during low temperature tests in the high
altitude test chamber indicated that a modification
of the bearing was required. The schedule slippage
was caused by the redesign of this bearing. A new
bearing has been delivered to the contractor for
installation in the scanner.

©@ The development of the two Baird-Atomic dis-
play consoles is proceeding on schedule. The first
console is scheduled for delivery on 15 June, the
second will arrive approximately one month later.

Figure 7. The thermomechanical

Mowic, Ine, infrared detector mounted on test
testing in the High Altitude Temperature Sis

equivalent model of the Baid-

WDLPM-4 205



rh | UPPER PAYLOAD *TM
8 PAYLOAD
A. SECOND STAGE—ABLE-STAR (AS10-106) (36- INCH DIAMETER)
ot Thrvst ot alitvde 0090 pounds r
Specitic impulse (vec) 278 seconds PAYLOAD
Total impulse (min) 2:3 X 10° the/s0e SEPERATION PLANE
Berniog time 294 seconds
Ponce lewis PAYLOAD
I . “ SPIN MECHANISM
eainmiienl om _ j—| Equipment
‘Specific impulse (s. 1) 248 seconds ia t “ PS _ COMPARTMENT
H Specific impulse (vac) 287 seconds PROPULSION SYSTEM
Burning time 158 seconds {
Propetiont Liquid > 54.79 DIAMETER
a oon ian GIMBAL ¢
i oe
: STAGE I/IT
et SEPARATION PL ANE
’ napa STAGE I/IL ADAPTER
-Ob0ge) “stace 1
' GUIDANCE COMPARTMENT
1 TRANSIT 18, 2A and 28
1 % 20 INCH DIAMETER
TRANSIT 2A @ 2B ONLY
tof:
Powered Flight Trajectory The Powered flight
Program Objectives trajectory for TRANSITS 1B, 2A and 28 is shown and

1. Provide accurate navigational reference informa-
tion for POLARIS jounches.

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

3. Investigate the refractive effect of the jonosphere
n radio transmissions.

4. Acquire additional geodetic and geographical
data by precision tracking of the orbiting satellite.
Flight Vehicles TRANSIT 1A consisted of three
stages as shown in Figure + TRANSIT 1B, 2A
and 28 are two-sige veliicies as shown in Figure

Launch Plans All vehicies will be launched from
Atlantic Missile Range pad 17A or 178, Launch
azimuth for TRANSITS 1A ond 1B is 44.5 degrees
and for TRANSITS 2A and 2B, 140 degrees.

F2

described in Figure « The sequence of events
from launch through payload ‘separation for TRAN-
SIT 18 is given in Table 1.

Payload Description The spherical payloads are
approximately 36 inches in diameter and weigh
between 200 and 270 pounds. Payload equipment
includes four transmitters. fon frequencies of 54, 108,
162 and 216 megacycles}, two receivers, and a gate
which permits the insertion of date only when the
gate has been opened at a Previously scheduled
time. Power for the first five months will be supplied
by batteries, recharged by solar cells located in a
12-inch band around the sphere. The TRANSIT 1B
Payload will also contain an infrared scanner which
will operate for the first four days of orbit. On TRAN-
SITS 2A and 28 @ 20-inch sphere, mounted on top
of the 36-inch sphere, will contain instrumentation
for studying solar emissions, The payloads will be
spin-stabilized in orbit.



Monthly Progress——MIDAS Program

Flight Test Progress

© Preparations for the second MIDAS flight con-
finued during the month. This flight was rescheduled
from late March to 12 May because of problems with
both the AGENA vehicle and the ATLAS booster.
The diodes in the AGENA flight contro! package
have'been replaced and a special wiring inspection
and servicing was accomplished to improve reli-
ability. The present launch date is indefinite pending
‘© solution of the ATLAS combustion instability prob-
tems.

© _AFBMD has authorized preliminary planning and
design work in support of two additional MIDAS
flights using THOR/AGENA vehicles from the
DISCOVERER program. These flights which would be
scheduled for late this year, are contingent upon
the results of the second MIDAS flight. The pre-
liminary design of required modifications to the
DISCOVERER/AGENA vehicles has been initiated.
These THOR boosted flights would be boosted into
polar orbits from Vandenberg Air Force Base.-The
Payloads would be the “B” prototype Baird-Atomic
scanner, modified for flight purposes, and the

eral scanner No. 3. Ground support
equipment used for flights one and two would be
transferred from the Atlantic Missile Range to Van-
denberg Air Force Base to support these additional
flights. The major objective of the Proposed interim
flights would be to obtain basic payload data for
evaluation and analysis.

@ An investigation is being made of the feasibility
of extending MIDAS operational system capability to
provide worldwide coverage, including detection of
IRBM and Fleet Ballistic Missile launches. The study
will consider the number of additional satellites and
ground stations required to support this expanded
Program. The final report on this study is due in June.

Technical Progress
Second Stage Vehicles

@ Design and fabrication of the AGENA “BY
vehicle for the third MIDAS flight is Proceeding with
completion programmed for 11 July. Because of
longer prelaunch pad time than originally scheduled,
the launch date will probably be delayed from
December to early 1961.

Figure 6. AGENA vebicle for MIDAS fig 2 pre 0
mating with ATLAS booster at AMR Stand 14,


CONFIDENTIAL

FIBERGLAS
ATTACH RING

UPPER WINDOW

REACTION
NOZZLES

i f
iy

min
a ait

ANTENNA A
om Lean
g oo \ oe

ARISEN
Gas

PERISCOPE @ UMBILICAL DOOR

FLOTATION
BAGS ACCESS

‘AF TERBODY

Figure 3. McDonnell shell to be carried on second
ATLAS/MERCURY Hight text,


xh

THOR al sm7s  Mllow.21 "ATLAS Series D
Weight—dry 7,746 6,510 | Weight—wet 15,100
Fuel 30,500 33,695 Fuel 74,900
Oxidizer 68,300 68,190 Oxidizer 172,300
TOTAL WEIGHT 106,546 108,395 | TOTAL WEIGHT 262,300
Thrust-ibs., $.L. 152,000 167,000 | Thrust-bs., $.L.
Spec. Imp.-sec. 246.42 248.3 Boost 356,000
Burn Time—sec. 163.59 148.0 Sustainer 82,100
Spec. bap.-sec. .
: Boost 286
Sustainer 310
vorss AGENA [fT . ~
© Payload weight not included. Engine Model YURSI-Bo-S | XLR81-80-70 | y0R81-Bo-9d
Does include controls, guid.
ance, APU and residual pro- | ©Weight—inert 1,155 1,370 1,400
pellants, Impulse propellants 6,550 13,100 13,100
© Doe not ince THO, OR Pyrotechnics 67 108 108
asec (225 be) Be) or ATLAS | @TOTAL WEIGHT 7,772 14,578 14,608
’ Separation Weight 7,74 14,552 14,582
@ Single restort capability,
Thrusttbe., vac. 15,000 15,000 15,000
@ Duat burn operation, Spec. Imp.-tec., vac. a7 277 290
® _O Allegany Ballistic Laboratory. Burn Time—sec. 120 240@ 2400
Ar Al AJ10-104
“AEROJET-GENERAL 10-42 to-101 PEM ABE staR PABL 248
Weight—wet 1,247.1 847.9 1,297 59.5
Fuel 875.1 869.0 2,247 O 455.5
Oxidizer 2,499.6 2,461.0 6,227 (solid)
TOTAL WEIGHT 4,621.8 4,177.9 9771 D 515
Bumout Weight 1,308.6 944.1 1419 50.5
Thrustlbs., vac. 7,670 7,720 7,900 : 3,100
Spec. Imp.-sec., vac 267 267 278 250.5

DISCOVERER (1 thru 16)......
DISCOVERER (16 thru 21)...
DISCOVERER (21 thru 29}.
COMM, Sara

A-D MIDAS (1 and 2) :
MIDAS (3 and subs). . .



sc of SAMOS system
orbit, When the

is i over the area of
terest the sens:
int ipment

mm range 4 ground receiv.
rate ara a

vead-ont command
processing, ay sand 0

asing agencies, This
continuow: dur-
ing the cy pu the

INFORMATION STORAGE
VISUAL AND FERRET

7 a ind maim ror lo sation thn 4 dete link. Growl slecironcs wil recon.
jensional techniques with automatic - vert the signal image form, capability
Pacisiond ira hee of resolving ob jocts 20. feet i length, ‘

* WDLPM-4 205



Component ond
Subsystem Tests

‘Qualification test setup for ABLE-
STAR component test (above) . . .

Programmer subsystem test (right)...
and vehicle subsystem tests,



PROJECT MERCURY
a eenneisinatetatateahla
NASA Responsibility
Booster-Capsule integration
Capsule
Ground support
Recovery
Modified
Flight 1 Flights New guidance ontennae
| 2-12 Thin skinned tanks
NASA | ; Shifted tank bulkheads
Loboratory Flight Light weight thrust structure
le Copsules Copsule separation mechanism
“i (McDonnell) interface electrical connections
LOX dome protection
Re-eniry Programmer Modified
heating, Range safety destruct time delay
dynamics, |Abort-sensing system.
recovery
Detects dangerous variations
Launch in tank pressures, fuel injector
Pressure, electrical power,
Unmanned non-orbital flights attitude and sustainer hydraulic
thanned ‘and aamenned orbital flights Pressure. Can initiate escape
un
Earth track 33°N/33°S/Lat, (for orbital veavence
flights)
oe oi Wty 28 hour Integrated countdewn—including pilot insertion
Orbit weight 2500 tbs, and capsule countdown. AMR launch Stand 14—
Orbit altitude 105-115 nm, Sa et for pilot and capauie,
GE ground guidance equipment modified to
tomatic if
“tome resi safety equipment with Provide: {a} real tie data, tb] additional discrete
command signals during powered flight,
(a) Bollistic trajectory —108°
{b) Orbital trojectory—072°

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

WDLPMA 205 —CONFIDENTIAL Ks



)
eh

TET

Figure 1. ABLE-3 flight test vebicle
(left) of fowr-stage ABLE-3 vebicle,

being launched from Aslantic Missile Rasge. Dimensional deeving

El


CONFIDENTIAL

Flight tests of the three ABLE-1 vehicles in 1958 con-
firmed the feasibility of using this three stage vehicle
fo launch satellite Poyloads on interploneary 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-4
Projects. In February 1960 NASA authorized the
two-flight ABLE-5 (ATLAS boosted) 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 ‘aver interplanetary dis-
tances. A four stage vehicle was selected consisting
of @ THOR oF ATLAS first stage, an ABLE second
stage, ABL 248 solid propellant third stage and the
satellite vehicle fourth stage. A hydrazine engine
with multi-stort 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
euxillary power equipment was developed with o
Usetul 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 antenna
at the Jodrell Bank Experimental Station, University
of Manchester, Englond. Central contro! and data
computation is accomplished at the Space Naviga-

Figere 2. ABLES third sage and
Ind” (above) wih tol headene fF

extended. Drawing of extresech chi
oe ‘hieved by ABLES Pe peed

E2

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-I01A rocket engine, a third
stage powered by the ABL-248 A3 engine, and a
fourth stage consisting of the payload and an injec-
tion rocket. In addition to carrying 4 highty sophisti-
cated payload, the ABLE-3 flight was used to
demonstrate the validity of the ABLE-4 vehicle ond
component configurations. All phases of the jaunch-
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 os predicted with devia-
tions in cpogee and periges occurring on the more
than nominal side. The Poyload was the most sophis-
ficated to have been placed in orbit by this nation
at the fime and contained provisions for conducting
13 experiments in space environment and propaga-
ton. A wealth of valuable data was obtained from



CONFIDENTIAL

The TIROS Program consists Of one flight from the
Alfantic Missile Range early in 1960. Primary objec-
tives include: {a} To determine the feasibility of using
‘an earth satellite to measure, Fecord, and transmit

+ Synoptic weather conditions; (b} To establish system

Parameters for weather sotellites; (c) To acquire
information on electromagnetic Propagation through
the atmosphere and ecquisition of additional geo-

le, and Providing communications to the tracking

and dato-handiing @gencies from: launch

‘Attainment of orbit. Payload design, fabrication and

testing will be accomplished by the Radio Corpora-

tion of America for NASA. NASA retains cognizance

for operating, tracking, and recording and process-
data,

The three-stage TIROS vehicle (Figure 1) consists of
a THOR Booster, Aerojet-General (A510-42) liquid
Propellant second stage with Bell Telephone Lab-
oratories radio-inertial guidance system, and the
Allegany Ballistics Laboratory solid propelicnt third
stage (248). Design specifications for each of the
three stages are shown on Figure 1

THIRD STAGE—X-248 (Allegany Ballistic Leb.)

iu Threst of oltitude 3150 pounds
Specific impulse (vee) 250 seconds
Totel impulse 116,400 tbe /a0e
Buraing Thee ‘37.5 seconds
Propellant Solid
SECOND STAGE—As10-42 (Asrejet-Generel)
Threat at oltiude 7700 pounds .
Specific impulse (voc) 271 seconds
Total impulae (min) 870,000 Ibe /s0c
Burning time 115 seconds
Propellont Uquid

WDLPM-4 205

Thrust (ah 151,500 pounds
Specific impulse (0.1) 248 seconds
Specific impulse (voc) 287 seconds
Burning thee 158 seconds
Prepaliont Ugeid

(a)

FLIGHT DESCRIPTION

The sequence of events for the
Powered flight from launch at AMR
to injection into orbit is given in
Table 1. The payload will be placed
in @ 380 nautical mite circular orbit
having an inclination angle of
48.67 degrees. Orbital life is ex-
Pected to be five months.

PAYLOAD OBJECTIVES

The 270 pound, cylindrical payload
will be 42 inches in diameter and
17 Inches in height. Payload equip-
ment includes 2 television cam-
eras designed to observe, record
and transmit weather data. Power
sources include sixty 20-volt nickel-
cadmium chemical batteries and
9260 solor cells to techarge the
batteries. The solar cells, installed
in the top and cylindrical side wolls
of the satetiite will furnish an aver-

possible, When the satellite is within radio commuy-.
nications range of a ground station, pictures may be
taken on command and transmitted directly to earth,
When the satellite is beyond radio communication’
fange, camera operation is controlled by a clock
‘ond programming circuits and the images recorded
on magnetic tape for readout during the next pass
Over a ground station. Two beacon transmitters are
installed on the bottom side of the satellite to faciti-
tate tracking.

GROUND suPPORT STATIONS

The Air Force ground station at Koena Point will be
used fo support this Program. Tracking and dota
acquisition will be conducted on 108 mes and com-
mand transmission on 140 mcs. Required modifica-
lions to the TLM and VERLORT radars are in progress.
Use of this support station will result in: (a) minimum
cost by maximum use of existing facilities, (b) mini-
mum equipment modification and Operation effort,
and (c) a satisfactory system configuration with mini-
mum complexity, Use of this facility also will benefit
the SAMOS and MIDAS Programs by attaining an
early buildup of experienced Personnel.

-CONFIDENTIAL

Hl



ENTER ELLIPTICAL ORBIT
PERIGEE OF

COAST ELLIPSE “ 180° coas a.
- ~
\ - ~
AGENA
IST. —_ ;

VERNER. & SEPARATION &

ow

mo on oe”

Figure 2, for fi ced sab : aiitade raference, Also goveras is
Launch-to-orbit traje ights 3 and su requent. Opti- irection by inertial guidance system moniti horizon
mum ATLAS Boor, puided ee are ben sytem. Scanner, Onbita abtitude mainicined by reaction tea and
AGENA ascent (coatt, berm, coast, second burn) provides E45 jets.

. -,

.

4
PROGRAM HISTORY

The MIDAS Program was included in Weapon
System 1171 when WS 1171 was transferred
to the Advanced Research Projects Agency
eorly in 1959. ARPA subsequently separoted
WS 1171 into the DISCOVERER, SAMOS and
MIDAS Programs, with the MIDAS objectives
based on an Infrared reconnaissance system.
The MIDAS {Missile Defense Alarm System)
Program was directed by ARPA Order No.
38, dated 5 November 1958 until transferred
fo the Air Force on 17 November 1959,
‘An ARDC development plan for a ten flight
R&D program hes been approved. This R&D
Program will make possible the achievement
of a reliable operational system by 1963,

Figure 3.
Proposed MIDAS system, Four satellites spaced equidistant in each of
so orthogonal lant at 2000 msm abit, Prova: maximure co
erage of ISSR with minimam anmber of satellites,

C2



WDLPM-4 205

Three-quarter rear view of ABLESTAR vebicle mounted on handling dolly.

Monthly Progress—ABLE-STAR Vehicles

Program Administration

© With the successful flight test of an ABLE-STAR
second stage vehicle on 13 April (TRANSIT 18
fligh}}, the development Program for this vehicle was
completed. Under ARPA Order No. 95, AFBMD was
directed to develop an Upper stage vehicle com-
Patible with THOR, ATLAS or TITAN boosters, and
capable of being modified to accept a solid propel-
lant third stage. Funds of $1,708,000 were provided
in FY 1959. A contract for design, development,
fabrication and test of this vehicle was Issued to
Aerojet-General Corporation on 6 April 1952.

Flight Test Progress

@ The first flight test of the ABLE-STAR vehicle was
achieved within one yeor after issuance of the design
contract. All pre-flight tests and checkout Procedures
were accomplished smoothly and in accordance with
the detailed lounch procedures. No difficulties were
‘encountered during countdown or launch. All ground
support equipment functioned satisfactorily.

© First ignition of the ABLE-STAR’s AJ10-104 pro-
Pulsion system occutred two and one-half minutes
after launch, following burnout of the THOR booster
engine. Operation continued within specified limits
for the programmed Period of just over four minutes.
During this time, Wralectory corrections were made by
the STL space guidance system. This system deter-
mines vehicle position by measuring the doppler fre-
quency shift via the vehicle transponder. Deviations
from the established trajectory were computed and
correction commands transmitted to the vehicle
receiver.

@ At the end of the first burn Period, the engine
was shut-off by signal from the guidance system. At
this time the vehicle had aitoined the programmed.
velocity of approximately 16,500 miles per hour.
During the nineteen minute coust period, the vehicle's
attitude wos oriented into its nominal attitude by
meons of the pneumatic gas jet control system.

© Following the nineteen minute coast petiod, the
ABLE-STAR engine was re-ignited and burned for 13
seconds. Vehicle altitude and second burn duration
were sufficient to infect the TRANSIT 1B payload into


PROJECT MERCURY

in support of
PROJECT MERCURY
NASA HS-36
includes:

Design, engineering studies
Equipment modification
Hardware fabrication
Flight scheduling

Launch support
Trajectory data

Modify boosters for NASA prelim.
inary research ond manned orbital
flight and safety objectives.

Lounch, control and define tralectories

of booster-capsule vehicle up to, and

including, injection into orbit,

Provide fourteen (14)
ATLAS boosters.

Table 2. AFBMD responsibilities in support of PROJECT MERCURY.

Monthly Progress—Project MERCURY

Flight Test Progress

@ The second flight test of an ATLAS/MERCURY
vehicle has been rescheduled by NASA from late in
May to mid-July. The deloy was made necessary
Primarily by capsule delivery problems. Launch will
be made from Atlantic Missile Range Complex 14.
The vehicle will consist of an ATLAS booster modi-
fied for Project Mercury and a McDonnell capsule
shell containing. instrumentation and components fur-
nished by NASA. The flight capsule will be boosted
through a trajectory and released so that re-entry
conditions associated with critical abort requirements
will be simulated. The Proposed trajectory param-

1. Booster-capsule ‘separation at 610,200 feet
altitude.

2. Separation velocity—19,400 ft/sec.

3. Flight path angle—4.7 degrees,

4. Predicted impact—1550 nautical miles down-

1. Measurement of capsule afterbody heating
rates during re-entry.
2. Establish adequacy of capsule re-entry system
and recovery procedures.
3. Determine integrity of capsule structure and
afterbody shingles.
4. Personnel training in MERCURY faunch and
recovery operations,
© The following objectives also have been defined
by NASA for the MERCURY modified ATLAS booster
fumnished by AFBMD:
1. ATLAS capability to effect capsule release
under position, velocity and attitude conditions
defined by guidance equations,

2. Evaluote open-loop performance of abort
sensing and implementation system.

“3. Obtain data on ATLAS missile and ground sys-
fems reliability.

4. Demonstrate suitability of equipment and Pro-
cedures associated with checkout and lunch

range. of ATLAS/MERCURY vehicle.
@ NASA has established the following capsule test 5. Evaluate propellant utilization system perform-
Objectives for the MA-1 flight: ance.

K4

CONFIDENTIAL

WDLPM-4 205



reducing weight, increasing thuet, lengthening

Programs:
buming periods,
improves overall

in short, ony change which

Performance, the use of the vehicle must be

Of use as a satellite or space probe booster.
ore achieved which

terms

using improved

re-evaluated in
As
in

the

odvance

Propulsion,

more durable materials ond

guidance, re-entry; in

more reliable components, new doors
additional space capabilities are made possible.

Ore opened through which

Because of the wide

be

U

=

il
re

°2

Hu

Hey



‘WDLPM-4 205

.

it being prepored for acceptance testing. Delivery
of this unit is scheduled for 6 June.

Vehicle Aerodynaimes

®@ Wind tunnel data obtained at the Amold Engi-
neering Development Center has been used to cor-
rect pressure distributions estimated for the ABLE-5
configuration, This information has been incorporated
into the latest calculations of loads.

Third Stage Vibration Evalvation

®@ Data obtained from fest firings of the ABL
248-A6 engine revealed: vibration characteristics
Consistent with those Previously experienced. As a
result, NASA vibration specifications established for
ABLE-4 THOR will not be altered for the ABLE-5
vehicles.

Payload

@ the final bosic design and general arrangement
layouts ware completed during the month. Design
completion is anticipated for May.

e Progress on all payload and experiment com-
Ponents is essentially on schedule. Fabrication and
testing is underway in several of these creas.

Environmental Testing

e During April, 110 environmental tests were con-
ducted as follows: 86 component parts evaluations,
17 type tests, and 17 RED tests. Tests were performed
on assemblies, components, parts and a simulated
payload. The only failure encountered was struc-
tural damage sustained by a flux gute magnetometer,


8,000,100 miles from the earth. Initial Operation of
the 150-watt transmitter was accomplished Ina
3-stage sequence. At 0500 hours, EDT, the FILA-
MENTS ON command was transmitted which put
Power into a tube filament through a current fieniting
resistor thereby warming the filament for about a
minute. At 1100 hours, the first step was repeated
and the second command transmitted which removed
the current limiting resistor and Permitted full fila.
ment heating for several minutes. The circuit. passed
both. tests successfully. At 0503 hours, 8 May, the
third command was sent which energized the static
converter and the 150-watt transmitter. At 0504.5
hours, Manchester received the first 150-watt trans-
mission from PIONEER V. Manchester is now able to
receive satellite telemetry at the rate of 8 or 64
bits/sec. Hawaii will continue to receive only at the
1 bit/sec. rate. Available Power aboard the satellite

will limit the transmitter Operating time to approxi-
mately 3 minutes every 6 to 8 hours. It is anticipated
that satisfactory communications between Manchester
and PIONEER V can be maintained up to a distance
Of 94 million miles. Neither the static converter nor
the 150-watt transmitter had previously been flight
tested. The critical factor involved. was the ability of
these components to survive in the hard vacuum of
Outer space for nearly two months prior to any opera-
fon. Following the 150-watt transmitter “ON” com-
mand on 8 May, 3 minutes 28 seconds of telemetry
reception provided Manchester with 5059 bits of
information (as compared to the 208 bits previously
received via the 5-watt transmitter).

@ All eight. possible commands have now been
transmitted to PIONEER V. These were accomplished
in the following sequence:

” a
Commend Statlen Date tama)
1. 5:watt transmitter “ON! AMR TT March . - 700
at 64 PPS
2. Third stage-payload Manchester 11 March 10,000
separation
3. 5-watt transmitter ON at Singapore 12 March 147,000
8 PPS
4. S-watt transmitter ON at Hawaii 17 March 972,000
1 PPS
5. Receiver—narrow band Manchester 16 April 4,848,000
“6, Filaments ON Manchester 7 May 7,851,000
7. Filaments ON—full current Manchester 7 May 7,898,000
8. _150-watt transmitter ON Manchester 8 May 8,000,100

‘WDLPM-4 205

~ CONFIDENTIAL By


by long range planning and maximum integration
with other programs. Use of the basic four-sioge,
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 cn economy by permitting tests
Gnd experiments to be conducted on regularly sched-
vied ballistic missile test flights whenever possible
without delaying schedules. Economy in the opera-
Hional phase will be exercised by the use of this low-
cost vehicle as a standard flight test platform to
Perform scientific and military experimental research
in support of all Air Force focilities, RELIABILITY will

Program, at least four flights of the basic SCOUT,
and maximum use of knowledge gained in prior Air
Force baliistic missile flight testing. VERSATILITY will
be achieved by designing a vehicle capable of being
readily adapted fo 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) ballistic
missile trajectories; {d) downward boosted, high-
speed re-eniry profiles, and (e) full orbit to approxi-

Mate ‘maximum of 400 miles with 150 pound pay-
loads,

Program Management—An abbreviated devel-
opment plan, covering the R&D Phase: only, was
@pproved on 9 January 1959. Funds in the amount

viated portion of the program only. A letter was issued
assigning management Fesponsibility to AFMBD, with
‘emphasis on integrating the Program with the scien-
fific and military research experiments conducted on
regularly scheduled ballistic missile flight tests (Piggy-
back Program). in June 1959, Aeronutronic Division
of the Ford Motor Company was chosen through nor-
mal competitive bidding as the Payload, Test, and
Systems Integration Contractor, Arrangements have
been made for the procurement of vehicle compo-
nents and associated support equipment, modified
to meet Program 609A requirements, through NASA,
rather than through the SCOUT Program contractors,
Atlantic Missile Range facilities consisting of launch
complex 18 will be made available to the Air Force
for this program, A Project 609A division has been
established within the 6555th Test Wing (Develop-
ment} at AMR to supply Air Force technicians to par-
ticlpate in the assembly, checkout and launch opera-
ions of the RED phase under the direction of the
Payload and Test Contractor. An all-military opera-
tional capability will be developed from within this
group.



’
: Facility Equipment Flight Funetion

Sateltite A Overall control, convert tracking stations data to obtain a predicted orbit
Test Center ‘ond generate ubsequent ephemerides iswve acquisition data to tracking
Sotions for subsequent passes, Predict recovery area,
Ve AFB @CDEFGHIUK Launch, ascent and orbital tracking, Feception, trajectory meas-
F ondenerg urements including time to ignite ‘cond age -
. Point Mugu RCDEFSHIKL —Atcen tacking and telemetry dato reception, tronunty command to .
_ ignite ond shut down AGENA {via guidance computert,
Telemetry Ship oF Final stage ascent trocking and date reception,
. ne Mano} rectiog ond telemetry
s- Annette Island, Activity at this station terminated ? December 1959 due to fund limitations,
Alaska tracking
stotion)
Cape Chiniak, BDEFGHUK. Orbital tracking and telemetry data reception, including first poss ocquisi-
Aleska (trocking tion, recovery capsule ejection and impoct prediction,
Keeno Point, BCDEFGHIK Orbital tracking and telemetry date feception,
Oahu, Hawaii
(tracking station)
Hickam AFB Over-all direction of Capsule recovery operations,
Ochu, Hawaii
. Reine UNIVAC 1103-4 digital computers 1h Plot boards for radar ond TLM:8 wracking dota
e b. VERLORT (Modified Mod i rodor i ‘cawipment for teletype ronsmitsion of radar,

Conversion seus
. TUM-18 ond doppler rocking dato in binary format
© TUMIE cell-tracking telemetering ontenna eh bs °
@. Wichelin ie Zccuitton programmer for pre-ocquistion direction of
©. Doppler range detection equipment . k Ground command to sotelive ranemission equipment
1. Telemotry tope recording equipment |. Guidonce computer
& Telemetry decommutators for real time doto presentation

GROUND suPPorRrT FACILITIES |

“y

{pn
WT

- oes i



WDLPM-4 205

K

ithe middle and Soaih Adastra e ree oI ”
cease ‘in she a

Tight is tbe Gulf of Se, Lara oo ihe Tas die sb

Se om the sarfce wasiber map indicates the goograpbie portion of

TIROS when the phesogrepbs wore tehea.

“CONFIDENTIAL

Figare 2, A series of three Pnetebhs taken met, TIROS on its third :

HS


@ successful orbit, This significant milestone marked
the first time that an upper stage vehicle had demon-
strated the restart capability. Alf phrases of the restart
Operation were accomplished successfully and the
Performance achieved was excellent/in relation’ to
Programmed times and specifications. This flight also
wos the first in which compelte control of the attitude
and direction of a second stage space vehicle was
maintained throughout its flight.

©@ At the present time, the ABLE-STAR vehicle is
Programmed for additional flight testing on TRANSIT
2A and 28 and on COURIER TA and 18.

Summary of ABLE-STAR
Development Program

@ The ABLE-STAR vehicle JAJ10-104 Propulsion
System} is a refined version of the earlier ABLE
vehicles and Aerojet-General Corporation propulsion
systems (AJ10-42 and AJ1O-101). Design objectives
included: increased payload. weight and vehicle
range capability by providing two-and-one-half
times the propellant capacity and an engine restart
capability; ond providing positive vehicle contro!
during powered flight and coast periods through
pitch, yaw and roll control iets. In addition, two
longitudinal acceleration ists were added to settle
the fuel in the tanks prior fo re-ignition of the engine.
Design specifications for the ABLE-STAR are shown
in Table 1.

@ Throughout the ABLE-STAR Development Pro-
gram, the guiding philosophy included minimum
redesign, over-all simplification and maximum use of
flight-proven components to maintain the high level
of reliability established by previous ABLE vehicles;
and to accomplish these objectives within a minimum
‘amount of time.

© Following contract initiation in April 1959,
design studies and ‘preliminary manufacturing efforts
Proceeded at a sufficiently satisfactory rate to per-
mit simulated high altitude tests of the AJ10-104
thrust chamber. to: be performed in September.
Objectives of this test program, conducted at the
Arnold Engineering Development Center, included:

1. Determine. the. firing life of the aluminum and
steel thrust chambers.

2. Obtain dato for propeliant loading and flow
balancing of the propulsion system.

i —CONFIDENTIAL

3. Determine accurate chamber. performance data
by actual thrust coefficients demonstrated in
tests.

4. Evaluate thrust. chamber starting, restarting and
shutdown transients for steady state and coast
Phase operations.

@ © During November, operational test runs to full
duration (300 seconds} were started. Injector cooling
problems associated with injector manifold design
end the use of inhibited fuming nitric acid os a
coolant, resulted in burn through of the injector plate
‘and cooling tubes. These Problems were solved and
two full duration. tests were completed during the
month, Also in November, the first flight test engine
Passed Air Force acceptance testing ond the pre-
liminary flight rating test ‘engine was delivered to
the Air Force,

@ in Janvary 1960, all Preliminary flight rating
tests for this propulsion system were compieted suc-
cessfully. A total of seven full duration firings were
made with four thrust chamber assemblies accumu-
lating approximately 700 seconds of hot firing time.
The first flight article Propulsion system was deliy-
‘ered to the Air Force in mid-Janvary. The remaining
four systems were delivered in February, March,
April and May.

PERFORMANCE
Total impulse 2,300,000 Ib-sec.
Thrust 7,890 Ib.
Specific impulse 278 Ib-sec/Ib.
Chamber pressure 206 + 6 psia
Nozzle throat area 21.64 sq. in,
Nozzle arec ratio 40:1
Propeliant flow rate 28.36 Ib/sec.
WEIGHT
Dry weight 1040.7 Ib.
Total propellant capacity 8474.3 Ib.
Nitrogen, helium, etc. 201.2 Ib.
TOTAL 9716.2 Ib,
DIMENSIONS
‘Overall length 177.68 in,
Diameter, propellant tanks 54.8 in.
Diameter, separation plane 63.6 in.

TABLE 1. ABLE-STAR (AJ10-104)
SPECIFICATIONS

WDLPM-4 205


Monthly Progress-—DISCOVERER Program
Hight Test Progress

© DISCOVERER Xt wes. launched from Pad 5,
Vandenberg Air Force Base, at 1230 hours, PST, on
15 April. No technical holds were encountered during
the countdown. Terminal countdown time was only
12 minutes, 45 seconds. Significant events occurred
as follows:

1. Liftoff was normal and boost trajectory was
nominal.

2. Second stage separation occurred at T plus
186 seconds.

3. Trajectory during the coast period was slightly
below normal dictating early AGENA engine
ignition.

4, AGENA performance was very close to nom-
inal,

wo

. Orbital status of the vehicle was indicated by
ascent radar tracking.

@ The resulting orbit has o perigee of 109.5
statute miles, an apogee of 380 statute miles, an
eccentricity of .033 and an orbital period of 92.3
minutes.

© Acquisition was accomplished by every station
‘on every. pass. All fifteen commands were received
and verified. The horizon scanner, inertial reference
package, and gas jet control system functioned
extremely well, resulting in excellent satellite attitude
stabilization. The satellite power supply, including
the two advanced design static inverters, performed
efficienty. The main batteries lasted through the 26th
orbit,

© DISCOVERER XI was the first orbiting AGENA
fo carry the dual-frequency doppler beacon (APL)
used in the TRANSIT Program. This vehicle also car-
tied four optical tracking lights which were visible at
night as a seventh-magnitude star. These lights were
photographed by cameras at a Smithsonian Astro-
physical Observatory station providing the most
Precise satellite tracking data ever obtained. Both
frequencies of the doppler beacon Operated and
were tracked during all passes. Sufficient data were
received to determine the accuracy of the TRANSIT
beacon and the DISCOVERER verlort radar stations
by comparison with precise optical data.

© Telemetry data indicate that the recovery cap-
sule was ejected on the 17th orbit as planned. A

* good track of the recovery capsule telemetry trans-

mitter was obtained by the Kaena Point station, show-
ing a high re-entry trajectory beyond the capability
of the recovery forces. Analysis of all available data
is being conducted to determine the couse of this
high trajectory out of orbit,

@ Four AGENA “B" vehicles have been added to
the DISCOVERER Program. These additional vehicles
bring the DISCOVERER/AGENA “8” total fo sixteen.

Technical Progress
Second Stage Vehicles

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

Piper 1 i ;
ee OMe el bist viatan es” “etme

“ CEP rpm


HEADQUARTERS

. AIR FORCE BALLISTIC MISSILE DIVISION (ARDC)
UNITED STATES AIR FORCE

Air Force Unit Post Office, Los Angeles 45, California

iN
i WDLPM-4 30 April 1960
FOREWORD

Activities summarized in this report include the major space systems, proj-
| ects and studies for which the Air Force Ballistic Missile Division is wholly

This month's report includes detailed follow-up information on the accom.
Plishments of DISCOVERER XI, TRANSIT 1B, TIROS and ABLE-4 THOR

. The development of the Able-Stor stage, as authorized by ARPA, has
been completed. Also completed recently is the AGENA modification

| Program authorized by ARPA.
.

RSG

©. J, RITLAND
‘ Maj. Gen., USAF
"Commander



SPACE

~—d . —]

ne aden ER ; ene Re |

|

—d

SL1D3fO¥d IDS

projects

Tt"

|

g
gz

ABLE-STAR

MERCURY

609A



gy _ ,

Faciities

@ Vandenberg Air Force Bose—Completion of the
technical supporting building is scheduled for
October. Completion of the SAMOS laboratory bulld-
ing is scheduled for July. Construction of the data
acquisifion and processing building is complete and

‘installation of equipment is in progress. Design of a

data acquisition and processing building modifice-
tion fo permit installation of a new computer has
been completed. Bids for construction have been

advertised with completion scheduled for July. The -

last two consoles for checkout complex 2A in the
Missile Assembly Building were delivered on 26 April.
© Offutt Air Force Base—A construction contract
has been awarded for the construction of the interim

data processing facility. Notice to proceed has been
deferred by request of the Under Secretary of the
Air Force.

© Point Arguello—instailation of the leunch contro!
equipment for pad 1 is nearing completion. All
ground handling and service equipment for both
pads has been delivered to the launch site and
installation of the equipment at pad 1 is essentially
complete. Acceptance testing of the launch monitor-
ing contro! equipment for pad 2 was completed on
25 April at LMSD. Final acceptance of launch pad 2
is scheduled tor May. The beneficial occupancy date
for the technical support building is now scheduled
for August.



@ foreword fo...

SPACE

WDAT 60-2098



Flight Time Inertial Speed Downrange Altitude
Point (seconds) Comments (ft/sec) Distance (n.m) (amd
2A it vehi “18 2A 18 2A 1A 2A
18 28 Transit vehicles 28 28 28
1 0 10 End of vertical rise 1,346 1,346 a 0 0.077 0.077
2 167 167 First stage burnout 13,611 12,929 752 797 a2 a3
End of second stage
3 M2 448 first burning period 24,539 24,376 785.6 778.0 = 200.1 203.0
4 148917 kenert second st09¢ 24s 253942032 4080.0 © 5000 © 500.0
5 1,504 1462 __ Injection into orbit —24,258-—=—«24259 «4 A1G~—ANGOD 500.0 500.0
FLIGHT TRAJECTORY —TRaNsit 18, 2A ond 28
sae epee .

Orbital Performance Achievement of program
objectives is based Primarily on measuring the
doppler shift of sotellite franseitted 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 two satellites. After four
months of tracking the satellite by measuring the
doppler shitt 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 ond aircraft con 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 Atlantic Missile Range. A
mobile tracking and telemetry van will be located in
Germany for TRANSIT 1B and South America for
TRANSITS 2A and 28. These locations were selected
© the closest sites possible to the orbit injection
point.

F3



Management respontibility for the microwave com-
~ taunications subsystem as directed by ARPA Order
* 54, .

. ing the program objectives 'in three progressively.

The Communications Satellite Program will investi-

gate the feasibility of using synchronously spaced |
satellites as instantaneous repeaters for radio com-
munications. Under ARPA Order No. 54, as
‘amended, AFBMD is responsible for the design,
‘development, and fiight 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

The Communications Satellite Program is currently
being conducted in accordance with amendment 5,
‘(dated 11 Aprit 1960) to ARPA Order No. 54. Under
this amendment the previous method of accomplish-’

Figure 1. Proposed sallite with jettisonable

fairing mounted on AGENA second sage, .

Communications

JETTISONABLE.
NOSE FAIRING
}-— PAYLOAD MAXIMUM
ENVELOPE
‘
cA
.
\ |_--SOLAR PADDLE
1 sO
i
ra

a AGENA STAGE



‘WDLPM-4 205

—CONFIDENTIAE

Program Vehicle (see figure 5)

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

Second Stage—ABLE vehicle with Acrojet-General
AJ10-101A 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 Vehiclel]—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 cell paddles, 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

5. Final burnout is programmed to occur 23,290,000

feet 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
Periune ...... 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 50Key per
Particle} and proton energy (greater than 1.0Mev
er particle), -.

fon Chamber and Geiger-Muiler Tube—flux and
fate data for electron particles (greater than 1.25
Mev per particle) and proton particles (greater than
25 Mev per particie).

Proportional Counter Experiment—measure inte-
Grated Intensity of cosmic ray Particles: electrons
{greater than 12 Mev per particle) and Portons
(greater than 70 Mev per particle).

Spin Search Coil 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 Coil ond Flux Gate inputs to deter-

mine magnetic field direction relative to inertial
space.

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

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

Plasma Probes Experiment—mecsure the energy
and momentum of streams of protons having energies
of the order of a few kilovolts per particle.

Ground Support Program

Atlantic Missile Range—track vehicle for first 14
hours after launch (excep! 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. vernier corrections os 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 thé SPAN center at

Los Angeles.

"CONFIDENTIAL rs



Figure 4,
biting satellites detect infrared radiations

or
emit
Data

Soviet ICBM’s in powered flight.
phonon instantaneously to alias
via far north readout stations.

Decoded date reveals ap iximately the nam- f

WDLPM-4

and launch location,
burning characteris:

TECHNICAL HISTORY

The MIDAS infrared reconnatssance payload
is engineered to use a standard launch
vehicle configuration, This consists of a “p"
Series ATLAS missile as the first stage and the
AGENA vehicle, powered by a Bell Aircraft
rocket engine as the second, orbiting stage
{Figure 1}. The total payload weight is
@pproximately 1,000 pounds.

205

The first two of the ten R&D flights will use
the AGENA "A" vehicle which is programmed
to place the payload in « circular 261 nauli-
cal mile orbit, Subsequent fights will utilize
the ATLAS/AGENA “B" configuration which
will be programmed to ploce the payload in
@ circular 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 additional objective of this program is
the development of a controlled re-entry and recov-

ety capability for the Payload capsule (Figure 4).

An Impact area has been established near -the
Hawaiian islands, and a recovery force activated.
Techniques have been developed for aerial recovery
by C-119 oireratt and for sea recovery by Navy
surface vessels, The recovery Phase of the program
has provided advances in re-entry vehicle fechnol-

gy. 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 fight test vehicles used in the
DISCOVERER Program are defined in the launch
schedule shown on page A-5, Specifications for the
fwo THOR configurations and three AGENA configu-
rations used are given on page A-1.

AGENA VEHICLE DEVELOPMENT

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

£><

LINES OF SIGHT— HORIZON SENSING.

NOSE CONE

aaena "4"

LM

gas jet system for orbital attitude control, An urgent
need for attaining higher altitude orbits resulted in
development of the AGENA "B” versions which
included doubling the propellant capacity and eddi-
tion of engine restart and extended burn capabilities.
The YLR81-Ba-5 version of the LR81-Ba-5 engine,
developed by Bell Aircraft for B-58 aircraft, is used
on AGENA “A vehicles.

Early AGENA “'B” vehicles will use a later version of
this engine (YLR81-Ba-7), redesigned to use
unsymmetrical dimethyl hydrazine fuel instead of
JP-4. The majority of AGENA “B" vehicles will use
the XLRB1-Ba-9 engine, incorporating a nozzle
explansion ration of 45:1, and Providing a further
increase in performance capability.

LAGE ROCKETS
(Von)



‘CONFIDENTIAL

Project MERCURY represents the transitional threshold viding 14 ATLAS boosters modified in accordance
between this nation’s cumulative achievements in space with program objectives and pilot safety factors, and
research 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 reiponsibilities for this program is given
effect 0 controlled fe-entry and successful recovery in Table 1. Specific details of AFBMD support are given
of the man and capsule (Figure 1). Unmanned (CBM . in Table 2,
trajectory and near-orbital flights, and unmanned .
orbiting flights will be used to vorify the effectiveness ‘Major contractors Participating in the AFBMD portion
and 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 efigineering and technical direction;
be conducted over a period of Nearly two years. The Convair-Astronautics,. modified ATLAS boosters;
initial R&D flight test wos 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: (e) pro- meeting Project MERCURY requirements.
ee en —
LEGEND — —— ©
RESPONSIBILITY: :
AFEMD =

NASA

t /
ESCAPE | y
ROCKET / ’
I / .
CAPSULE / Y ; ha
! J @) BALLISTIC TRAvECTORY
artas oy TO SIMULATE REENTRY CONDITIONS
BOOSTER i 4 NEAR ORBITAL INSERTION, IMMEDIATE
if REORIENTATION, DECELERATION, REENTRY
Wa ATLANTIC RECOVERY
i ;

FULL ORBIT 3-18 orsiTs (05-115 N.M.
© WEST COAST REENTRY ATLANTIC RECOVERY
Figure 2, Visgbs test wayectories tor Project MERCURY, depming speciic Objectives. Trajectory C

sebrctentt the path of the final (manned) fight. The poiat at wbich AFEMD end Nth i

m2 CONFIDENTIAL WDLPM-4 205



Time
(sec) Stage : Event (sec) Stage Event
xF00 1 _Litoff switch activates X +2300 tt lettin nove Fairing

Programmer starts Times vary in It Stop pitch Program

Gyros uncaged accord. with Pitch command

1) Umbilicals eject trajectory, —- Yaw command

Arm destruct initiator X— 4279.0 Il Stop pitch program
x42 |__ Roll program initiated X45 Engine cutoff signal
X+9 | Roll program complete Switch Pneumatic coast control
x10 Fitch program initiated Syem on pitch, yaw and roll

Ist step pitch rate As required X— 471.0 {Tum off hydraulic power
x+25 | “2nd step pitch rote for trajectory X= 40.0 lt _eitiote coast Phove pitch program
x+70 | Std sep pitch rote ond detailed in 710568 I_ Stop coos phase pitch program
X+9 1 “Gh sep pitch rate DTO 2a TEN Stet hrceouis power

Autopilot gain change X— 1488.6 1 _ Engine restart fire signal

Programmer armed Uncage accelerometer

x4 130 |_ Pitch program complete X— 18916 Cage coast pneumatic control system
x4 152 | Main engine cutoff (ECO) X— 1500 Whe TPS cat probe fback-vp)

Circuitry armed Arm oxidizer probe (bock-vp)
X+1835 1 MECO backup ormed Arn spin ond separation mechanism
x4 180 1. MECO X — 1504.0 Engine cut-off signal
X+1670 Start programmer Uncage coast pneumatic control system
XF1700 _W Engine fire signal Start spin table

Gamage in combo Start timer on spin table

in pitch and yaw X= 15060 i Engine cutoff fbock-up)

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

Uncoge gyros X= 1507.0 W__ Remove spin table bolt power
X+17085 "| Blow séporation bolts X= 15260 ll Blow separation bolts
X + 176.0 Wl Start pitch program * Activate separation actuators

F4

Sequence of Events—TRANSIT 18, 2A and 2B

Se

Payload separation occurs

-CONABENTHAL
az wou



‘WDLPM-4 205

“CONFIDENTIAL

The ARPA COURIER Program consists of two flight
vehicles to be launched from the Atlantic Missile
Range. The program objective is to test delayed
repeater communications between a satellite and
Ground stations, The program also will be used to
determine the Operating characteristics and capa-
bilities of the ABLE-STAR {AJ10-104) second stage
vehicle. The program is being conducted under ARPA
Order No. 98, dated 1 July 1959 (Project Code No.
2200). AFBMD responsibility includes development
of the lounch vehicle, payload integration, launch,
injection of payload into orbit, and verification of
orbital parameters at Injection. The Army Signal
Research and Development Laboratory will design,
develop and fabricate the payload, and will be re-
sponsible for workd-wide ground station requirements.
Primary payload contractor is Philco ie
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 a gyro platform
and a programmer. The second stage is controlled by
‘© gyro used to govern engine gimballing during pow-
ered flight. Stability 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 capability. The 500 pound COURIER
Payload is a 60-inch sphere, containing radio repeot-
€rs, storage and memory equipment, and a battery
Power source,

Flight Description—Both vehicles are to be launched
from the Atlantic Missile Range. After first stage burn-
out, the ABLE-STAR vehicle will place the payload into
the desired trajectory and then shut down. The second
stage and payload will coast to the desired 650 nav-
tical 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 three ground stations; as well as exchang-
ing “real time” information when the satellite is within
line-of-sight of two ground stations. During these peri-
ods a ground station can relay messages direct to the
Rext ground station, through the satellite simplex
repeaier equipment.

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

79.3"

60°

[= J [=] Je Jo [a]

‘SECOND STAGI—ABLE-STAR (AJT0-106)

Thewst at attitude 9090 pounds
Specific impulse ivoc} 270 seconds
Total impuise (sin) 23 X 10° the/rec
Qerning time 294 seconds
Propellant quid

FIRST STAOE—THOR mem

‘Thrast {. 1) 151,500 pounds

Specific mpuise (3. 1) 248 seconds
‘Specific imputee (vec) 207 seconds
Burning time 138 seconds
Propeliaa Uquid

“CONFIDENTIAL o


A. THOR—SM-75 / AGENA "A"

8. THOR—DM-21 / AGENA “B”

C. THOR—DM-21 / AGENA "8"

~ MB-3 Block 1 / XLRB1-Ba-7 MB-3 Block 2/ XLR81-Ba-9
Flight History: — —
DISCOVERER AQENA THOR
Ne Ne. No. Flight Date Remorks
) 1019 160 21 Je AGENA de: by malfanction .
muery GON scerkibod fora on igo
_ J 1022 163 28 Feb 1959 Gacinad orbit sucessfully, Temetry received for 514 seconds after
w 1018 170 3 a ined orbit 2 je 78h orbit
“en st tensor cine cet rtovey ceded hire.
~ mm 1020 174 34 Launch, ion, coast and orbital boos ful. Failed
“ne to ahlore By vinood of tow performance A ii engine.
Vv 1023 179 25 June Same as DISCOVERER Ill.
~ v 1029 192 13 August is achieved ale
9 4a ghiectives 5 eccesstlly excapt capsule recovery after
vi 1028 200 19 August Same as DISCOVERER V.
~ vil 1051 206 7 November orbit y. Lack
fii orbit snccenssily ; of 400-cycle: power prevented ste-
viit 1050 212 20 November Attained orbit successfully, prevented AGENA engi:
_ Sherdowe ai dasived orbital selociy. Recovery eapinle ejeciad bat
mot recovered,
Xx 1052 218 4 Febrvas THOR shut down prematurely. Umbilical cord mass did not retract.
7 Quick disconnect failed, canting loss of ‘belinw presiere,
7 x 1054 223 19 February THOR destroyed at T pins 36 sec. by Range Safety Officer.
xt 1055 234 15 April

Attained orbit z nsle eje 17th orbit
nes saceesefaly Pisaisid capsule ejected on 17th orbit

hives
wag not ‘except recovery successfully

AS