Flight History

Did orbit because failewe
ATLAS/AGENA opeatonn f * tale daving

1008

290

26 February

Performance with

Highly successful,

1007

45D

24 May

date

i

DISCOVERER Vehicle

20 December

RM-1

f

anu HI]

A

4 la
le H a ty

HOY if iy

te

altel ; 4]
nil

ae

1201

DISCOVERER Vehicle
97D

18 February
12 July

RM-2
iT

SSLPR-20


—SEERET—

Monthly Progress — SAINT
Program Administration

© The fourth Management Meeting was held on
13 July. The current configuration and design status
of the Final Stage Vehicle was reviewed. Tests will
be conducted to determine the seriousness of pro-
Pulsion heat and exhaust deposits on the Final Stage
Vehicle optical sensors. The Radio Corporation of
America will evaluate the impact of Proposed de-
sign changes on the FSV system's functional capa-
bility and reliabitity. {5}

¢ Proposals for the SAINT target were received
from prospective contractors on 14 July. The SAINT
Target Evaluation Board convened on 17 July to
choose the contractor who will design and fabricate
the SAINT target. Selection of a contractor was post-
Poned pending receipt of additional cost data re-
quested from the participating contractors. (U)

* SAINT Program Office personnel attended a
coordination meeting at the Arnold Engineering
Development Center on 12 July. Discussions were

SSLPR-20

telctive to the use of the AEDC altitude chamber
for testing the main Propulsion unit. Use of the
facility has been requested and approval is pend-
ing. {U)

¢ The Final Stage Vehicle contractor (RCA) has
established subcontracts with Emerson-Electric Com-
Pany for the range and illumination radar. AVCO.
Corporation has been selected to design and fobri-
cate the FSV structure. The Garrett Corporation was
chosen to design and fabricate the temperature
contro! unit. Douglas Aircraft Company will design
and fabricote the Final Stage Vehicle ascent fair-
ing. {C}

© Air Force Missile Test Center support require-
ments for the flight test phase cre being finalized
for inclusion in the SAINT Program Requirements
Document due in September. Detailed launch com-
plex facilities requirements for the Final Stage Ve-
hicle and its ground environment were submitted to
General Dynamics-Astronautics in July for inclusion
in the integrated facility design criteria for modifi-
cations to Aifantic Missile Range Complex.13. _(U)

—SECGRET- Bs



:
5

ee

1, SAINT vebicle copfigwre.

ej p. Propoted Final

Visi on cee engine wossle,
jas

storage spheres, and atti.

Fi
Ve

The SAINT (Satellite Inspector System for Space
Defense) Program has been established to develop
and demonstrate feasibility of a co-orbital satellite
inspector system capable of rendezvousing with

and inspecting suspected hostile satellites and
assessing their mission,

, Program Objectives

1. Design, fabricate, and demonstrate feasibility
of a prototype vehicle capable of co-orbital ren-
dezvous with another satellite at 400 nautical

- miles with a capability of inspecting and identifying

the unknown satellite.

2. Study and define a SAINT vehicle which could
be used as an ultimate defense vehicle having a

capability of rendezvous up to 4,000 nautical miles
with necessary orbit changes,

3. Develop ond fabricate those long lead type

duding a capability of negating hostile systems,

—SECRET—

El



The ADVENT Program wilt investigate the feasibility
of using satellites in synchronous orbit as instantene-
ous repeaters for microwave radio communications.
A satellite vehicle station in synchronous equatorial

orbit will remain in a fixed position relative to any .

polit on the surface of the earth. Active communica-
tions equipment contained in this satellite will receive,
amplify and instantaneously retransmit any message
beamed in Its direction.

PROGRAM HISTORY

The Research and Development program for active
communication satellites was initiated by ARPA in
January 1959, Following early research and develop-
ment, a three-phased development program (STEER,
TACKLE and DECREE} was initiated In May 1959 by
Amendment No. I fo ARPA Order No. 54. Phase 1
{STEER} was given Priority in order to demonstrate
the feasibility of Providing an early UHF communica-
tions capability for Positive contro! of the SAC strike
forces. Space Systems Division (SSD) was given re-
sponsibility for the design, development, and flight
testing of the complete system, including launch,
satellite tracking and control, and Necessary support
facilities and ground equipment. Aeronautical Sys-
tems Division (ASD) and the U.S. Army Signal Re-
search and Development Laboratory (USASRDL) were
delegated responsibility for the development of the
cemmunications subsystem for Phase | and Phases II
and II], respectively,

Figure 1. Proposed: satellite with
i

touable fairing mounted
Generate woud aaggnee om

Temperature
Control Louvers

Temperature
Shroud

ssuan SEGRET-

Gl



—SEGRET—

DISCOVERER XXVI CAPSULE RECOVERY



-SECRET-
~ Been BOOSTERS

@ The primary Pacing factor in the accom.

Plishment of space missions has been, and for
some time will continue to be, the ‘availability
of Air Force ballistic missiles ond upper stages
to boost the payload vehicle. Space flight
planning requires close examination of all
technological areas wherein advances provide

dictable space research.

° Because of the, wide range of its activities,

The Air Force Space Systems Division has

accumulated a broad base of experience in

booster. selection for space missions. Expe-

rience in ballistic missile R&D Programs and

in development of upper stage vehicles have
a provided much information. Research Programs
in the propellant and materials areas also are
Providing new capability for space research,
The number and variety of boosters available
Permit the selection of o combination of stages
tailored: to provide specific capabilities for
specitic missions,

‘comparisons of vehicle capabilities. Specitic
qualifications ore made where necessary for
clarity, ;

oN, Mie

N-1



Figure 1. Mockup, opposite poge,
of the two-stage TITAN If booster
which will be used te boost the
DYNA SOAR glider. The pitch fin
projects toward the right. The first
stage motors are shown above and
the second stage motor with its

SSLPRID —ECONFIDENTIAL



CONFIDENTIAL

site. The capability of DYNA SOAR type systems to
perform these programmed missions appears attrac-
tive as a result of studies made to date. The missions
under study are: reconnaissance (manned and un-
manned}; air and space defense; strategic bombard-
ment and logistics support. Manned and unmanned
versions are being considered where applicable.

Flight Program — Step I includes twenty air-
launched, manned flights with the glider being
dropped from a B-52. Sixteen booster-launched
flights will follow; flights 1 and 2 are designated as
vamanned flights. If alt significant flight objectives
are achieved, the third flight will be manned. Flights
3 and 4 hove been Programmed as backup flights
in the event that flights 1 and/or 2 do not achieve
Program objectives. The frequency is five launches
at two-month intervals and eleven launches at six.
week intervals. The range from Wendover AFB,
Utah, to Edwards AFB is adequately instrimented
for the tracking and telemetry required during the
Gir-launched tests of the DYNA SOAR glider. in-
strumentation sites for the AMR launches will be
located at Cape Canaveral, San Salvador, Mayo-
guana, Antigua, Santa Lucid, and Fortaleza. In
strumentation, tracking, and recovery ships will be
provided to supply additional support for the AMR
launches. Landing facilities will be provided at
Fortaleza, Brazil; Santa Lucia, Lesser Antilles; and
Mayaguana, Bahama islands.

Program Responsibilities — Steps | and ll of the
DYNA SOAR Program ara to be conducted by the
USAF with NASA participation. USAF will provide
Program management and technical direction, with
ASD having responsibility for over-all system man-
agement,

SSD is responsible for the booster, and its Aerospace
Ground Equipment (AGE), special airborne systems,
and booster requirements of the launch complex.
ASD will have responsibility for glider, glider AGE,
and subsystem development. NASA will provide
technical support in the design and operation of
the glider in obtaining basic aeronautical and space
design information.

Technical Approach — Space Systems Division
technical approach to meet the objectives of the
Program are:

1. Modifying a TITAN Ii ICBM. by adding stabiliz-
ing fins; strengthening the holddown and skirt area,
intertank ond interstage sections; redesigning the
guidance bay; incorporating a malfunction detec-
lion system.

2. Modifying the XLR 87-AJ-5 and XLR PI-AS-S
rocket engines to obtain structural compatibility with
the modified booster; include malfunction detection
system shutdown and fail safe systems,

3. Modification of an AMR launch pad.
4. Provide an integrated launch countdown,



~CONFIDENTIAL |

t Launch Schedule

| Eat

Flight History, ———_—

MERCURY
Right Launch Date ATLAS No. Remarks |

ouno-=—

_

Big Joe! . 9 September 10D Flight test objectives were achieved to
such a bigh degree thet « second, simi-
lar flight was cancelled. The capsule
was recovered intact.

MAel 29 July 50D After ome minute of normal flight r

oow—

t buidence, rate, track lock, and telem-
. etry were lost and the vebicle was
destroyed. The exact cause of the mal-
function bas not been determined. |

MA-2 21 February 67D Test enalyses have been completed and
all booster and capsule test objectives
were achieved.

25 April 100D Vebicle destroyed after 43 seconds of
flight by the Range Safety Officer.
- Programmed pitch end roll fusctions
failed to occur and Renge Safety cri-
teria were violated, Investigations to
determine the cause of programmer
failure have resulted in changes to the
autopilot system of the MA-4 and sub.
sequent boosters,

ra

E

NoOo~

wno—

He Successful flight

@ Unsuccessful flight

CONFIDENTIAL

N
0
J
nN
s
0
nN
0
”
F
“
a
M
a
’
a
8
0
N
D
J
F
M
A
M
d
J
A
3
0
N
0
”
F
M
A
Mu
v
Jv
A
8
°
N
D



CONFIDENTIAL—

TOPSIDE SOUNDER SATELLITE MISSION (S-27)

The primary objective of the S-27 Satellite is the
examination of the structure of the ionosphere from
above in a manner similar to that now being done
by ground-based ionospheric sounders. In particular
the objective ‘is to obtain information about the
ionosphere in the tegion above the F layer maxi-
mum, Other objectives are to measure the cosmic
noise level and determine the plasma frequency at
the altitude of the satellite,

The Topside Sounder {S-27) will be launched on
board « THOR/AGENA “B” booster system from
Vandenberg Air Force Base into a 540 n.m. circular
orbit, This will be the first Pacific Missile Range
launch in this program; however, it will be similar
fo previous Air Force THOR/AGENA B launches from
Vandenberg Air Force Base.

The THOR/AGENA “8 booster system will be com-
Posed of the standard DM-21 THOR booster with
Bell Telephone Laboratory guidance systems and
AGENA "8" second stage similar to the one used

SSLPR-20

in the RANGER launches from Atlantic Missile Range.
Minor modifications will be made to the AGENA to
make it compatible to the mission; howeyer, maxi-
mum use will be made of the experience developed
in the RANGER Program.

COMMUNICATION SATELLITE MISSION (A-12)

a
The primary objective of Project Echo A-12 is the
demonstration of a spacecraft deployment and
tigidization technique applicable to Passive com-
munications satellites. Development of the: space
craft will be undertaken by the Langley Research
Center. The Communication Satellite (A-12) will be
launched into a 650 n.m. orbit aboard the THOR/
AGENA “B" booster. The shroud which surrounds
and protects the Communication Satellite will be the
same general shape as the $-27 except the length
is reduced to accommodate the shorter space. craft.




a)

mI

Figure 2. Hoisting AGENA
vehicle 1201 (right) above
ATLAS 97D for mating as
MIDAS II. fnstalling the _
Baird-Atomic payload
On the MIDAS lil AGENA
Vehicle. This flight verified
the thermal and mechanical
design of the payload.

aa

J

r

ae)

in

ioe)

CJ to ¢ ae

SSLPR-20 ~~SECREF- Ba


VELA
HOTEL

Program Objectives

‘The objective of the VELA HOTEL Project-is to con-
duct a research and development Program including
experiments and prototype testing to gain informa-
tion which will lead to the definition of an Opera-
tional space-based system for high altitude nuclear
detonation detection.

Program History :

The Panefsky Panel on High Altitude Detection, re-
Porting to the President's Scientific Advisory Com-
mittee, made several recommendations with respect
to research and development work which should be
accomplished in order to increase basic understand.
Ing of the physical mechanisms involved. The De-
Partment of Defense agreed to assume over-all
responsibility with Atomic Energy Commission ‘sup-
Port in the high-allitude detection area. Further, it
was agreed that the AEC would undertake labora-
tory development of the nuclear detection instrumen-
tation and that the portion of the effort concerning
measurements of natural radiations in space shouid
be implemented jointly by the DOD and the NASA.
Within the Department of Defense, the Advanced
Research Projects Agency was assigned the man-
agement responsibility for Project VELA on 2 Sep-
tember 1959, On 18 September. 1959, ARPA issued
Order Number 102-60 to AFSC for a study and
evaluation of the technical and operational factors
associated with the detection of high-altitude nu-
lear detonations. The initial results were used in
October 1959 to provide the State Department with
supporting technical data for the United States dele-
gation at the Geneva conference. Amendment No, 1
to the original ARPA Order directed AFSC fo extend
and refine the original study. It was subsequently
requested that a joint working group including
AFSC, AEC and NASA representatives, chaired by
AFSC, be established. The mission of the Joint
Working Group was to recommend a research and

SSLPR-20

ATLAS

to

le configuration (right).
Artist's concept of fc ad
showing soler celiz. Xray de-

sectors and injection motor,

Figure 1. VELA HOTEL |

development program which would investigate the
concept of nuclear detonation detection from satel-
lites. To facilitate conducting the work involved, the
Joint Working Group formed subcommittees for
payload, space boosters, and communications and
control.

Program Concept

On 21 June 1961, the Secretary of Defense ap-
Proved and funded the VELA HOTEL Program. The
Program will consist of five launches from the
Atlantic Missile Range, beginning in April 1963
and extending through April 1964,

The launch vehicle for the VELA HOTEL Program will
be an ATLAS D/AGENA 8, Each vehicle will place
two spacecraft into a single highly elliptical orbit.
The instrumentation aboard the spacecraft will be
fumished by the AEC ond will consist of X-ray,

Fl



SPACE

BOOSTERS

SPACE BOOSTERS

EXISTING OR PROGRAMMED
STAGES



The DISCOVERER Program consists of the design,
development ‘and . flight testing of two-stage vehi-
cles, using the Douglas DM-21 Space Booster 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 Projects Agency, with technical manage-
ment assigned to AFBMD. On 14 November 1959,
Program responsibility 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 per-.

form space research in support of advanced’ satel-
lite programs.

PROGRAM OBJECTIVES

{a) Flight test of the satellite vehicle airframe, pro-
pulsion, guidance and control systems, auxiliary
power supply, and telemetry, tracking and com-
mand equipment.

{b) Attaining satellite stobilization in orbit,

1c} Obtaining satellite internal thermal environment
data. ,

(d) Testing of techniques for recovery of a capsule
ejected from the orbiting satellite.

{e) Testing of ground support equipment and devel-
opment of personnel proficiency. .

(f) Conducting bio-medical ‘experiments, including
injection into orbif, re-entry and recovery.

PROGRAM SUMMARY

Early launches confirmed vehicle flight and satellite
orbit capabilities, developed system reliability, and
established greund 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 programs. DISCOVERER vehicles are
launched from Vandenberg Air Force Base, with
orbital operational control exercised by the Satellite
Test Center, Sunnyvale, California,

Tracking and command functions are performed by
the stations listed in the Table on Page A-4, A

history of DISCOVERER flights to date is given on
pages A-5 and A-6.

«

55.9 feet

AGINA
SECOND STAGE ="
Weight—
Orbitet 2,261
Impulse propellants 12,980
Other —
TOTAL WEIGHT 15722
Engine Model XLR81-80-9
Thrwstibs,, vac. 16,000
‘Spee. Iepeee., vos. 290
Bern time-sec. 40
soosten om2t
Weight—Dry 4,500
Fuel 33,700
‘Oxidizer (LOX) 68,200
GROSS WEIGHT (tbs.) 108 400
Engine 63
Block 2
Theust, tbe. (S.L) 169,000
Spec. Imp., sec. {S:L.) 248.3

Burn Time, sec,


passe
—_— —
i a - TM~
: 24 HOUR EQUATORIAL ORBIF ORBIT FOR EASTWARD
; Lg \
/ : @ INJECTION THRUST

’ ( « cout |

Performance Susemary—pasnno on PROGRAMMED BOOSTERS

20,000 perare 7 Alo eee
Vy \ —— ATLANTIC MISSILE RANGE EASTWARD
VN \ — 7 PACIFIC MISSILE RANGE POLAR
10,000 | -AA—a NN —@ 24 HOUR EQUATORIAL ORBIT _
te St LAUNCHED FROM THE ATLANTIC
AS MISSILE RANGE (Paylood capability
§ 5,000 DAN a x reduced because of yaw maneuver}
: = 3,000 SA OSSA =~
2 ST SS ~
2 \, NN ss
o A. oe ~
= NN “s
2 eof NN [NaS
1,000 py} ~—* S
| ————
~ AN
3 500 y i" ~ N ~ —
| E rey ‘ _\
TS g00 LT THOR-aBLesTaR\ | \ \
1 LLY sue scour AP aig
N amas b |) \
Si ‘\ \
1% 1 Lib, of
| ° 5 10 15
PAYLOAD — 1000 LBs



‘DM-19/A310-118/ DM-21/Abledter DM-21/AGENA B THAN ATLAS D/AGENA B
ABL X248-A5

ADVENT (Phase One} .

ADVENT (Phase Two) .
ADVENT (Phase Three}
ANNA ..
BAMBI .
COURIER ....

N-2

DISCOVERER (1 thru 15)
DISCOVERER (16 thru 19)

MIDAS (land Il).......
MIDAS (II and subs). . .

ATLAS D/CENTAUR



SECRET

fo 7 io -- Existing or Programmed Stages

‘ SATELLITE VEHICLES

, AGENA - teciheed missites ond Space Compan
; J NGINE MODEL — Boll Aerospsce Systems Ml yLR-81 Bans mesizor Buns: Ba-9@

Oweight — inert 1,262 1,328 1,346
Fuel — UDMH
Oxidizer — IRFNA
Orotat 8,165 14,789 14,807
Height — feet 4 19.5 21
Engine
: Thrust — tbs. (vacuum) : 15,600 15,600 16,000
iy Specific Impulse — 'b.-sec/Ib. (vacuum) 277 277 290,
4 Burn Time — seconds 120 240@ 240@
it OOM OO®@ OHOGD
ABLE series — Aerojet-General Spacecraft Division
. L
: Aj10-42 | Al10-101 BE ior
as. (and -118) (and -10TA) (Ablestar)
Weight — wer 1,247 848 1,297
Fug! — UDMH . 875 869 2,247
Oxidizer — IgPNA 2,500 2,461 6,227
Total : 4,622 4,178 771
Height — feet 18 16 15
Ehgine
Thrust — tbs. (vacuum) 7,670 7,720 7,900
Specific Impulse — Ib-sec/Ib. (vacuum) 267 268 277

. C102 OO@ OEOXE))
CENTAUR ~ General Dynamics

Asi

Weight - ary 2,891@ CENTAUR modifications
Fuel — Hy, lrogen - necessary to meet
Oxidizer — Liquid Oxygen . - ADVENT mission are
. Total . : 32,000 being determined
. Height — feer 45.5
Engines (Two) — Pratt & Whitney RLIOA-3

Thrust — Ibs. (vacuum) (1 5,000 each) 30,000

Minimum Specific Impulse — tb-sec/Ib, (vacuum) 420
Burn Time — seconds

NOTEs;

Payload weight not included, Does include CO) Number of suecesstut flights,
controls, guidance, APU and residual propellants. °

oes not include THOR adapter (225 ibs.) Not tested- because of first stage failure.
or ATLAS adapter (315 Ibs.) O use of fi

Single restart capability . D) Number of iounches attempted.
val burn capability

@changes in payload weight affect fuel and (=) Percentage of success,

oxidizer weights, but not total weight. :
ssn “SECRET:

Burn Time — seconds n3 296 |



Launch Schedule

& Successful flight . @ Unsuccessful flight

Flight History ee

Blue Launch of
Scout Date Lede Dealt oeion ' Remarks

DI 21 September A XRM-91 Telemetry was lost prior to fourth stage burnout.
: All of the primary opens Sts Core accom.
plished; none of the secondary (payload) objectives

were achieved,

D2 8 November A XRM-91 A second stage motor failure occurred at T plus 60
seconds. The vebicle impacted approximately 240.
1.18, downrenge,

8 Tiemann Fs Rishon pled wet tached sce
recovered. All orber primary objectives were achieved
45 were the majority of secondary objectives,
D4 3 March A XRM-90 The 172-pound load was launched successfully,
conden} obeceet wert eb rma and
se o were .
load experiment data were obtained, per

0S 12 April A&C XRM-90 The 365-pound payload was launched on a probe

D6 9 May ARG XRM-89 ledicasions are shat « control motor power lead be-

was ers.
*Type of Flight ‘A— High Altttvde Experiments C— Recovery E— BoorGtide
8 — Re-Entry Study 0 — Orbital

SSLPR.20



MIDAS GROUND SUPPORT FACILITIES

Facility Equipment* Flight Function
Satellite Test Center ABCDEP Operations control, orbit computations and predictions, initi-

ation of commands to satellite (via tracking stations), process
Payload data,

Vandenberg AFB ABCEFGHIJKLMP: Ascent and orbital tracking; telemetry reception; trajectory
Tracking Station computations; command transmission; reception recording
and processing of Payload data,

Downrange Telemetry GHUNO Tracking and data reception during ascent. (Three ships are
Ships ‘available for this function, Equipment is typical.)
Hawaiian Tracking BEFGHJ Orbital tracking, telemetry reception, payload data reception.
Station
AMR HJ Orbital data reception.
New Hampshire ABCEFGHIJKLM Orbital tracking; telemetry reception; command transmission;
Station reception, recording and transmission of payload data,
African Tracking BEGJ Telemetry reception and recording during second burn,
Station
North Pacific BCEHKMP Satellite and Payload data reception, command transmission.
Station
Kodiak Tracking FJ Orbital tracking.
Station
Mugu Tracking BEFGJ Tracking and telemetry reception.
Station

NOTES: (1) in addition to equipment listed, all stations have inter. and intra-station

communications equipment and checkout equipment.

(2) Equipment listed is either
for procurement.

“Equipment
A. General Purpote
ond Support Equipment

PICE

VERLORT

ZOTMPOne

PAM FM Ground Station

Data Conversion Equipment

. Master Timing Equipment
Control ond Display Equipment

VHF FM/EM Telemetry Station

Presently available or planned and approved

Doppler Equipment

YUP Telemetry Antenna

UH Tracking and Data Acquisition
Equipment (60 foot FAD Antenna)
UHE Angle Tracker

UNF Command Transmitter

|. APL Doppler Equipment

. SPQ-2 Rader

Midas Paylood Evaluation

end Command Equipment

Ree

POZE

SSLPR.20



~SHGREF

Tracking Stations which received data from
the VHF Data Link and the method of trans-
mission to the Satellite Test Center.

KODIAK ISLAND,
ALISA
e
&
Few manpsnize
. NN
re tones -VANDENBERG =” Ps
TmacKina ‘

KAENA POINT,
HAWAII
@.
© SmP HO. 2
‘ORBITAL
TRACKING
cinefeoemaecgmmmTM
Teaching Station, the Hawall Trucieg Stories ond wraica
ote Atlantic Miaale Range TEL 3 Station, pare
time at Vandenberg. Data was transmitted in
ie

shi
ation was transmitted in near H time to the
STC by vole and telatype,'s "Met Tet fie

Experimental telemetry date received and
receded the A hte aso ae,

biz =SECRET__ SsLPR2n



Figure 1. piidapiethied
solar ai febove) on MID,
I. The new atitede contra!
‘valve heating element instal-
lation is mounted at the 12
o'clock position behind the
Haine shield. This installation
Insuced operation

‘engines fire prior

to main engine ignition and
the vehicle to

force the fuel and oxidizer
toward the rear of the tank.

SSLPR-20


Monthly Progress — BLUE SCOUT
Program Administration

© Preliminary Program Plans for Calendar Year
1962 were established. The planning included range
support for the program, payloads that require space
. boosted support from the BLUE SCOUT Program, and
submittal of cost estimates for the Program. (U)

© A Complete Manpower Package has been pre-
pared, justified, and submitted. Included in the
package were the new jobs created and personnel
required to support the new Programs scheduled for
indusion in the Calendar Year 1962 faunch program.
(u)

Flight Test Progress

© The launch of the seventh BLUE SCOUT vehicle
(D-8} is scheduled for early September. Recent pay-
load equipment changes by NASA have caused the
launch to be rescheduled from early August. This
guided four-stage XRM-92 vehicle will be lounched
from the Atlantic Missile Range and will place a 150-
pound payload into a 300-nautical mile circular
orbit with @ 32.5 degree inclination angle. The pay-
load will check out airborne and ground-based units
Of the world-wide MERCURY tracking network. It will
contain S-band and C-band radar beacons, a Mini-
track system beacon, command ‘equipment for con-
trolling the payload equipment during flight, and
telemetry equipment for obtaining data on payload
Operation and for assisting in the control ‘and track-
ing of the satellite. in addition to the payload
objectives, the vehicle objectives are as follows:

1. Evaluate the guidance and control system.

SSLPR-20

2. Investigate the temperature and vibration envi-
ronment within the vehicle. .

3. Verify motor performance.

4. Demonstrate stage separation of the Air Force
Scout.

5. Verity the adequacy of Pad 18B for use in
launching guided BLUE SCOUT vehicles.

6. Demonstrate the compatibility of the vehicle
and the aerospace ground equipment.

7. Develop a military capability for assembly,
checkout and launch of the Air Force Scout vehicle.
tu}

© The BLUE SCOUT Junior vehicle (0-1) is being
processed on a non-interference basis with vehicle
0-8 at the Ationtic Missile Range. Launch Prepara-
tion end documentation will be accomplished entirely
by Air Force personnel of the 6555th Test Wing
(DEV) and the Air Force Special Weapons Center,
respectively. The lounch of this vehicle with an
AFSWC payload is scheduled for late in August.
(U)

Facilities .

© Approval for initiation of BLUE SCOUT facilities
design ot the Missile Test Annex at the Atlantic Mis-
sile Range has been requested from HQ USAF
through HQ AFSC. Amended construction project
justification data {Form 161) reflecting minimum
facility requirements were forwarded to HQ USAF
in April. Allocation of P-313 design funds has: also
been requested to permit immediate Architect-Engi-
heer contract negotiaions upon receipt of approval.
tu)



Eight MIDAS Satellites — — four each in
two orthogonal polar orbital
tes — 28 2,000 n.m. altitude

Si

Satellite Test Center

Point Arguello Launch Comm



ie ee ee eT =

BOOSTERS

THOR — Douglas Aircraft Company :
| DM-18 | DM-19
Weight — dry 7,846 7,204
Fuel — RP-1/RJ-1* 31,500 31,500
Oxidizer — Liquid Oxygen 68,000 68,000 68,000
Total . 107,346 106,704 108,090 106,370 :
Height — feet 61.3 65.1 55.9 60.4 4
Engine — Rocketdyne Division of North American Aviation MB-3 Block | MB-3 Block | MB-3 Block it MB-3 Block I =
— Ibs. {sea level) 152,000 152,000 169,000 152,000
Spec. Impulse — ib.-sec/Ib. (sea level} 247.0 247 250 247 |
Burn Ti seconds 160 160 149 160
Bell Telephone Laboratories series 400
cartels “—" ©® © ©C©@ OOH OO
ATLA — General Dynamics-Astronautics .
Series D
Weight — dry 15,100
Fuel — RP-| 74,900
Oxidizer — Liquid Oxygen 172,300
Total 262,300
Height — feet 69
Engine — Rocketdyne Division of North American Aviation MA-5
Thrust — Ibs. (sea level) *
Booster 309,000
>  Sustainer 57,000 :
Vernier 2,000 ‘
Specific Impulse — 1b-sec/Ib. Isea level) :
Booster 251 :
ao © B®

Guidance — Radio Mod Hi/INl — General Electric (radar), Burroughs (computer)

TITAN Il ~The Martin rt sr STAGE

Weight — dry
Fuel — NsH./UDMH 83,713
Oxidizer — N,O, 161,632.
Total 257,576

Height — feet (combined first and second stage}

Engine — Aerojet-General Corporation XLR87AJ-5
Thrust — Ibs. 430,000 {sea level)
Specific Impulse — Ib-sec/Ib. 258 (sea level)
Burn Time — seconds 146.3

Guidance — Radio Mod WU — General Electric (radar), Burroughs (computer)
UPPER STAGES

X248-9
Allegany Ballistics
Lab
Weight — wet 60
Propellant — Solid 459
Total a9
Height — feet
Engine

Thrust — lbs. (vacuum) .
Specific Impulse — tb-sec/Ib. (vocuum}
Burn Time — seconds

2750
Od@
—SECRET_

N4

90

SECOND STAGE

20,

375 .
200
702 oy

37,7

63,714

XLR9

TAJ-5S

100,000 {vacuum}

1

314 (vacuum)
81.9

SSLPR-20



—CONFIDENTIAL-

RANGER- NASA
/ AGENA “B”

Program Responsibilities — The RANGER-NASA
AGENA "BY Program is the over-all Fesponsibility
of Headquarters NASA, The responsibility for the.
spacecraft has been assigned to Jet Propulsion
Laboratory (JPL for interplonetary investigations
1 and Goddard Space Flight Center (GSFC) for the
AGENA B earth satellite programs. The booster system was
delegated to Marshall Space Flight Center (MSFC)
who in tum assigned Space Systems Division the
Fesponsibility and authority for the over-alt accom-
Plishment of the booster Program,
Under NASA Order No, $4601-G the Air Force is
supporting the NASA AGENA "BY Program. This will
permit NASA to take full advantage of the technical
and operational background and experience devel-
oped by the Air Force in space booster projects;
Permit contractors to discharge their contractual
obligations with NASA ond USAF utilizing already
established management relationships, insofar as
Practicable; and provide NASA the benefits of
contract administration services and procedures
already established for USAF Programs employing
the same basic vehicles as those scheduled for this
program.
The ATLAS and THOR first stage boosters were allo:
cated to NASA for the missions planned through
1964. Contractual action was initiated with General
Electric {GE} and Bell Telephone Laboratories (BTL)
for the guidance systems necessary for the respec-
tive boosters.
letter contract AF 04(647)-592 was awarded to
Lockheed Missiles and Space Division {LMSD) for
Procurement of nine AGENA “Bp second stage
boosters. This contract also Includes modification to
Stand 12 at AMR: conversion of the Polaris static
test stand. at Santo Cruz Test Base; and procurement
of Aerospace Ground Equipment to checkout,”
handle. ond launch the AGENA “BY booster.

-CONFIDENTIAL a



_—<SEGRET—

Flight History (continued)

awe —
ENA mall
o 160 1019 . 21 January 1959 FeOn fects 2 melinctin om pad
163 1022 8 Attained orbis Te received for 514
1 6 0 28 February shor wean ‘demetry
u 170 1018 13 April Se Tonk oct mtcetall, Recoony cobonle cecal -
ow 176b orbis seas not recovered, All objections except
recovery successfully achieved,
1] 174 1020 . 3 June Lanach, atcont, seperation, coast and orbital boos suc-
orbit becasse of low
Seite Raid to achieve of low perform.
Vv Wg > 1023 25 June Same as DISCOVERER HL.
ale
v 192 1029 13 August Alt obiectioe seisgitally schioved except cops
vi 200 1028 19 August Same as DISCOVERER V.
vii 1 ovbis » Lack
U 206 1051 7 November Asteined ncegssally tof 00-czele power
vIn 212 1050 20 November Arsained orbis successfully, Malfenction .
AGENA engins thuidown a dented onbudl ceenee
Recovery copsale ejected but not recovered, .
ix 21 05: 4 February 1 THOR shus down promaturely, Umbilical cord
5 1052 February 1960 ‘id not raeacs. Quick dscoenacs fallod, conor lone ct
helium pressure,
THO! Tr
x 223 1054 19 February Fs IR deswrozed at inte bY Rapes Setery
aatopilos mali 5
xi 234 1055 15 Aprit Astained orbit successfully, capsule ejected
ab ke Resoeary *
on 17th orbit was mot recovered. All objectives exces
xu 160 1053 - 29 June Lawnch, ascont, coast and orbital stage ig-
sition Pe achieve orbit because
OF AGEN nds darn ta epiece obi
xu 231 1057 10 August Asained orbit j. Recovery capsule ejected
Avo on Thi era. Copal as reconayed ier « water
she airborne racovery wore succetsfally achieved,
xiv 237 1056 |. 18 August Aitained orbit successfully, Recovery capsule sjected
17¢b orbit and 1
on tty ta, Successfully recovered by she
5 Attained orbit: . ond
xy 246 1058 13 September 4 Ejection yrovery
Of te reves foray, cael Boh as ne Soe
retvieved. .
1 2. and BNA failed
xv! 53 1061 26 October Launch Ae spe AG failed to seperate
xv 297 1062 12 November Attained orbit successfully, Recovery caprate
31 orbit ond aerial recovery
‘i cbjasioes Gore mses bie eds
XVI 296 1103 7 December Assained orbit successtuily, Recovery copiale nerd
48th orbis and aerial recovery
XIX 258 1101 20 Dec Attained orbit Ne , radio-
ember metric data gathering IDAS support flighs.
xx 298 W WwW ined orbis 5
04 February dined + successfully. Capsule déd nos re-enter
AS



———

—SECRET=

solid propellant vehicles, to train AIR- FORCE PER.
SONNEL in Processing launch of the vehicles, and
to accomplish BLUE SCOUT Program objectives. The
Application Phase will sUPport programs such
as SAMOS, SAINT, BAMBI, ASSET, TRANSIT, and
” PROBES. The vehicle receipt, assembly, payload mat-
ing, checkout and launch will be accomplished by
Air Force military Personnel during the Application
Phase.

Performance

The BLUE SCOUT vehicles have a performance capa-
bility which permits them to: (1) place a 200-pound
Payload into o 400 nautical mile circular orbit, (2)
boost a 200-pound Payload to 4,000 nautical miles
‘on a probe trajectory, {3} boost a 25-pound payload
to 75,000 nautical miles on a Probe trajectory, (4)
place a 400-pound payload into a boost-glide tra-
iectory at a velocity of 20,500 feet Per second at
250,000 feet altitude. Besides ORBITAL FLIGHTS,
PROBES, and BOOST-GLIDE trajectories, the vehicle
can boost payloads into trajectories and downward
booster HIGH-SPEED RE-ENTRY Profiles, data RE-
COVERY capability and ATTITUDE STABILIZED final
stage (and payload) are also provided,

Program Management

Development Phase: An abbreviated Development
Plan, covering the Development Phase only, was ap-
Proved on 9 January 1959. This plan gave Space
Systems Division management responsibility. In June
1959, Aeronutronic Division of the Ford Motor Com-
Pany was chosen through normal competitive bid.
ding as-the Payload, Test and Systems Integration
Contractor. The procurement of vehicle components
and associated support equipment, modified to meet
BLUE SCOUT requirements, is being made through
NASA, rather than direct Procurement from the
SCOUT contractors, Atlantic Missile Range launch
complex 18 and on existing assembly building are
being used for the Development Phase of the pro-
gram. The 6555th Test Wing (Dev) manages the
Development Test Program at the Atlantic Missile
Range and provides the Air Force personnel who are
being trained to assume the vehicle Processing,
launch and evaluation tasks. An ail-mititary opera-
tional capability will be developed from this group.

Application Phase: Space Systems Division will
have the responsibility for Providing BLUE SCOUT
booster support to the Air Force and other gOvern-
ment agencies for SPACE SYSTEMS, test of SPACE

High Altitude
Experim

eee

mye

SSLPR-20



SECOND STAGE— ABLESTAR (AJ10-104)
Thevet (vacuum) 7900 pounds
' ‘Specific impulse (vecwm) 277 seconde
Boring theme 296 seconds
Propeilent waa
t FIRST STAGE — THOR tan
Thrust (000 level) 182,000 pounds
‘Specific impulse (s0a fevel) 247 seconds
Burning time 163 seconds
H Propellant Lguld Oxygen
wr
'
'
‘
L Figure 4. Payload ervengoment for TRANSIT 4A fight.

Figure 3. Two stage vebicte msed for.

TRANSIT 1B ond subsequent fights,
Program Objectives

1, Provide accurate navigational reference informa: ino eerition | The ANSI nl prea’
‘tion for POLARIS launches. . Separate assemblies and has a total weight of 300
2. Precise determination of satellite position by Pounds. The TRANSIT payload (175 tbs) is the next
measuring the doppler shift of satellite transmitted step in the Navy Program to develop an Operational
radio signals. navigation system. The payload is a short cylindrical
shape as opposed to the spherical shape of all the
3. Investigate the refractive effect of the lonosphere Previous payloads. The new shape is close to that’
on radio transmissions, which is proposed for the Operational system pay.
4. Acquire additional geodetic and geographical ads. The TRAN A NSIT 4Ap Pevlood a the fie satelite
PI [a
data by precision tracking of the orbiting satellite. SNAP Power Supply). This radioa clive supply. pro-
Flight Vehicles TRANSIT 1A was a three stage vides power for the operation of several satellite
vehicle as shown in Figure 1. TRANSIT 1B and subse- dom, he jecond scale, fe DON Payload,
is under the cognizance r. Van Allen of
Hoey icles are two stage vehicles as shown in the State University of lowa. It will perform redienic
‘gure 3. Reuiurements. The third satellite (55 Ibs) is a Naval
Launch Plans All vehicles will be launched from Research Laboratory GREB with to study
Complex 17 at the Atlantic Missile Range. Launch solar emissions, There ts clso 3° Pounds of inter-
a o . ° connecting structure consis! ng of a spin table to spin
fan will vary between 45.5° and 140: for each the GREB, springs to separate the payloads. cog

supporting brackets for the launch phase.

M2” CONFIDENTIAL SSLPR.20


Launch Schedule
59

slalsfotnfofofe|ulalnl

CONFIDENTIAL

60

sfsfalsfolnfo

Pita

6 62
mlalmlufyfalsfofufo Jlefmfa ufo
IUMBER

TRANSIT FUGHT NUMBE!

a 1B 2A 3A 3 4A 4B SA
‘ ay - be "7 fa by ijt
Ly : iy C
ORBIT INCLINATION ANGLES A. 50° B.67.5  C. 28.5
* Attained orbit successfully © Failed to attain orbit
Flight History
TRANSIT Thor —Ablestar

Neo, Launch Date -_ No. No, Remarks

1A 17 September 136 - The three-stage vebicle was launched from Stend
174 at the Aslansic Missile Renge. The peyload was
08 injected tuto orbit, because the shind stage motor
failed t0 ignite. :

IB 13 Aprit 257 002 The Thor Ablester boosted satellite was launched
from Steud 17B at AMR. The satelite was placed
into orbit, The Ablestar second stege (om its fist
Highs 1031) fred, shut off, coasted, and shen restarted
om space,

24 22 Jane 281 003 A dat payload, consisting of TRANSIT 2A plas

. GREB (which studied soler emsissions), was placed
se orbit by she Thor Ablester vebicle. A propellant
slosh problens, discovered in the second stage, bas
been corrected,

3A 30 Noxembor 283 006 = TRANSIT 3A failed to achiove orbit when she fast
stage Thor shut down prematurely, after « failore
in she main ongine cutoff civcaitry, Staging occurved
and the second performed i sntil it
toas cut off end destroyed by Range Safety.

3B 21 February 313 007 TRANSIY' 3B was leunched with only partial success,

. The Ablastar stage failed to vasters in space and the
deyloads did wos seperase. Alshough wo definite cause
‘bas yet been determined, the counting device in the
Ablaster programmer is considered she most probable
cause of malfunction,

44 28 June 315 008 = TRANSIT 44 twas laanched, with great success, into

IT 4A, containing the fst radioactive power poly
+0 be used im space; INJUN, which studies radiation
tm the lower Vaw Allen and awroral zones; and GREB,
which studies solar X-Ray emissions,

M4

~ CONFIDENTIAL SSLPR-20


Monthly Progress — TRANSIT
Program Administration

. ‘Al the request of the Navy, the launch of TRAN-
— SIT 48 has been rescheduled from late August to
mid-November. (C)

Ablestar

_ guidance (below). Close
ob (right of hd epee slo Clove

on the new mounting tlag. The BTL

ssumn CONFIDENTIAL —

MS


—CONFIDENTIAL

Program History

The BIOASTRONAUNICS Office was established in
May 1958 and charged with the biotechnical super-
vision of the early military “Man-in-Space” Program
‘and the Bloustronautics Aspects of the DISCOVERER
Program. NASA was subsequently assigned the
“Man-in-Space'’ responsibility in the fall of 1958,
The development and fabrication of suitable Biomedi-
cal Recovery Capsules for the DISCOVERER Program
has continued without interruption.

On 13 May 1959, a MARK | biomedical capsule was
successfully flown without specimens. ‘The flight telem-
etry demonstrated successful Operation of the
Bioastronautic subsystem as an ‘engineering concept.
Although re-entry was successful, recovery was not
accomplished. A second MARK | capsule was
launched on DISCOVERER IV on 25 June 1959 with
four mice aboard. Although orbit and recovery were

‘animals to be in geed condition throughout the
flight.

Subsequent DISCOVERER efforts culminated in Prep-
Gration of a MARK I capsule suitable for a small
Primate. Launch and recovery of a small primate
from orbit awaits approval of an “Abbreviated Space
Systems Development Plan, Biomedical Program’
submitted to Hq AFSC in November 1960.

Applied Research contracts for the design and de-
velopment of advanced biocapsule hardware include
photosynthetic oxygen production, super-critical gas
storage, radiation shielding and bio-instrumentation,
All components ore scheduled to be flown in subse-
quent advanced space blocapsule Programs,

An Advanced Biomedical Capsule has successfully
completed the mockup phase of development. The -
capsule Is designed to carry a fifty pound chimpan-
zee to altitudes of about 25,000 n.m. to thoroughly
explore and assess the radiation hazards of the
inner and outer Van Allen Belts. In addition, tong-

ca CONFIDENTIAL

term weightlessness effects will be investigated. On
7 November 1960, Space Systems Division approved
continued development of the advanced capsule in

support of eventual manned military space systems.

Program Concepr
The complete exploration of space, including limits

fo manned operational space systems, requires a
determination of the biological effects of the space

environment. The Space Systems Division Is continu. *

ing its aggressive research and’ development pro-
gram In this technical area to insure that sufficient
bioastronautics knowledge will be available during
the 1963-1965 time period. Present deficiencies in
teaching these goals are: capsule development, life
support system design, biological’ Instrumentation
and determination of space flight stresses (long term
weightlessness, operational *xperience in the radia-
tion belts, and isolation). Neither Project MERCURY
with its short duration, low altitude orbit, nor DYNA
SOAR with its low altitude suborbital flight will Pro-
vide data concerning the key problems of long term
weightlessness and Van Alien Belt radiation, Knowl.
edge which is crucial to manned operational space
systems,

The current BIOASTRONAUTICS Program is furnish-
ing a limited amount of data from actual ballistic
and orbital flights. Experiments include those made
on @ space-available basis aboard scheduled ICBM
and DISCOVERER Program flights. The Bioastronau-
fics Orbital Space System (BOSS), when approved
as on Air Force system, will not be limited by piggy-
back or space-available restrictions. Data obtained
from these tests will be available for correlation with

DYNA SOAR Program and Project MERCURY and will
be necessary to the ‘success of future manned mili-
tary missions such as SMART.

SSLPR.20


jite
Higa
H i allie Hi
HM Hal iy

iy

egy
al tf
il in |

1} rt
i

M

4 awe



—SECREF-

Powered Flight Trajectory

5. tm Orbit — Controlled (same os 4.

i

Telemetry ships are positioned as required by the
specific mission of each flight. Illustrations on the
Opposite page show a typical launch trajectory from
Vandenberg Air Force Base and a typical orbit. An
additional objective of this program is the devel-
opment of a controlled re-entry and recovery
capability for the payload capsule. The recovery
operation is.also shown on the opposite page. An

“impact area hos been established near the Hawaiian

Islands and a recovery force activated, Techniques
have been developed for aerial recovery by C-119
and JC-130 aircraft and for sea recovery by Air
Force pararescue men and Navy surface vessels.
The recovery phase of the Program has provided
advances in re-entry technology. This information
will be used in support of more advanced projects,

AGENA VEHICLE DEVELOPMENT

The AGENA vehicle was originally designed asa
basic satellite vehicle for Military Space Programs.

The first AGENA “BY used the Bell XLR-81Ba-7
engine and was first fiown on DISCOVERER XVI.
The latest AGENA “BY vehicles use the 16,000
Pound thrust XLR-81Baq-9 engine.

=
AGENA “BY

Nose Cone

Fuel ond Oxidizer
ro
ee
45:1 Noazle Frgine (uM)
DISCOVERER/AGENA

FIGHT PATH



' maoas pan muptoveaner . PRESIDENT OF U.S.

' DEPARTMENT OF DEFENSE

. i

NORAD
OTHER US porn] OTHER ALLIED
GOVERNMENT AGENCIES MIDAS CONTROL AND GOVERNMENTS
DISPLAY FACILITY
i
5 MIDAS TRACKING &
“ NOTE: The Air Defense Com- CONTROL CENTER
‘ mand will operate the MIDAS
: System under the operational i
control of CINCNORAD, READOUT STATIONS
SPACE VEHICLE NETWORK

a

CONCEPT

the MIDAS system is designed. to provide
continuous infrored coverage of the Soviet
Union. Survailionce will be conducted by
eight satellite vehicles in accurately posi-
tioned orbits. The area under surveillance
must be in line-of-sight view of the scanning
satellite. The system is designed to accom-
plish instantaneous readout of acquired
data by at least one of three strategically

located readout stations. The readout

stations transmit the data directly to the
MIDAS Tracking and Controt Center where
it is processed. It is then displayed and
evaluated in the MIDAS Control and Dis-
play Facility. If an Gttack is determined to
be underway, the intelligence is communi-
cated to a central Department of Defense
Command Post for relay to the President
‘and all national retaliatory and defense
agencies,

AL

SSLPR-20



EGRET

Flight History

_ ‘Ne. "Ne. Fight Dete : Remarks

DISCOVERER FLIGHTS 0 THRU XX ARE ON PAGE A-6

ined orbis radio
xxl 261 1102 18 February Attained oF . RAN Now-recoverable,
~ xl 300 1105 30 March Lownch, ascout, speraion, coast and orbital stage
sormal, selocity ‘atainsd
fer pod sty oe at
XXII 307 1106 8 April Attained orbit smccessfully, Loss of control gas pre-
sented 2 she
Sermons. of tb celta for capmnle
_ xxIV 302 1108 8 June mie to attain orbit because of « second stage
xxv 303 WwW Asteined. orbit
07 16 June he tcoen th Ceetally. Cabsale cecoyered from
achieved,
~ xv! 308 1109 7 July Astained orbit , Copeule wat eincted om the

orbit and
32ed recovery was accomplished.

XXVIE 322 1110 21 July Failed 20 attain orbie because of severe booster pitch

earn SECRET. as


f=
La
cz
W)
ui
Vv)





—CONFIDENTIAL

Monthly Progress — ADVENT
Technical Progress

Booster Vehicles

© General Dynamics-Astronautics started fabrice-
tion of the 1/14 scale models to be used in the
NASA Ames Laboratory “ground” wind tunnel test
program for ATLAS/AGENA and ATLAS/CENTAUR
space vehicles. Work is proceeding on schedule with
the tests programmed to begin on 15 September.
(u)

© Wind tunnel model construction at Lockheed
Missiles and Space Company is proceeding on
schedule. Present planning calls for the LMSC super-
sonic tunnel portion of the test program to start on
4 September with the Langley transionic tunnel to
be used starting on 11 September. The first phase
of the Ames Research Center has been completed;
this phase concerned pressure data on a 1/10 scale
model, Initial evaluation of the static pressure data
indicate no major problem areas. The ‘fluctuating
Pressure data reduction will be completed during
August. (C)

¢ Apreliminary copy of a revised work statement
for the ATLAS (Series |} booster has been completed
and is currently being reviewed by the Space Sys-
tems Division and Aerospace: Corporation. (U)

© LMSC is verifying the capability of the horizon
sensor to see the sun at various launch dates and
vehicle attitudes. The AGENA B horizon sensor has
been a problem on other space programs. (C)

¢ Final assembly of the first ADVENT AGENA
vehicle wilt be completed on 7 August. (C)

¢ A detailed work statement for the ADVENT/
CENTAUR engines has been completed and is being
reviewed and coordinated with other Air Force Sys-
tems Command agencies. (uy

@ General Dynamics-Astronautics is revising the
ADVENT/CENTAUR proposal to incorporate changes
fo the original proposal as requested by the Space
Systems Division. Aerospace Corporation is provid-
Ing technical assistance in this effort. It is anticipated
that GD-A will submit the revised proposal no later
than 15 August. {U}

Final Stage Vehicles

© A tentative agreement on the basic propellant
handling and loading procedure for ADVENT Final
Stage Vehicles has been reached by all agencies

concerned. The basic concept, as submitted by Gen-
eral Electric-Missile and Space Vehicle Department,
is a remote loading procedure which involves mating
the satellite to the second stage in an unloaded
condition and filling the propellants from containers
located at the base of the gantry. (U)

© Because of the ADVENT code generator “Secret.
Crypto” classification there is an urgent need for
clarification and an issuance of security guidelines
for the handling of this material by the contractors.
A visit by the Air Force Security Service to GE-MSVD
has been set for 2 and 3 August. At this time AFSS
will tour the General Electric plant and establish the
Proper security requirements for the ADVENT code
generator, (C}

¢ Anair and ground code generator resynchronous
capability investigation has been conducted con-
sidering (1) no-resyne, (2) resync without using telem-
etry, and (3) resync using telemetry. Upon reviewing
the investigation it was recommended that the re-
sync using telemetry be adopted. The National
Security Agency was in agreement with this method.
(cy

© Asa result of the Orbit Test Vehicle schedule
review, General Electric was directed to reschedule
the structure completion date for two weeks earlier.
This will permit subsystem installation to begin on
1 November. General Electric was requested to re-
view their drawing release dates to avoid the incon-
sistency of having drawing completions occur in the
middle of the fabrication period. (C)

Tracking, Telemetry and Command,

« A study has been completed of the personnel
manning requirements to support technical equip-
ment maintenance and operation at Camp Roberts
and Fort Dix. Recommendations were forwarded to
the USAAMA with a request that-a meeting be
scheduled in the near future to establish the number
of personnel, by fob description that will be re-
quired. (U)

© Phitco has officially subcontracted the Kaena
Point antenna feed system modification. Down-time
requirements at Kaena Point for the 60-foot antenna
are being correlated with other program require-
ments for the same ontenna. The investigation of
interference from the Navy Communications Moon
Relay Station is still proceeding, but the shadowing
by fand mass of direct-line-of-sight between the two
installations will minimize this interference. (U)

ssLPRag — CONFIDENTIAL os





SECRET

Monthly Progress — DISCOVERER
Flight Test Progress
DISCOVERER XXVI Flight

© DISCOVERER XXVI was launched from Vanden-
berg Air Force Base at 1629 PDT on 7 July and was
Injected into a near-nominal orbit. All events during
launch, boost, separation, coast, AGENA burn and
orbital injection occurred as planned except for a
longer than normal AGENA burn time. This is attrib-
uted to an error in the accelerometer-integrator
system. Table | shows the predicted and attained
orbital parameters. (C}

Event Programmed Actual
Apogee, statute miles 293.6 505.5
Perigee, statute miles 147.4 142.8
Period, minutes 91.6 95.02
Eccentricity 0.0175 0.0421
Inclination Angle, degrees 81.5° 82.9°

Table i. Comparison of Programmed and Actoal
Orbital Parameters for DISCOVERER XXVI

© Ail subsystems operated satisfactorily through-
Out the orbital flight. The thermostatically controlled
electric heaters installed on thé control vaives Pper-
formed successfully, As Planned, capsule recovery

Figure 2. Discoverer XXVI AGENA B vehicle showing the space research instruments furnished
by the Geophysical Research Directorate (center). The new “sceppers” are visible on the right of

the experiment packages. They are Part of a system for draining propellant
The rectangular box on the lower left is the attitude contro! valve heating element Installation.
These modifications corrected problems that had occurred on previous fights.

SSLPR-20 ~<SECRET-

alippoge ot liftoff.

A7



CONFIDENTIAL

Monthly Progress — Project MERCURY
Flight Test Progress

e@- ATLAS 88D underwent a thorough review using
procedures required by the ATLAS Booster Pilot
Safety Program. Final factory acceptance was ac-
complished on 13 July using approved Factory Roll-
Out Inspection Procedures. This booster has been
modified to include all engineering changes recom-
mended by the MA-3 Investigation Board. {(c)

© The launch of MA-4 is scheduled for the week
of 21 August. ATLAS 88D was delivered to the
Atlantic Missile Range on 15 July and was erected
on Pad 14 on 18 July. MERCURY Capsule No. 8,
which was recovered after a successful close in
abort during the MA-3 launch, will be mated with
the ATLAS booster on 7 August. (C)

* Analysis of the recovered ATLAS 100D autopilot

Programmer is still in progress. Several engineering
modifications were incorporated In the ATLAS 8BD
Programmer and satisfactorily checked out during
composite testing. (C)

° The decision to proceed with a test program for
Incorporation of baffled injectors on MERCURY
launches is stilt awaiting a decision by the NASA.
Space Task Group. (C)

© During the week of 17 july General Bectric,
Company demonstrated the operation of the recent
modification to the Mod IIIA guidance system at the
Atlantic Missile Range. These modifications will im-
Prove system performance by extending the theo-
retical tracking limit of the system to 92,000 miles,
by providing rapid rate reacquisition to improve rate
data early in flight, and by reducing the lateral rate
nolse resulting In smoother data and improved ac-
curacy. (U)

Figure 1. Factory checkout of ATLAS 88D.
Missile Range Stand 14 on 18 July.

SSLPR-20

This booster was installed on Atlantic

—CONFIDENFHIAL Ks


Monthly Progress — VELA HOTEL
Progrom Administration

% A pre-proposal briefing for the spacecraft was
given to contractors on 20 July 1961. Proposals
from contractors will be received on 18 August.
Technical and management working groups are
bping selected to evaluate the Proposals. (U)

Technical Progress

*: A final systems test with the first of the VELA
HOTEL “Piggyback Payloads was completed on
28 July and compatibility of the equipment and the
DISCOVERER vehictes was demonstrated. A second
systems test will be conducted early in August. (U)

SSLPR-20

F3


SSLPR-20

4 Blue Scout il

JET VANES AND
AERO FINS

XRM-90

XM-78.
(THIOKOL)
SPIN IN

AERO FINS

BLUE SCOUT

(yper-Environmental Test System) ©

Program Description

The BLUE SCOUT Program provides the Air Force and
other governmental agencies with a family of eco-
nomical and versatile standard Space booster vehi-
cles for supporting. SPACE SYSTEMS, test of SPACE
SUBSYSTEMS, and RESEARCH programs, The BLUE
SCOUT vehicles have the inherent simplicity and
reliability of solid Propellant vehicles, and are for
more economical for many applications than the
liquid boosters that were derived from the ballistic
missile programs. The Program Is divided into Devel-
opment and Application Phases. The Development
Phase is being used to develop and flight test the °

HUe seouations of
we od
IT vebsclos
versatility af the bro-

ram. The Force of-

on
of le sixes,



—E€ONFIDENTIAL

Systems Test

© Discussions were held with General Dynamics-
Astronautics on the instrumentation for CENTAUR on
the ADVENT Phase Il launches. A detailed review of
the felemetry measurements has been completed
and is being correlated with the airbome instrumen-
tation package requirements. A memo is being pre-
Pared summarizing the instrumentation requirements
for Phase Ill ADVENT CENTAUR together with the
associated instrumentation requirements, wu)

Facilities

© Detailed descriptions of the additional launch
support facility requirements and facility modifica-
fions required for Pad 12 and Pad 36, are being
compiled by Aerospace Corporation for release dur-
ing the week of 31 July. Completion ef this task hes
been delayed pending the definition and epproval

of the procedure to be utilized for loading Propel-
lants on the Orbital Test Vehicle. {U)

* The contract for modifications to Atlantic Missile
Range Hangar AA In support of ADVENT Program
requirements was awarded on 29 June. A notice to
Proceed was issued on 13 July, with beneficial oc-
cupancy scheduled 110 days from that date. {U)

© Delays in receipt of final approved criteria and
late release of construction’ funds by USAAMA for
the Kaena Point tracking and telemetry station have
resuited in the decision to allow the associate con-
tractors (Lockheed Missiles and Space Company and
Philco) to proceed immediately and provide the
urgently required farfield boresight tower, and the
transmitter support requirements. The remaining
items required to support the ADVENT Program will
be designed and constructed by the Corps of En-
gineers, Hawali. (U) .

SSLPR-20



Monthly Progress — BIOASTRONAUTICS
Small Primate Unrestrained (Project SPURT)

© The second eighty-hour test of the capsular life
support function was conducted of the General Elec-
tric Philadelphia facilities on 11 July. The ecological
system functioned well. The monkey was in good
physical condition at the end Of the test. The elimi-
nation of paint from the capsule interior corrected
the excessive carbon monoxide build-up. observed
during the first test. The quality of the film taken
during the test was excellent. {cy

© The water feeder nipple was accidentally de-
Pressed during capsule assembly permitting water
to flow freely from the feeder without requiring
action on the part of the animal to initiate flow. The
animal saw the water flow but made no attempt to
drink. The feeder functioned for only thirty minutes.
Modifications are being incorporated in the water
feeder that will insure Proper functioning of the
feeder for twelve hours. The results of the two tests
Provide assurance that the hardware will function
Properly. No other eighty-hour tests are planned.
« .

* Because of the death of the animal in the previ-

SSLPR-20

us fest due to malnutrition and dehydration and the
failure of the primate to respond fo the water flow
during this test, plans cre being made to condition
several animals to the capsule environment and the
mission profile. (C)

BOSS Program

¢ A Development Plan for the Bloastronautics
Orbital Space Satelite Program (BOSS) was pre-
pared and forwarded to higher Headquarters for
Gpproval. This program calls for six orbital flights
into the radiation belts to determine the effects of
profonged exposure to weightlessness and space
radiation. Chimpanzees will be utilized os the fest
subjects. The initial phase of the Program will be
directed to the development of a suitable life support
system ond its mating to a suitable re-entry vehicle.
Advantage will be taken of the developed capa-
bility inherent to the ATLAS D/AGENA B combination
for orbital flights. (C}

© The Bioastronautics Orbital Space Satellite Pro-
Gram (BOSS) has been approved at Hq USAF with
provisions for suitable funding during FY 62. Direc.
tion has been received from Hq AFSC to implement
the program in accordance with the Development

Plan. (Cy


A, THIND SYAGE~X-248 (Allegeny Ballistic Lab.) T

Three) at oltitude 3150 pounds A

Specific impulse (vos) 250 seconds

Total impulse 116,400 ts /s0c

Burning Time 37.5 seconds

Propellant Solid B
"B. SECOND stact—as1o-42° (AcrejerGeneral) _ |

Thrust ot altitude: 7790 pounds

Specific impulse (vac) 273 seconde

Totol impulse (min) 870,000 Ibe/see

Burning time 115 seconds

Propeliont Liquid |

C. FIRST Stage—THOR RBM,

Theuat (6.1) 181,500 pounds ¢
Specific ienputse (5.1) 248 seconds

‘Specific impulse (vac)- ‘287 seconds

Burning time 158 seconds

Propellant Uquid

Figure 1, TRANSIT IA three stage fight vehicle,

The TRANSIT Program consists of the flight testing

of eight vehicles to place 200-350-pound satellite
payloads into circular orbits of 400 io 500 nautical

miles. The program is designed to provide extremely
accurate, world-wide, all-weather navigational infor.
mation for use by Gircraft, surface and subsurface
vessels, particularly in relation to POLARIS missile
firings. The ARPA Order for TRANSIT 1A was initiated
in September 1958 and amended in April 1959 to

AAUNCHINE SUPPORT Toss

OUTER Ana inne
TACING eine

ANTENA coveuNa
sarwour

ba-soem waren
rehearse HHVOASH Cane

Figure 2. Currauay drewing of TRANSIT 1A payload (NAY 1),

SSLPR-20

TRANSIT 34 launched from Aslontic Missile Reage

odd TRANSIT 1B, 2A and 28 flights. The TRANSIT
3A and 3B flights were initiated by a Navy MIPR,
dated 18 May 1960, Because of the successful
TRANSIT 2A taunch and excellent Payload per-
formance the Navy elected to launch TRANSIT 3A
rather than 2B, TRANSIT 28 was scheduled to carry
the same type payload as was carried on the 2A
flight, Subsequenily, the Navy initiated requests for
TRANSIT 4A, 48, 5A and 58,

The program was originally authorized by ARPA
Order No. 97-60, which assigned AFBMD: responsi-
bility for Providing the booster vehicles, integrating
payloads to the vehicles, and flight operations from
launch through attainment of orbit. The TRANSIT
Project was transferred to the Navy on 9 May 1960.
The Navy has now assumed both the administrative
and technicat fesponsibility for the TRANSIT pro-
gram. Paytoad tracking responsibility has been
assigned to the USN Bureau of Weapons. Applied
Physics. Laboratory is the Payload contractor.

~ CONFIDENTIAL ~ me


RET COMP BEATS

: GROUND SUPPORT FACILITIES
i .
‘ ee
Facility Equipment* Flight Function
: Satellite ABCD Orbital control, orbit computations and predictions, acquisition
Test Center data for tracking’ stations, Prediction of recovery ares.
Vandenberg AFB BDEFGHI Ascent and orbital tracking, telemetry reception, trajectory
Tracking Station measurements, command transmission.
$
4 Downrange : BFHI Telemetry reception and tracking during ascent and orbit injec-
4 Telemetry Ship fion. .
tNew Hampshire BDEFGHI Orbit tracking, telemetry reception, commands to satellite.
Tracking Station
sd. tKodiok BDEFGHI Orbit tracking, telemetry reception, initial acquisition on pass
Tracking Station 1, monitor events:in recovery sequence.
tHawaiian BDEFGHI Orbit tracking, telemetry reception and transmission of com-
Tracking Station mands to satellite.
Hickam AFB D Over-all direction of capsule recovery operations,
Oahu, Hawaii :
Tern Island BFGI Recovery capsule tracking.

Primary Tracking Stations (have command capability)

Se

*Equipment
— VERLORT
“ Several Purpose Panaiiie ond Support Equipment F. VHF FA/EM Telemetry Station
. : : eines ipment G. VHF Direction Finding Equipment
©. Control and Display Equipment nnessehank

1 . 1. VHF Telemetry Antenna:

NOTE: In addition to equipment Usted, oll stations have inter ond iatrotetios! communications equipment and
checkout equipment.”



—SEGRET-

Monthly Progress — MIDAS
Program Administration

% Lockheed Missites Gnd Space Company is con-
tinving Preliminary design of their Proposal for g
“simplified MIDAS satellite configuration. Funda-
mental to the “simplified” MIDAS concept is the
use of an orbital network of randomly distributed
satellites os opposed to the controlled distribution
previously proposed. System. analyses are being
conducted by LMSC, Aerospace Corporation, and
Uncoln Labs to determine the coverage capability
of the random network which will be evaluated in
the light of operational requirements to be estab-
lithed by the Air Defense Command. ($)

& During July, Air Defense Command personne!
were briefed on MIDAS coverage for various satel-
lite network configurations, The Purpose of these
briefings was to ‘sequaint ADC personne! with the
fundamentals involved to facilitate their analysis
which will result in determination of MIDAS opera-
tional requirements. (S} :

Flight Test Progress

* On 2 July the countdown of MIDAS Iil-went to
T:6 seconds when an ATLAS booster malfunction
caused the launch to be rescheduled to 10 July. The
second countdown proceeded to 1-0 when a mal-
function of the ATLAS umbilical caused the booster
@ngines to shut down immediately after ignition.
The maifunctions were corrected and MIDAS Ill was
successfully launched into orbit from Point Arguello
Gomplex 1, Pad No. 2 at 0811 PDT on 12 July,
Throughout ascent and orbit injection, booster and
satellite engine performance were extremely close
fe the predicted values. Table | shows the predicted
and altained orbital parameters. (¢)

Event Programmed . Actual
Apogee, nautical miles 1850 1891.2
Perigee, nautical miles 1850 1849.2
Period, minutes 161 161.5

TABLE |. COMPARISON OF PROGRAMMED AND
ACTUAL ORBITAL PARAMETERS FOR MIDAS tt,

«© A number of significant firsts in space technol-
Qgy were achieved or proven during the MIDAS Itt
flight.

1. The ability of the ATUAS/AGENA B (3672
Rounds orbital weight) to successfully establish a

SSLPR-20

Programmed, oriented, and stabilized 1850 ‘nm.
circular orbit with 0.0039 eccentricity,

2. AGENA B dual burn performance.
3. ATLAS D/AGENA B compatibility,

4. Measurement of the high energy proton spec-
trum of the Van Allen belt from 90° to the equator.
{S}

© Review of the flight data to date Indicates that
MIDAS Il was highly successful. Failure of one solar
array to extend fully caused a Partial loss of power

data. The flight test data re being reduced and
Gnalyzed to determine the cause of this difficulty. (S)

© Considerable payload data, including vehicle
systems information, were received through the fifth
orbital pass. These, together with tracking data,
indicated successful operation of second burn, re-
orientation, initial attitude stabilization and satisfac.
tory performance of the payload. (S)

© Vehicle “real time’ command control was suc-
cessfully accomplished on Pass number one and pass
number five Gctivating payload eperation and
telemetry. However, deficiencies were revealed in
the design of ground equipment and ground “com-
mand and control" operating procedures by the
inability to resoive the emergency created by receiv-
ing onty partial power from the solar array. The
inability to formulate and load the required “stored
Program" commands into the vehicle contributed to
the indicated early depletion of vehicle Power and
subsequent loss of Payload data link and vehicle
status telemetry. Vehicle status telemetry was re-
ceived on pass one as Programmed through stored
commands loaded prior to tounch, {s)

© The payload data received were still undergoing
analysis at the close of the report period, Analysis
thus far indicates no observed background, normal
ity, and verification of thermal ond mechan-
ical design. ($)

© Yan Al'en radiation measurement data required
28 a mission objective for MIDAS [it were still being
Provided by the High Energy Proton Density Experi.
ment (HEPDEX} at the close of the report period. The
HEPDEX equipment Power supply is independent of

SECRET B7


ENTIAL peed ok 2

.
Vision Se
Functions . T _
‘D” boosters 1 {_

dort thru orbital insertion . :

stance

-4 Flight I ° 7
. cOnvann nocareves Jemana, macteic
J- . —

eNones scostens OUIDANCE
ATTITUDE
uys7 a.m. RETRO ROCKETS FIRE wr Mena
: RE-ENTRY we tome hewn
17am, b. wane memonee

: vormat ORBITAL FUGHT ROGUE PARACHUTE OPENS

MAIN PARACHUTE DEPLOYED

i

i

i

i

I

i

i

i

: i
- aa
i

i

i

i

i

i

i

i



CONFIDENTIAL

Monthly Progress — RANGER
Lunar Test Missions
Flight Test Progress

© The first lunar test vehicle, RA-1, is now tenta-
tively scheduled to be launched from Pad 12 at the
Atlantic Missile Range on 24 August. Attempts to
launch. RA-1 during the July “window” were unsuc-
cessful. On 29 July, the countdown progressed to
1-27 minutes when a failure of base Power caused
the launch to be rescheduled. On 31 July, the count.
down was started but was discontinued at 1-232
minutes because of an inadequate supply of attitude
control gas in the spacecraft. The countdown in-
itiated on ? August was discontinued at T-15 minutes
when altempts to refill the ATLAS liquid oxygen tank
failed. The tank had been emptied to allow Lockheed
Personnel to resolve a problem in the AGENA
Propellant pressurization ground system. More
spacecraft problems developed during the 2 August
countdown and caused the launch to be called off
for this firing period. {c)

© Objectives for the first RANGER lunar test mis.
sion ore:

1. Demonstrate the ability of the ATLAS to
place the AGENA B vehicle at a Predetermined po-
sition and velocity in space as defined by the
guidance equation.

2. Inject the RANGER spacecraft into the pre-
scribed orbit using the ATLAS/AGENA B vehicle.

3. Demonstrate the compatibility of the ATLAS/
AGENA B/Spacecraft configuration,

4. Demonstrate the Capability of the Atlantic
Missile Range and DSIF (Deep Space Instrumentation
Facility) tracking, telemetry, and communications to
provide the required data and control of the
RANGER system during ail phases of the Operation.

3. Demonstrate the ability of the launch con-
trol equipment, the AGE, and the launch Procedures
fo launch the RANGER vehicle within severe time
limitations. (The launch’ window for RA-1 has been
limited to 34 minutes to avoid Overloading the hori-
zon sensor on the AGENA B vehicle.) (C)

Figure 1. RANGER ! on Atlantic Missile Range Stand
12. The lawach of this lunar test vehicle has been re-
scheduled for the next lunar firing period,



Program History
Initial studies were conducted by Industry in 1958
under SR187, Studies were continued in 1959 by
the Radio Corporation of America under ARPA
contract and Space Technology Laboratories under
Space Systems Division management. The STL study
was completed 21 December 1959 and the RCA
study 31 January 1960, both indicating SAINT
would be a feasible system of practical value to
the Department of Defense. Subsequently, the fol-
lowing actions have been taken:
1. AF System Development Requirement

No. 18 published ............21 April 1960
2. AFBMC approval of SAINT

Development Plan ste veeeee eee LS July 1960
3. Department of Defense approval

of Development Plan . . 25 August 1960
4. Air Force Development Directive .

No. 412 ...... steeeeeeee17 October 1960
5. Assigned Systems No. 621A. .31 October 1960

6. RCA chosen as Final Stage Vehicle
and payload contractor. , . .25 November 1960

SSLPR-20

—SEGRET-

7. Contract agreement with RCA 27 January 1961
8. Contract with RCA...........17 March 1961

Concept

Philosophy — The Philosophy for development of
the prototype vehicle calls for a step-by-step de-
velopment program with a conservative choice of
subsystems and emphasis upon reliability. Ground
tests will provide assurance of component capability
and reliability before flight.

Over-all System — Unidentified orbiting objects
will be acquired, catalogued, and the ephemeris
‘accurately determined through the facilities of the
Space Detection and Tracking System {SPADATS)
utilizing available acquisition and tracking equip.
ments. (It is anticipated that, for the ultimate Opera-
tional system, the capabilities of SPADATS will be
expanded to provide additional information . such
Gs target size, configuration and stability in orbit,
possibly within 12 hours after detection.) This infor-
mation will be relayed to a Defense Command
Control Center which will determine if inspection

E3


a

i xi
ALTITUDE (NAUTICAL Mi

ae

AY
\
\
\
midi ti L

PAYLOAD — 1000 LBS



—SPCRET-

is necessary. Should inspection be deemed neces-
sary, the ephemeris information will be used to
compute data which will be iriserted into the
guidance system of a SAINT vehicle. The vehicle
will be launched into an appropriate position at a
time which enables the final stage vehicle to go
into orbit with the unknown satellite and inspect It
at close ronge. This inspection data will be stored
in the payload for transmission Upon command to
ground stations. After reception by the ground
stations the data will be Processed, displayed and
evaluated, to determine the mission and intent of
the unknown satellite.

Vahicle — The SAINT system as Presently en-
visioned, consists of three stages including an
active “Final Stage” or rendezvous vehicle. Early
configurations of the SAINT vehicle will consist of
@ Series “OD” ATLAS booster, AGENA “B" second
stage, and a SAINT final stage vehicle. This con-
figuration is shown in Figure 1. Later fine! stage
vehicles having increased maneuvering capability
and additional sensors would be boosted with the
ATLAS/CENTAUR. The final stage vehicle (Figure 1)
will include a radar seeker, launch and homing
guidance system, attitude control, maneuvering pro-
pulsion and a payload. The payload will include
television cameras and various other sensors to
determine the nature of the target satellite and its
functional purpose. In addition the payload will have
@ storage and communications capability.

Feasibility Demonstration — Four flights launched
from the Atiantic Missile Range, ‘are planned for
the feasibility demonstration. The first flight is
scheduled in March 1963 with the subsequent flights
scheduled at three month intervals, The feasibility
demonstrotion configuration of the SAINT vehicle
will consist of a Series “D* ATLAS booster,
AGENA “B" second stage ond @ SAINT final
stage vehicle. The demonstration final stage vehicle
weighs approximately 2,400 Pounds. In this dem-
onstration (Figure 2), the final stage vehicle will
be programmed to rendezvous with an existing
satellite if one is availble in a three hundred to
five hundred mile easterly orbit. If such a satellite
is not available, a target satellite will be placed in
a 400 nautical mile, 28.8 degree inclination circular
orbit by a USAF SCOUT booster. Rendezvous will
be accomplished while under surveillance of a

E4 _ —~SEERET

eu,
Southeast Africa station and a TV image of the
target, in addition fo the telemetered data of final
stage vehicle performance, will be transmitted to the
ground station. The image and data will also be
stored and read out on command os the vehicle
passes over the Air Force Missile Test Center. For
the purpose of the feasibility demonstration Ten-
dezvous is defined as a closing of the final stage
vehicle with the target satellite to within 50 feet
and a relative velocity of less than one-foot per
second. Station keeping will be maintained for one
orbital period.

Program. This effort will distinguish certain long lead
type items on which development action must be
Initiated and provide further refinements to the
system, Included are extension of the maneuvering
Capability of the vehide. into 4,000 nautical mile
orbits with the Necessary station keeping and in-
spections of multiple targets as well as more exotic
sensor capability. For example, a sensor capable
Of detecting a nuclear warhead Is most desirable.
Effort is currently underway to proceed with the

Space Systems Division management of this program
is based upon the associata contractor structure
composed of a First Stage contractor, Second Stage
contractor, Final Stage. Vehicle contractor, and Sys-
tems Engineering and Technical Supervision con-
tractor (Aerospace Corporation). Military support is
Provided by the Space Detection and Tracking Sys- ~
fem through the Air Force Command and Contro!
Development Division, and by the 6594th and
6555th Missile Test Wings.

Facilities

The demonstration Program will utilize existing
launch, tracking and date reduction facilities inso-
far as possible. However, some edditional ground
Support equipment will be required at the Air Force
Missile Test Center and at the Southeast Africa
tracking site,

SSLPR-20



CONFIDENTIAL

Monthly Progress — DYNA SOAR

Program Administration

© A decision by the System Program Office on the
activation of DYNA SOAR test sites was announced
on 13 July. The work in each test crea will be
integrated and supervised by a designated “area
administrator.” The area administrator for Atlantic
Missile Range launch complex No. 20, as recom-
mended by the Space Systems Division, is the Martin
Company. (U}

. A DYNA SOAR Management Council Meeting
was held at Wright-Patterson Air Force Base on 7
July. Subjects discussed included the full Step | con-
tract negotiation schedule, the Present design status
and a possible program acceleration. {U)

© PERT networks were received from the booster

ssociate contractors. After being reviewed, these
will be integrated into a system network. (U}

® Statements of work for the entire DYNA SOAR
Step 1 Program have been written for oll associate

contractors. These documenis cre now being re- _

viewed by the System Project Office and the Space
Systems Division. {U}

© Letter Contract AF 04(647}-894 between the
Department of the Air Force and the General Elec-
tric Company Defense System Department for re-
search and development on the DYNA SOAR Step |
booster radio guidance, was fully consummated and
distributed to the contractor on 19 July. (U)



~SHGRET

the R&D radiometer. Modifications are also being
made to:

1, Increase the reliability of the solar array
extension mechanism.

2. Provide “real time” commands for operation
of the “S" band tracking beacon and vehicle status
telemetry (FM/FM) readout.

3. Provide for transmission of selected, critical,
vehicle status telemetry date over the SAPUT telem-

etry system.

4. Provide additional instrumentation of the
solar array.

Vehicle changes are currently being implemented
at the Vandenberg Air Force Base Missile Assembly
Building. Satellite control procedures are being
changed to provide more positive control and to
improve backup procedures for operation if primary
operational modes fail. MIDAS IV is scheduled for
delivery to the launch pad on 3 September. (S)

After completing the flushing operation at the
Santa Cruz Test Base, the MIDAS V vehicle was
fetumed to the Lockheed Sunnyvale facilities and
started integrated systems tests on 19 duly. Systems
tests will be conducted in a manner to comply with
@ pad ready concept that is expected to reduce the
vehicie time in the Missile Assembly Building from
28 to 6 days. {S}

Infrared Scanners

¢ MIDAS Series Ill payload subassemblies com-
pleted acceptance tests at the Aerojet-General facil-
ity and data from. these tests are being analyzed.
The complete systems test of this payload is cur-
tently being accomplished. The first MIDAS Series Il)
payload is scheduled for flight on MIDAS VI in early
1962, (S} :

Facilities

© Construction on Point Arguello Launch Complex
No. 2 was started on 1 duty. All major items required
during construction have been ordered by the con-
tractor. Excavation for faunch stand No. 3 is now

., under way and construction of the complex main

Gccess road and the access road to Stand No. 3 is
Progressing satisfactorily. Trailers to be used as “on
site” offices by Navy, Alr Force and contractor
supervisory personne! have arrived. initiation of a
Critical Path Scheduling (CPS) Program as a man-
agement tool for construction of this complex is
believed to be the first use of this technique within
the Air Force during facility construction. (U)

* Modification of the Vandenberg Air Force Bose
Technical Support facilities is in Progress with bene-
ficial occupancy scheduled for 30 August. The sec-
ond increment of this package is now scheduled for
contract award on 7 August, within limitations of
FY 61 fund svailability. The final increment of the
modification effort will be awarded upon receipt of
FY 62 Military Construction Program funds. (U}

¢ A shortage of funds has delayed award of the
Construction contract for modifications to the North
Pacific, Donnelly Flats, readout station. Temporary
deferral of a portion of the modifications will be
required to allow award of contract for the most
critical requirements. A joint USAF, Alaskan Air
Command, and Space Systems Division effort is in
Progress to resolve this problem. {U)

@ A government to government agreement provid-
ing for use of RAF Station Kirkbride as a MIDAS
readout station, construction of technical facilities,
and..operation and maintenance of the station by
the United Kingdom was consummated on 19 July.
(s)

* Submission of final ptans for the construction of
the Ottumwa, lowo, MIDAS Tracking and Controf
Center technical facilities is scheduled for 21 August.
(u)-



® Studies and technical d

@ Launch complex and
© Systems development
© Safety program

g PLAN 3?

sui Ha
iy Ha He
HL ih I fli; an
ainnllntal
BEL ati
ELUTE
Bee LTH
aire e
FEHB
putt i ALE
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HEL

Trajectory Outline fq

a
CAPSULE SEPARATION

INER ENGINE CUTOFF



Technical Progress,

| @ The AGENA B vehicie scheduled’ to, be flown on
the second RANGER flight has been placed in stor.
age ot the Lockheed Sunnyvale facility awaiting
shipment to the Atlantic Missile Range in August. (u)

© in early June the delivery date for ATLAS 117D
was established for August. This booster will be
used for the October Lunar Test Mission (RA-2). A
review of the ATLAS Planned Systems Schedule,
dated 20 June, revealed a one month delay in the
delivery date. The Space Systems Division is making
© concentrated effort to recover the schedule for
. this booster, (C}

CONFIDENTIAL

Lunar Impact Missions

Technical Progress

© The first Lunar Impact AGENA B vehicle has
entered final systems test. Following completion of
these tests the vehicle will be shipped to Santa
Cruz Test Base for static firing. (U)

Facilities

© Design of modifications to Complex 75-1 at
Vandenberg Air Force Base in support of NASA -
polar launch requirements is Progressing on sched-
ule. Final plons were submitted on 31 July. (U)

SSLPR-20


SATE LLITE

SYSTEMS

SATELLITE SYSTEMS

DISCOVERER
MIDAS
BIOASTRONAUTICS
BLUE SCOUT
SAINT

VELA HOTEL



In Aprit 1960, Amendment No. 5 jo ARPA Order
No. 54 reoriented the Program. The research and
development effort Previously directed foward
Providing o round-to-satellite-to-circraft UHF com-
munications capability for the SAC strike forces was
cancelled. A single integrated ADVENT Program for
the development of a 24-hour microwave communi-
cations satellite replaced the former STEER, TACKLE
and DECREE Programs;

On 15 September 1960, the Secretary of Defense
transferred over-all Monagement responsibility for
the ADVENT Program from ARPA to the Department
of the Army. The development responsibilities of
SSD and USASRDL were retained essentially status
quo. The Army was given responsibility for funding
and for over-all systems engineering to provide
guidance and a basis upon which detailed design
data can be evolved by SSD and USASRDL.

PROGRAM OBJECTIVES

The primary ADVENT objective is to demonstrate the
feasibility of achieving a military system for micro-
wave communications {surface-to-surtace) employing
satellite repeaters in 24-hour equatorial orbit. The
feasibility of placing @ satellite in Predetermined

SECRET

Position in a 19,300 noutical mile equatorial orbit |
mutt be demonstrated. The feasibility of being able
fo stabilize the satellite, control its attitude and orbit,
and keep it on station within the required tolerances

gram Plan is based Upon the design of a single con-
figuration of a final stage vehicle compatible with
launching by either AGENA "B” or CENTAUR second
stage boosters.

The ADVENT Program will consist of the following
flight tests, launched from the Atlantic Missile Range:

Phase One. Three ATLAS/AGENA “5° flights,
nominal 5,600 nautical mile orbits, beginning March
1962,

Phase Two. Two flight tests, using payload space
on NASA ATLAS/CENTAUR research and develop-
ment flights numbers 9 and 10, April and June 1963,

Phase Three. Five ATLAS/CENTAUR flights
launched into 19,300 nautical mile equatorial orbits,
beginning Juty 1963,

launch Schedule

62

63 64

ARMY

NASA ARMY

ATLAS/AGENA “BY

ATLAS/CENTAUR

G2 ” — _ sSeper—

SSLPR-20


LAUNCH

VEHICLES

MERCURY
RANGER-NASA AGENA “B”
TRANSIT



ORBIT INCLINATION ANGLES
|r BOOSTER IMPACT
3 INJECTION INTO ORBIT

. _ SS”
Figure 3. Zreicel TRANSIT launch trajectories showing Wahi path, Sooster iespact arees, ond orbital injection potats,
Orbital Performance Achievement of program Ground Support and Tracking Stations The

objectives is based primarily on measuring the Navy Bureau of Weapons Payload contractor Ppro-
“doppler shift of satellite transmitted radio signals, vides a system of Payload tracking stations which
During the first three months of flight, the four trans- obtain information for Precise orbit determination,
mitters will be operated to obtain experimental con- These stations are located in Maryland, Texas, New
firmation of the theoretical mathematical relationship Mexico, Newfoundland ‘and Brazil, First and second
between the frequency and the refractive index of stage tracking and telemetry, and second stage
the ionosphere. Studies have shown that refraction guidance will be Provided by the facilities of the
effects on the doppler shift can be eliminated by Atlantic Missile Range, A mabile downrange tracking
using the transmission from two satellites. After four station at Punta Arenas, Chile, will receive tel
months of tracking the satellite by measuring the data and tracking information during the last Por.
doppler shift of the satellite radio signal, the exact tion of the second stage Ablestar coast, re-ignition
Position of the satellite ot any point in the orbit and second bum, Payload spin-up and Payload
should be known. Using known orbital Positions, injection pesiods, This station was located in Erding,
ships ond aircraft can then use satellite signals to Germany, for the TRANSIT 1B filght, Punta Arenas,
make analogous’ computations to establish accurate Chile, for the TRANSIT 2A and 3A and Pretoria,
position, . Union of South Africa for TRANSIT 3B,

SSLPR20 CONFIDENTIAL . Ma


Stat

was initiated on the 32nd pass (two days on orbit)
at 1905 PDT on 9 July. All events occurred as pro-
grammed and the capsule followed the predicted
descent trajectory. The capsule wos sighted north-
west of Hawaii and aerial recovery was accom-
plished. This was the fourth DISCOVERER capsule
recovered by the airborne forces, two other capsules
have been recovered from the sea. Following cap-
sule ejection, the AGENA satellite reoriented: to its
normal “on-orbit” attitude and operated satisfac-
dorily for the remainder of its battery life. (C}

DISCOVERER XXVI Experiments

© As part of the continuing program designed to
‘measure the space environment and determine radi-
‘ation effects on various materials, nearly 45 pounds
<of instruments and specimens were carried on the
‘DISCOVERER XXVI satellite vehicle and its capsule.
‘The capsule carried “poker chip" samples of iron,
‘nickel, ytterium, titanium, magnesium, lead and bis-
muth. Some of the somples were returned to the
‘Air Force Geophysical Research Directorate for
‘evaluation and the remainder are being analyzed
by Lockheed scientists. Three canisters were also
‘recovered with the DISCOVERER XXVI capsule. One
‘contained various dosimeters and was returned to
the Air Force Special Weapons Center. Another
contained inert biological materials (cellulose prod-
ucts} and was transmitted to the Space Systems Divi-
sion for analysis. Various metal and film samples
were included in the third canister to provide in-
formation on the effects of space radiation on
Photographic materials. Analysis of the specimens
is in process. (S}

© The non-recoverable Geophysical Research Di-
rectorate equipment, which was mounted on’ the
module that replaces the engine access door, in-
cluded two atmospheric density gages, two micro-
meteorite detectors, a cosmic ray monitor and tem-
Perature probes. During the flight, data from these
instruments were telemetered to tracking stations
via the AGENA telemetry system. The information
was sent to the Geophysical Research Directorate
for reduction and analysis. Inspection of the raw
data indicated that all instruments operated satis-
factorily and the data obtained appeared to be
valid. (U)

DISCOVERER XXVII Launch

@ DISCOVERER XXVII was lounched from Vanden-
berg Air Force Bose at 1535 PDT on 21 July. A
DM-21 booster pitch oscillation, evident immediately
after launch, became severe after approximately
one minute of flight. The vehicle apparently broke
up ot this time. A destruct command was sent at
T + 95.1 seconds. Three minutes after launch the
DISCOVERER satellite S-band beacon signal was
lost and approximately two and one-quarter min-
utes later, booster telemetry was lost. The DISCOV-
ERER satellite reached an altitude of only 35,000
feet and impacted twelve to fifteen miles down-
range. Ships from the Pacific Missile Range located
main parts of the DM-21 booster, but were unable
fo recover the parts connected with the failure. (C)

Future Flights

© The next three DISCOVERER satellites will carry

recoverable capsules with recovery planned after
between one to four days in orbit. (C)

—<SHCRET- An


Project MERCURY represents the transitional threshold
between this nation’s cumulative achievements in
space research and the beginning of actual space
travel by man. The primary program objective is to
Place a manned satellite into orbit about the earth,
and to effect a controlled re-entry and successful
recovery of the man and capsule. Unmanned bal-
listic trojectory and unmanned orbital flights will be
vsed to verify the effectiveness and reliability of an
extensive research program prior to manned orbital
flights, The program will be conducted over a period
of approximately four years. The initial R & D flight
test was accomplished successfully in September
1959. The total program accomplishment is under
the direction of NASA. The primary responsibility
of Space Systems Division to date consists of: (a) pro-
viding 15 ATLAS boosters modified in accordance
with program objectives and pilot safety factors,
and (b) determination of trajectories and the launch-
3 ing and controt of vehicles through injection into
orbit,

Major contractors participating in the Space Systems
Division portion of this program include: Aerospace
Corporation, systems engineering and _ technical
direction; Convair-Astronautics, modified ATLAS
boosters; GE/Burroughs, ATLAS guidance equip-
ment; and Rocketdyne, engines. Ail of these com-|
panies also participate in launch operations, special
studies and engineering efforts peculiar to Project
MERCURY requirements.

The MERCURY astronomical sombot (8)
with the x for Reliability wilt be
tached to ti 6 components wsissile
items which have been selected and accepted

fo eee boosters identified for Peojacs



—€ONFIDENTIAL—

RANGER Program

‘a

a

Ef

Lunar Test Missions

The RANGER Program is a series of five deep space
probes to be launched from the Atlontic Missile
Range (AMR) on the ATLAS/AGENA B booster sys-
tem. Jet Propulsion Laboratory (JPL) under contract
from the National Aeronautics and Space Adminis-
tration {NASA} is responsible for the missions and
Providing the spacecraft hardware. The mission of
the first two RANGER launches wilt be an inter-
planetary investigation in support of the follow-on
lunar impact mission. The orbit will be highly ellipti-
cal (near escape velocity) and have.an apogee of
approximately 625,000 nautical miles. The space
craft is planned for one orbit with approximately
a 50 day period.

Lunar Impact Missions

The remaining three launches will impact the surface
of the moon and transmit scientific information back
to the earth. Experiments are designed to measure
seismographic disturbances, temperature changes
and impact acceleration. These Ranger spacecratts
will also have the capability of accomplishing a
mid-course maneuver to correct for minor errors in
the trajectory.

La CONFIDENTIAL —

The ATLAS/AGENA “B" booster system will include
the standord ATLAS “D* first stage booster with
GE Mod I! G guidance system. The second stage
will be a modified AGENA B second stage booster
similar to those used in several Air Force space
Programs. The only major change to be incorporated
for these missions is the capability to separate the
RANGER spacecraft and fire @ retro rocket to pre-
vent the AGENA “B” from hitting the moon. Lunar
impact of the AGENA “B” is not desired due to
its unsterile condition.

The RANGER Program will be the initial lounch by
NASA of the Air Force developed AGENA “'B” sec-
ond stage. Maximum effort is being given toward
using the same components that have been flown
on Air Force missions.

Scientific Satellite Program

NIMBUS is a 650 pound earth oriented stabilized
satellite to be placed in-a “high noon” circular orbit
at 600 miles altitude. This satellite is intended to
serve as a platform for experiments designed to ex-
plore the meteorological Process of the earth's at-
mosphere. Experiments include full picture coverage
of the clouds over the entire earth, electromagnetic
radiation maps of the earth, and the atmosphere
Ground the earth and other experiments to deter-
mine the effect of the sun on the atmosphere.

A total of five NIMBUS satellites will be put into
orbit by the THOR/AGENA B booster from Vanden-
berg Air Force Base. The first launch is scheduled
for June 1962 with subsequent launches every six
months. The booster system wil! be the same as used
on Topside Sounder and the Communication Satel-

lite with slight modification to accept the larger
payload.

SSLPR-20



PROGRAM HISTORY

The MIDAS Program was induded in Weapon’ System
TI7L when WS 117k was transferred to the Ad-
vanced Research Projects Agency. ARPA. subsequently
separated WS 1171 into the DISCOVERER, SAMOS
and MIDAS Programs, with the MIDAS objectives
based. on an infrared early warming system. The
MIDAS {Missile Defense Alarm System) Program was
directed by ARPA Order No. 38, dated 5 November
1958 until transferred to the Air Force on 17 Novem-
ber 1959. The Air Foice directed that the program be
continued under the technical guidanca of the ARPA
Order and approved the MIDAS R&D Development
plan dated 15 January 1960. This plan was a “mini-
mum essential” program directed toward the satellite
vehicle and proof of the feasibility of infrared.detec-
tion capabilities. It Provided for ten test launches,
two from the Aifantic Missile Range and eight from
the Pacific Missile Range. ‘Subsequent authorization
was obtained to utilize two DISCOVERER flights
(designated RM-1 and RM-2) to carry background
radiometers in support of MID; a

A program of complete system development, includ-
ing the ground ‘environment of MIDAS, hos been
submitted fo the Department of the Air Force and
hes been Spproved in principle and objective.
Authorization has been received to initiate action
implementing the plan with reconsideration for ap-
Proval to be ‘accomplished subsequent to a success-
ful test launch in 1961,

TECHNICAL HISTORY

The MIDAS infrared early warning payload is engi-
neered to use a standard launch vehicle configura-
tion. This consists of on ATLAS missile as the first
stage and thie AGENA vehicle, Powered by a Bell
Aircraft rocket engine as the second, orbiting stage.
The final configuration Payload weight will be
approximately 1,000 pounds,

The first two R&D flights used the AGENA “A” and
ATLAS “D" vehicle ‘Programmed to place the pay-
load in a circular 261 nautical mile orbit. Subse-
quent R&D flights utilize the ATLAS “D"/AGENA
“B" configuration programmed to Place the pay-
load in a circular 2,900. nautical mile. polar orbit,



HEADQUARTERS
BALLISTIC SYSTEMS DIVISION
AIR FORCE SYSTEMS COMMAND

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

SSLPR : 24 August

Monthly Summary of
SPACE SYSTEMS DIVISION
ACTIVITIES
JULY. 1961

FOREWORD

During July, two space vehicles were launched successfully, contributing significantly
to the progress of satellite system Programs. DISCOVERER XXVI was placed in orbit on
7 July. Two days later, on its 32nd orbit, the satellite capsule was retuned to the
atmosphere and aerially recovered. On 12 July, the ATLAS-boosied MIDAS lit was
placed into a circular 1850 n.m. orbit. Payload data were received. Flight test records
which have been reduced indicate that MIDAS II was successful. However, failure of
one solar array to extend fully caused a partial power loss. Analysis is underway to
determine the cause of this difficulty.

4/0. J. RITLAND ;
Major General, USAF
Commander

—CONFIDENTIAL- SSLPR20





Figure 4. MIDAS Ii! TRAJECTORY

Technical Progress

Boosters

¢ ATLAS 105D is presently “on stond” at Point
Arguello and is being readied for MIDAS IV. (5)

Second Stage Vehicles

* The MIDAS IV vehicle (1202) completed opera-
tions at the Systems Test Complex, was shipped to
Santa Cruz Test Base for flushing, and arrived at
the Vandenberg Air Force Base Missile Assembly

Figure 3: Early morning photograph opposite page,
of MIDAS Ii! at Point Arguello, Pad No. 2. This fight
demonstrated the ability of the ATLAS D/AGENA B

combination to establish a programmed, orlanted ond
stabilized 1850 navtical mile rculor orbit with a
9.0039 eccentricity. .

SSLPR20 —=SEGRET.

Building. During the inspection at the Missile Assem-
bly Building, pin hole leaks were detected in an
oxidizer fill line weld. The part was x-rayed and
weld porosity was determined to be the cause. The
defect was corrected. {5}

© During July the Air Force Space Systems Divi-
sion initiated action.to effect equipment changes to
MIDAS IV, which will allow a higher orbital alti.
tude (2050 n.m.) for participation in the Westford
experiment. These changes include the deletion of
the vacuum bearing tester, all Geophysical Research
Directorate equipment, the APL doppler equipment
and its power supply, the Speidel tape recorder and

Bll



a foreword to...

.

_ SPACE

TABLE OF CONTENTS

PROGRAM
DISCOVERER ..............
MERCURY . eee e eee e eee ee ens K
RANGER-NASA AGENA “B"’
TRANSIT ......... 0.000005
SPACE BOOSTERS



SSLPR-20

Figure 1. Two stage ANNA vebicle,

CONFIDENTIAL

rit ANNA

Second Stage — ABLESTAR (AJ-10-104)

\ Thvvet (vacuum) 7900 pounde
Specific impuise (vacwm) 277 seconds
Burning time 296 seconds
if tear rT

ine ise
First Stoge — DM-21A
Theust {200 level) 152,000 pounds
Specific impulen (vou level) 247 spconds
‘Burning time 163 seconds
Propellant aay Oxygen

Program Description

Project ANNA is the tri-service geodetic satellite
Program. The program is designed to satisfy the
Primary military (Army, Navy, Air Force) and scien-
tific (NASA) requirements in geodesy. Th: Navy has.
‘over-all program management responsi ity and is
also responsible for satellite system management.
The Space Systems Division (SSD) was assigned the
tesponsibility for booster system management, which
indludes providing the booster vehicles, integrating
Payloads to the vehicles, and being responsible for
flight operations from launch through attainment of
orbit. On 4 April 1961, the Navy officially directed
the Space Systems Division to proceed with plans for
launching the first ANNA satellite on 5 December
using the THOR Ablestar (Figure 1) vehicle Previously
purchased for TRANSIT SA.

Payload Description

The ANNA payload (Figure 2) is a 36-inch diameter
sphere with a bank of solar cells encircling the
package at the equator. The satellite contains an
Air Force High-Intensity Pulsed Gos Discharge Lamp
for optical measurements, a Navy (TRANSIT) dop-
pler beacon for doppler measurements, and an
Army SECOR Transponder for radio ranging data.
The basic payload structure is the same as the
TRANSIT Navigational Satellite. The poyload weight
is 325 pounds. The payload contains high magnetic
Permeability rods which will reduce the satellite spin
to zero by hysteresis damping ofter a few days on
orb High tntensity, Pelsed Gos
Discharge Lamp (Ais Force)



SUBSYSTEMS, and SPACE RESEARCH flight opera-
tions. This Fesponsibility will include the coordination
Qnd establishment of Agreements of responsibilities
with payload agencies, both government and on-
tractor, for the integration of the Payloads and
boosters; the monitoring of flight peration plans,
objectives, schedules, accomplishment, and results;
the funding action for the booster support; the plan-
ning for launch facilities and launch personnel; the
Procurement of booster vehicles and other equip-
ment; and the over-all coordination required for
execution of the BLUE SCOUT booster support
Program,

Missions

The Application Phase missions for the BLUE SCOUT
Program, some of which Gre firm while others are
in the Planning stage, are os follows:

SAINT: Two BLUE SCOUT vehicles required, first
faunch from Atlantic Missile Range January, 1963,

ASSET: A requirement from Aeronautical Systems
Division for seven BLUE SCOUT vehicles to be used
in investigations of the Gerodynamic and thermody.

SSLPR-20

namic properties of boost-guide vehicles. The first
launch is scheduled from Atlantic Missile Range in
mid-1962 with o three-month launch interval.

BAMBI: Four BLUE SCOUT vehicles required, first
launch from Pacific Missile Range in mid-1962, inter-
val between launches of three months, :

TRANSIT: Six BLUE SCOUT vehicles required, first
launch from Pacific Missile Range in mid-1962, inter-
val between launches of three months.

PROBES PROGRAM: A requirement from the Office
Of Aerospace Research for thirty BLUE SCOUT ve-
hicles indicated FY62 funding will support @pproxi-
mately fifteen BLUE SCOUT vehicles. A requirement
of approximately fitteen BLUE SCOUT vehicles per
year for the period 1962-1970 is expected.

BEANSTALK: This Program is under the manage-
ment of Electronics Systems Division, Present informa-
tion indicates that ten BLUE SCOUT JUNIOR vehictes
will be required by Electronics Systems Division
for launch operations from Pacific Missile Range
during 1962,


0:

i a je i orbit which bas ¢ 200 ue. perigee and 4 50,000 wim.
Figure 2.,VELA HOTEL trajectory showing the elliptical transfer whi « wim. perigee «

0m ihe frst orbit one payload wil be sjected. om tbe wash orbiy, the second os
See orb appretimatde 150" oer sy oe pata ,

be fired and placed

gamma ray, and neutron detectors and Geiger.
Mueller tubes. Each spacecraft will contain @ pro-
Pulsion unit capable of transferring the spacecraft
into a minimum circular orbit of 50,000 nautical
miles, The propulsion unit of one spacecraft will be
fired at first apogee and the second spacecraft will
be transferred at a later apogee such thet the
spacecraft will initially be 140° apart in orbit, The
spacecraft will be designed to have an operating
life of six months with redundant telemetry transmis-
sion capgbilities in range of 75,000 nautical miles.

The vehicle will be launched from the Atlantic
Missile Range at an azimuth of approximately 110°.
After AGENA B separation from the ATLAS D, the
AGENA B will program through two bums with final
cutoff over Australio. A spin table on the AGENA B
will then spin and separate the tandem payloads,
The two spacecraft will then separate such that at
apogee they will be several miles cpart. The pre-
viously described transfer sequence will then be
initiated.

Simuttaneous tracking of the two spacecratt will be
carried out by the SSD world wide tracking net.
Data will be collected at Sunnyvale ‘Satellite Test
Center, punched on tape and shipped to the AEC
at Albuquerque, New Mexico for reduction and

analysis,

In addition to the major high-altitude portion of the
VELA HOTEL Program, several Discoverer piggy-
back low altitude polar orbit flights ore being
accomplished which will obtain background radia-
tion data below the Van Allen belts. These flights
Qs proposed will carry Lawrence Radiation labora-
tory experiments consisting of X-ray, gamma ray
and neutron detectors, PENG (proton-electron-
fneutron-gamma ray) detectors and solid state
spectrometers.

The first of these launches will occur in August 1961.
The AEC is also initiating, os a separate but re-
lated project, a piggy-back flight Program aboard
Rangers {Lunar probes}, NASA Scouts and Mariners -
{Venus probes).

Fa —CONFIDENTIAL- SSLPR 20



ORBITING SPACE CAPSULE



AQ


6t 62

MISSION
LEGEND
© LUNAR TEST VEHICLE (ATLAS) © COMMUNICATION SATELLITE {THOR}
Q@ LUNAR IMPACT {ATLAS} ‘# METEOROLOGICAL SATELLITE (THOR)

O SCIENTIFIC SATELLITE (THOR) BACKUP VEHICLE (THOR)

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

SSLPR-20


Hi

b 9- ;

H2

Figure 4. Location of ANNA tracking statlows,

CONFIDENTIAL

SSLPR-20


-CONFIDENTIAL

Program History—Competition for the DYNA SOAR
study contract was initiated in 1958 and resulted in
the Boeing Airplane Company and the Martin Com-
pany being awarded the follow-on contract fo more
fully define their proposed appreaches. In November
1959, following review and evaluation of the
Boeing/Martin detuiled studies by a Source Selection
Board, it was announced that Boeing had been
selected as the glider and system integration prime
contractor, with Martin furnishing modified TITAN
ICBM's for booster support. The concepival phase of
DYNA SOAR concluded with a study program re-
quirement known as Phase Alpha. The objective of
this study was to reaffirm Proposed glider design.
In Aprit 1960, Phase Alpha was completed and re-
sults were presented to the Department of Defense.
On 9 May, formal approval of the DYNA SOAR Step
! Program was received by AFBMD/BMC from
WADD/ASC.

During the period covering program go-ahead to
the end of CY 1960, efforts on the Program were
concentrated on design refinements to TITAN | and
Possible increased booster performance to accom-
plish program .objectives. Studies on booster capa-
bilities revealed many favorable factors on cost, time
and expanded objectives by use of the XSM-68B
(TITAN Ii) as the booster. Results of these studies
were presented to Headquorters USAF and the
Department of Defense. Headquarters USAF directed

FIRST — SECOND STAGE SEPARATION

use of TITAN Il as the SYSTEM 620 DYNA SOAR
Step | Booster. Formal direction to use TITAN fl
was received by AFBMD/BMC from WADD/ASC on
13 January 1961. Effective April 1961, the symbols
for AFBMD/BMC and WADD were redesignated SSD
and ASD, respectively.

Program Objectives—The DYNA SOAR Program will
explore the possibilities of manned flight in the
hypersonic and orbital realms, The Program will
Proceed in three major steps from a research orid
test phase to on operational military system. In Step
|, a full scale, minimum sized manned glider will be
developed. A modified version of the TITAN II Ic8M
will boost the glider into hypersonic flight at veloci-
ties up to 22,000 ft/sec and Permit conventional
landing at a predetermined site. In Step Il the glider
will be tested, using a more powerful booster to
achieve orbital velocities. This phase may ‘be ex-
Panded into cn interim operational Weapon system
Providing all-weather reconnaissance and satellite
interceptor capabilities, The objectives of Step If are
to test vehicle performance between 22,000 ft/sec
and orbital velocities; and to gather re-entry data
from various orbits; and to test military equipment
and man-machine relationships. Step {li will provide
Gn operational weapon system with a vehicle that
will operate primarily in a hypersonic glide, be able
to maneuver within the atmosphere, and be able to
make a conventional landing at a predetermined


AGENA “B”’