ENTER ELLIPTKAL ORBIT

PERIGEE OF va
COAST ELLIPSE. °

IST. = \ ‘ vn . y

SEPARATION &
‘mw “A T COAST

me

Figure 2,
Launch-to-orbit trajectory for flights 3 and subsequent, Opti
mum ATLAS bean ee 5, tadio-inertial system,

AGENA cent (coast, burn, coast, second burn) provides

ger jets

Figure 3,

Propoted MIDAS s5stem. Four satellites spaced equidistant in each of
10 orthogonal planes at 2,000 n.m. altitude. Provides maximum cov-
erage of USSR with minimum number of satell

180° coast.
v oN ott ef .
AGENA 7 ‘

ame SN

attitude reference, Also Soverns velocity magnitude and
divection by inertial guidance system monito by horizon
scanner, Orbital attitude maintained by reaction wheel and

PROGRAM HISTORY

The MIDAS Program wes included in Weapon
System 1171 when WS, 1171 wes tronsferred
to the Advanced Research Projects Agency.
ARPA subsequently separated WS 117 into
the DISCOVERER, SAMOS ond MIDAS Pro-
grams, with the MIDAS objectives bosed on
an infrared feconnaissonce system. The
MIDAS {Missile Detense Alarm System) Pro-
gram was directed by ARPA Order No. 38,
dated 5 November 1958 unt! transferred to
the Air Foree on 17 November 1959. A ten
launch development pian for MIDAS (WS-
239A) has been approved. This R&D Program
should make possible the achievement of on
Operational system by 1963,

Ney

[UO

WDLPM-4-222



my SECRETE

tatellite trighty, Dire rags below shaw
complete turmitace faghs tebule tight)
sud AGENA “B" asoud tnsee iobucle
lefts.

| Fegine 1, Aste’ cusception ul MIDAS

SECOND STAGE “a

Weight
Inert

1834 1763
Paytecd equipment 3,246 1441
Orbital 4700 1404
—_ tmpulte Propelioats 6.423 12,950
Fuel (UDMH)
Onidiaer (RPNA)
Other

GROSS WEIGHT jhe)
Engine VAR Ba-S XLR81-80-9
Theust, tes. (vac) 1$600 16,000
Spec. set. (vee) v7 290
Bern Time. vec. 120 20

Restor! Provisions No Yes

738

—
11408 WN?

Pressurization} Command Antenna

Hydroulic P
Ns Bottte vGreic Peckoge
\ “S$ Band Beacon:

Oxidizer Tank Fuel Tonk

AGENA
VEHICLE

*s, ATLAS
BOOSTE!
“G" Paylood
Solar Array Infrared Sensor System:
Main Engine :
GOOSTER—ATLAS 108M
Weight—Wer 15,100
MIDAS, Configuration Il, AGENA “B" Satellite Feet, RP.1 74,900
Onidizer (10%) 172.300
GROSS WEIGHT tbs) 262,200
Engine—MA-2
‘Taeust (Ibs, vee.) Boout 356,000
Susteiner 82,100
Spee. imp. (rec. voc.) Boost 106
Sustoiner 310

a [«]e a|=/3/

| H, Bottle (Propeliant VHEPUHE



60
VIF IMIAIMI JIvJAISIOINIOL UF
. yyy
VEHICLE
CONFIGURATIONS | ATLAS "D'/AGENA "A"

6!
AlMIJ/JJATS/OUN/D | JF |M]a iM] uj u/AalsjoIN| ©
2]2

Huyty2

ait

ATLAS "D'/AGENA "B"

SAMOS Launch Schedule

Monthly Progress—-SAMOS Program
Technical Progress
Second Stage Vehicles

@ The AGENA vehicle for the first SAMOS flight
was delivered to Vandenberg Air Forcé Base follow-
ing successful captive hot firing tests and completion
of dynamic systems testing at Santa Cruz Test Bose.
The vehicle is proceeding on schedule through modi-
fication and subsystem bench testing in the missile
assembly building. Although impeded by parts short-
ages and the recent strike, schedules are being main-
toined to cssure transfer of the vehicle to the launch
pad by 19 August.

@ The AGENA vehicles for the second and third
flights are currently in the modificotion and subsys-
tom test phases at the systems test area. Both vehicles
are behind schedule because of the recent one-
month strike and ports shortages. Efforts to recover
current schedules are dependent upon continued
availability of airborne communications equipment.
The second flight vehicle is short the UHF narrow-
band ond wide-bond dato link transmitters. A firm
delivery date is not available from the narrow-band
transmitter contractor; however, a backup flight unit
was received on 25 July. Delivery of « wide-band
transmitter to replace the one used in the first flight
vehicle has been made. The third flight vehicle has

eight major oirborne communications equipment
shortages. Since delivery of these units is not
expected before mid-August, it is doubtful that the
schedule con be recovered.

© The first AGENA “B" vehicle is in the major
subassembly phase of manufacture. Assembly was
delayed by the recent strike, but every effort is
being made to regain the schedule.

Visual Reconnaissance Systems
Visual Reconnaissance Systems payloods ore being
developed in o minimum number of configurations
to attain readout and recovery mission objectives.
The design and purpose of each configuration is
as follows:
Readout:
E-1—Component Test Payloads
E-2—Steeroble Reconnaissance Payload
{with 20-foot ground resolution)
Recovery:
£-5—High Resolution, Steerable, Recoverable
Payload {with 5-foot ground resolution)
E-6—Genero! Area Coverage, Recoverable
Payload (with at least 20-foot ground
resolution)
Payloods
E-1 Payloads—Checkout and testing of the E-1 pay-
load ore progressing satisfactorily at Vandenberg
Air Force Base.

72 as



ENTER ELLIPTICAL ORBIT
PERIGEE OF

7 180° COAST.
aN a ee
AGENA XN
1ST. BURN. \ 7
\ 150 N. Mi,

SEPARATION &
“mm a T COAST

|
aN

She bi for fights 3 and subsequent, F;
'ach-to-orbit trajectory for flights 3 and sul sequent, From

boost through se, i ided

by the AT!

/

with horizon scanner, provides attitude,
tional control to establish the

PROGRAM HISTORY

The MIDAS Program was included in Weapon
System 1172 when WS T1712 wes tronsterred
fo the Advanced Research Projects Agency.
ARPA subsequently seperated WS 1171 into
the DISCOVERER, SAMOS end MIDAS Pro.
Grams, with.the MIDAS objectives based on
an infrored reconnaissance system. The
MIDAS (Missile Defense Alarm System) Pro-
Gram was directed by ARPA Order No. 38,
dated 5 November 1958 until transferred to
the Air Force on 17 November 1959. A ten
launch development pion for MIDAS (Ws.
239A) has been approved. Additional euthor-
ization has been obiained to utilize two DIS.
COVERER flights (designoted RM-1 ond RM.2)
fe corry background radiometers in Support
of MIDAS.
Figure 3.
Proposed MIDAS system. Four satellites spaced equidistant in each

of two orthogonal Planes at 2.000 nm, altitude. Provides maximum
coverage of USSR with minimum number oj satellites.
cs

: Sighs



Technical Progress
Second Stage Vehicies

@ Assembly of the AGENA “B" vehicle for the third
MIDAS fiight is proceeding on schedule: Oelivery to
the systems test araa is scheduled for 3 August. This
is the first MIDAS vehicle to have restart copability.

© Because of the recent strike, o schedule slippage
has been incurred in the fabrication hose of the
fwo subsequent AGENA “B”’ flight vehicles. The
impact of these schedule slippages is not well defined
Gt this time,

Intrered Scanner Units

Infrored ‘scanner units for flights 3, 4 ond 5 are
being manufactured by Beird-Atomic, Inc. and for
flights 6, 7, and 8 by Aerojet-General Corporation.

©@ = Production and organizational chonges directed
foward achieving the desired production quality and
delivery rote have been instituted at Baird-Atomic,
Inc. A reevaluation of their infrared delivery schedule
has established 29 August cs the delivery date for
the initial igh? unit. Five flight payloads are sched-
uled for delivery.

© Should the results of acceptance testing indicate
the desirability-of replacing the drive motors or the

turret bearing, larger drive motors have been ordered
and @ new bearing is being designed,

© = Adetoiled reliability test Program is being deve!-
oped for the Aerojel-General advanced infrared
detection paylood configuration. In addition to
developing the service test mode! of this Payload,
Aerojet is now contracted to procure long-leadtime
items for the flight payloods. The definitive contract
for this payload is expected to be completed in
August.

Faciliies

Y

North Pocific Station—Construction of the Donnelly
Flats, Alaska, technical facilities is Proceeding on
schedule. Because of last year's prolonged stee! strike
and the late thow this spring, construction of the sup-
Port focllities at Fort Greely, Alaska, will be delayed
approximately two months, Completion is now sched-
uled for December,

LS

Figure 7. MIDAS data processing equipment inualled
so the Satelite Toot Coe te etsibmeet is



J earena
K ABtsowes

Figure 6. SAMOS concept, showing reception of commands and transnsission of data

between satellite and ground station,

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

Dato collected by the visual payloads will be elec-
tronically tronsmitted in the readout system ond
retrieved in the recovery system. Ferret data will be
transmitied electronically. These systems ere com-
posed of the AGENA vehicle, ATLAS booster, launch
focilities, tracking facilities, and a communications
and data processing network. The fecovery system
will also include @ re-entry capsule and a recovery
force.

CONCEPT

ATLAS Series D missiles lounched from VAFB will
boost the AGENA vehicle into polar orbits. Injection
into neor-circulor orbits (Figure 2) will be accom-
plished by the AGENA vehicle rocket engine. A self-
contained guidance system using a horizon reference
scanner wil provide altitude stabilization, As the
Satellite travels in on orbit essentially fixed in space
the earth rotates inside the orbit (Figure 3). Each
successive orbit is displaced laterally approximately
23% degrees ot the equator, Permitting one vehicle
to observe the entire earth in a time period depend-
ent upon the width of the area under surveillance.
Early versions will have a useful life of opproximately

mM —~GECREF=

3 and subsystem functions (schematic),

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

Visual Program—Three versions (E-1, £-2, and E-5)
of visual payloads are. being developed. The E-1 pay-
load is @ photo component test paylood which is
combined with the F-1 ferret paylood. The E-2 Photo-
graphic payload, under development by Eastman
Kodak Company, includes a camera, film processor,
ond electronic readout equipment. The E-5 recover-
able system designed by Lockheed will retain the
exposed film and the 66-inch focal length comera
developed by Hek Corporation.

Ferret Program—Ferret Payloads ore being devel-
ped on a progressively more advanced bosis from
R&D {F-1)'to advanced systems (F-4). The F-2 all-
digital, general coverage Poylood will use super-
heterodyne scanning receivers in conjunction with
directional antennas, an onalog to digital converter
and tape recorders (for storage). A programmer will
be used to control read-in over orecs of interest and
readout over tracking stations. The F-3 payload will
se similar receivers with stop-scan capability and
controllable ontennas added. Recording of the octual
signal intercepted {rather than the digital represen-

tation) will be possible with o bandwidth up to éme. -

A complex programmer will permit sotellite search
of a given area or frequency range.

WDLPM-4-222



SéOnaT-

equipment, the one month duration strike, and the
decision to incorporate engineering changes in the
systems test crea which were formerly programmed
for Vandenberg Air Force Bose. This change wos
made in the interest of decreosing the time required
for the missile assembly building phase of prelaunch
perotions. Although there are no @irborne com-

. Munications equipment delinquencies at this time,
Previous delays have made schedule recovery almost
@n impossibility,

© The stacking of major components for the first
AGENA “B" (single Poyload) vehicle wos completed
on 23 August. The vehicle has now entered the final
assembly phose of manufacture. The XLR81-Bo-9
engine (45:1 orea nozzle rotio) wes received in mid-
August. Delivery has oko been made of the guid.
ance control system inertial reference package and
its associated electronic items,

(

Wiha |

'T

Visual Reconnaissance Systems

Visvel Reconneissence Systems Poyleods ere being
in @ mininum avmber of

&2—Steerable Recoansisvance Peylead
{with 20-feot ground resolution)
Recovery:

B-S—High Resolution, Steerable, Receverable Payloed
{with S-feet ground Feselution)

£-4—Medium Reselvtion, Genera! Area Coterage, Recov.
. ereble Provad rese-

Peylond {with at lees? 10-foe

Payloads

E-1 Payload—Checkout ond testing of the E-1 pay.
load continues to Proceed on schedule at Vanden-
berg Air Force Base.

E-2 Payload—Final ossembly of the E-2 Payload for
the fourth SAMOS flight was completed during the
report period. Subsequent functional testing of the
completed payload has Fesulted in modifications to
the processor web feed system. Eastman Kodak is
expending maximum effort fo incorporate these
improvements with o minimum delivery schedule slip-

Figare 8. Stacking of bremating of the
major components of the AGENA “B"
rebicle fey, the fowrtb SAMOS figh,
This rebicle bas twice ax much propel
laut capacity as previous rebictey sed ea
be flown carrying an E-2 payload Fal.
flowing shi ration, the AGENA stenc.
tural assemblies are monuied herizoutully
ta a stand for fustallation of the engine
aud other fight comporcet



Figuw 4. DISCOVERER X11 during liftof from Viedeuberg Air
Forts Ban lineeh complex ow 10 August,

ar


17th orbit. Telemetry received by Kodiak from the
satellite and the capsule confirmed that sotellite
pitchdown, copsule ejection, spin, retro rocket firing,
capsule de-spin and thrust cone ejection were accom-
plished. Minutes later the Howoiion tracking station
acquired the telemetry signo! ond determined that
ablotive shield ejection and parachute deployment
had occurred.

@ All circraft ond ships of the recovery force within
range acquired the copsule’s RF beacon and began
homing on the signal. No aircroft was able to attempt
recovery, but one plane did observe the capsule
impacting in the sea. A helicopter from the “Hoiti
Victory,” one of the recovery ships, wos sent to
retrieve the capsule. The capsule was fiown to Hawaii
by helicopter, transferred to an Air Force plane, ond

delivered to Washington DC. After being viewed by

President Eisenhower, the copsule wos placed on
public disploy by the Air Force. This historic object,
the first man-made object recovered after a sustained
period of orbit, will become port of the Smithsonian

ww (fete) csteion of space vehicles.

8

@ DISCOVERER XIII carried o diagnostic payload
in addition to the normal recovery equipment. The
payload contained instrumentation to determine cop-
sule environment and the functioning of separation
and recovery sequence events. A five channel telem:
etry system wos installed to transmit the dota

obtained to ihe ground stations. To assure receipt
of all data, o tope recorder wos provided to record
the reol time events and copsule performance during
the telemetry “blackout" period which occurs when
the capsule re-enters the atmosphere. After a two-
minute time delay, these stored dota were trons-
mitted to the ground stations, The high speed of
re-entry induces ionization over the skin of the cap-
sule which effectively blocks telemetry transmission.
An S-band transponder wes olso provided to cid in
tracking the capsule from ejection through recovery.

DISCOVERER XIV

@ DISCOVERER XIV wos lounched at 1257, PDT,
on 18 August into o polar orbit from Vandenberg
Air Force Base: The launch wos deloyed opproxi-
mately 15 minutes because the still orbiting DIS-
COVERER XIIt satellite was passing through the
projected flight area. THOR booster performance
was near nominal. Separation, transmission of Com-
mands 5 and 6, and orbital boost were accomplished
es planned. Nominol and actual orbital parameters
ore given in Table Il.

Figure 2. Cluse-up of AGENA tebicle forwsnd equipment compartment pris tu mating with THOR booster.

‘WDLPM-4-234


SEQREr

+++ AERIAL RECOVERY OF CAPSULE

Phonograth of capsule and perachuti taben from within C119 fuselage
Con eee yi Mesmccessful attempts at arial recat Of Be
CONERER Xn".

Capsule being 1.
fuselage by mem
«5 crew,



sans

DISCOVERER CAPSULE AERIAL
RECOVERY

After capsule ejection from the satellite ond
Fe-entry into the earth's atmosphere, the pora-
chute deploys. Parachute deployment occurs
St an altitude of approximately 55,000 feet,
The crews of C-119 aircraft in the recovery
zone “home” in on the signals transmitted by
the capsule’s beacon and determine their inte?
Cept course, They have between 20 and 30
minutes from the time of Parachute opening
until it impacts into the seo to effect recovery.

The sequence on this Page shows contact
being made (top center}, the Gircraft moking o
Pass on the falling capsule lobove!, the hook
of the recovery gear snagging the nylon
conepy fabove right}, and the copsule being
hovied into the recovery aircraft. From the
time the chute is snagged until #t is safely
eboard requires from 15 to 20 minutes. If the
Gircratt cannot effect recovery, surfoce vessels
in the impact area attempt to recover the cap-
sule from the sea. A flashing lite, dye markers,
and the transmitter oid them in their seorch,

Recovery of the DISCOVERER XIV capsule
by the Howaiian bosed Fecovery force was the
first time in history © man-made object return.
ing from a sustained Period in space was
recovered by an aircraft.



see

1
8

A. THOR—DM-18 / AGENA “A” 8. THOR—DM.-21 / AGENA “BY C. THOR—DM.-21 / AGENA “B”

MB-3 Block 1 / XLR81-Bo-7 MB-3 Block 2/ XLRB1-80-9
@ Attained orbit successfully. A Failed to attain orbit,
Flight History
DISCOVERER AGENA THoR
Ne. ‘Ne. Ne. Plight Deve Romerks
Jonvary 1959 AGENA deutro malfunction L.
° rors 00 3 5° oR ‘fucked pi rintetra
l 1022 163-28 February fase orbit succest{ully, Telemetry received for 314 seconds after
ft-off.
Attained orbit falls. R ule ejected on 17th orbit
" tos 17013 Apa Seno rcv ancd Al oopeesexctpe sora acenrfol isc
. Lanuch, ascent, ration, coast and orbital boost jul, Failed
" 1020 174 S dune to achicte orkit berante‘of low performanre of nasiie roan
v 1023 179-25 June Same as DISCOVERER Itt.
v 1029 192 13 August AU gbiectices guccesstaly achieved except capsule recovery after
vl 1028 200 19 August Same as DISCOVERER V.
vu 1051 206 7 November fiycined orbit sacensfuly, Lack of 400-csle power prevented ste
bilization ou orbit and setorery.
v 5 20 Novem! Attined orbit success{uily. Malfunction prevented AGENA engi
m 1080 712 20 eer ierdowe a detned bial talecig Reborety cape atin
wot recovered. .
1 18 4 Fi 1960 THOR shu de maturely. Umbilical cond matt did not retract.
TM 052 ? ebrvory Qnied disconnect failed carting lest of beliom pretan TM t
x 1054 223.19 February THOR destroyed st T plus 56 sec, by Range Safety Officer.
55 1 Attained orbit successfully. Re snle ejected on 17th obi
x" 10 234015 April ate Tarn a oboe, eiale recovery suctestfally
achieved.
xi 1053 160 29 June Linuch, ascent, separation, coatt and orbital stage ignition were

successful. Failed to achieve orbtt because of AGENA attitude
during orbital stage boost.

xm 105723110 August Attained orbit success{ally, Recor ery capiale ejected on 11th orbit
Capsule was recovered after a water impact with negligible
All objectives excepe tbe arbarae recovery were incectifolly acberted.

xIV 1056 23718 August Attsined orbit successfully Recor ery capsule ejected on the 17th orbit
snd wat successfully recor ered by The airborse force: All objectives
Taccessfully sebteved.



ottained. Major problem @reos during the test were
in-orbit stabilization and communications.

. © Although poyload and vehicle transmission ceased
otter the thirteenth poss, some telemetry from the
solar auxiliory power under test system (SAPUT) hos
continued. The purpose of the SAPUT system is to
evolucte three types of solar cell coating materials,
Because of 9 failure in the telemetry switching sys-
tem, only one channel of SAPUT information wes
received subsequent to orbit Pass number one. Trans-
mission charocteristics of the SAPUT telemetry pro-
vided useful indications of the in-orbit motions of
the sotellite.

Technical Progress
Second Stoge Vehicies

© Fabrication of the AGENA “B" vehicle for the
third MIDAS flight was Proceeding on schedule; how-
ever, indications are thet a schedule slippage will
be incurred if the present strike at MSD is not ended
Quickly. Insteltation of the engine has been started
and assembly of the wiring harness is fearing com-
pletion,

© The electromechanicot ‘equipment that provides
directional Positioning of the solor cuxiliary power

array hos successtully completed @pproximotely 1000
hours of continuous tycling,

infrared Scanner Units

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

© = Menutacture of the first Beird-Atomic, Inc. infra-
red payload is behind schedule and slippages hove
occurred in delivery dates for the firs! three units.
This slippage con be Portiolly attributed to deficien-
in the turret bearing and drive motor which were
identified during acceptance testing of the thermo-
mechanical equivalent of the Boird-Atomic payload.

© Negotiations have been completed with Aerojet-
General Corporation for the development of a serv-
ice test mode! of an advonced infrared scanner
planned for later MIDAS flights. This model will con-
tain speciot instrumentation for engineering ond life
testing ond will not be o flight article.



ENTER ELLIPTICAL ORBIT

:
PERIGEE OF , 120° coasr.
— \ a oN ports
AGENA A , _
BURN Lome
IST, BU \ se ,
150 N. Mi, / . \
/ \

rom fe seers.
poe
: a ot ~ 4
sora \
Lee orbit trajectory for flights 3 and subsequent. Opti- Sree Teer peakerrrwclecty, mepmtnde and

ATLAS boost, guided by radio-inertial system. Scanner, Orbital attitude maintained by reaction wheel and
“GENA ascent (coms, barn, com, second burn) provides bas jets.

PROGRAM HISTORY

The MIDAS Program was included in Weapon
System 117L when WS 1171 was transferred
fo the Advanced Research Projects Agency.
ARPA subsequently separated WS 1174 into
the DISCOVERER, SAMOS and MIDAS Pro-
groms, with the MIDAS objectives based on
on infrared reconnaissance system. The
MIDAS {Missile Defense Alarm System) Pro-
gram was directed by ARPA Order No. 38,
doted 5 November 1958 until transferred to
the Air Force on 17 November 1959, A ten
founch development plan for MIDAS (ws-
239A) hes been approved. This RED Program
should moke possible the achievement of an
Operational system by 1963.

Figure 3. . . .
Proposed MIDAS s)s1em. Four satellites spaced equidistant in each of
swo orthogonal planes at 2.000 2.m. altitude, Provides maximum cov-
erage of USSR with minimum number of satellites.



SEGRE...

61 62.

ATLAS “D'/AGENA "6"

Il wnt Tie |

iCoNFiouRATIONs | ATLAS "O'/AGENA A"

SAMOS Launch Schedule
Monthly Progress—SAMOS Program
Technical Progress

Second Stage Vehicles

©@ The second stoge vehicle for the first SAMOS
flight hos undergone systems tests throughout the
feport period at Vandenberg Air Force Base. The
tests were successfully concluded on 17 August fol-
lowing o simulated faunch. Lote equipment deliveries

check (because of the DISCOVERER XII horizon scan-
ner problem) resulted in rescheduling the on-stond
date from 19 August to 2 September, This revised

on-stand date is compotible with the requirement of
fot installing the AGENA until after completion of
the ATLAS booster flight readiness firing (FRF). The
ATLAS FRF was successfully completed on 23 August.
Launch of the first SAMOS flight is now scheduled
for 4 October. This date will Permit the telemetry
ship Pvt. Joe E. Mann to return on station, following
its support of the DISCOVERER recovery operation.

© The two remaining SAMOS AGENA “A” dual
Payload satellites are proceeding through modifica-
tion and checkout in the system test area. These
vehicles ore approximately six-to-eight weeks behind
schedule. This delinquency was caused by late detiv-
ery of flight ond space airbome communications

Figme 7, The AGENA “A” sebicle for the first SAMOS Hight andergoing

auxiliary power subsystem checkout at
text fixture ow the extreme left is sed

Uandeuberg Air Force Base. The
dn checking the satelliu's mectial

refereuce unit, The inertcl reference auit and the korinon seatee, froth
the attitude reference for the AGENA flight control Siler.

| and the requirements for full-scale RF interference



Facility Equipment Flight Function

Sotefiite A Over-oll control, conver tracking stotions data to obtain o predicted orbit
Test Center and Generale subsequent ephemarides swe ocquistion data to rocking
Stations for subsequent posses, predict recovery area.

Vandenberg AFB BCDEFGHUK © Lounch, ascent and orbitol tracking, telemetry reception, Stajectory meos-
urements including time to ignite second stoge.

Point Mugu BCDEFGHIKL Ascent tracking ond telemetry doio feception, tronsmits command to
. ignite ond shut down AGENA (vio guidance computer),

Telemetry Ship OF Final stoge ascent trocking ond telemetry dota reception,

(Pvt. Joe E. Mannt

Anneite Island, Activity at this stotion terminated 1 December 1959 due to fund limitations,

Alasks ttrocking

stotion!

Kodiak, Aloska SDEFGHIIK Orbital trocking and telemetry dota reception, including first pass ocquisi-

(rocking station) tion, recovery copsule ejection ond impoct prediction,

Koena Point, BCDEFGHUK Orbitol tracking and telemetry date reception,

ttracking station)

Hickom AFB + Over-ail direction of capiule secovery operations,

Oahu, Hawaii :

* Equipment

©. 2 UNIVAC 1903-4 digital computers 1h. Plot boords for rador end TLM.18 tracking dete

b. VERLORT IMocklied Mod II} rador “ Comersion eqvipment lor teletype tronemision of redor,

< TUMI8 tatl.tracking telemetering antenne TUWI0 ond doppler wacking deta i benary formot

. Tishelee ontense 4 Acquettion programmer lor pre-ocquisition duection of
ontennos

© Doppler ronge detection equipment . & Ground commond to satellite trentmission equipment
# Telemetry tape recording equipment 1. Guidance computer
9 Telemetry decommutotors for rea! tme dato presentoion

GROUND SUPPORT FACILITIES

Oohu, Hawaii [



SEGRE

pleted to date at E! Centro, California, the single
chute system appears more desirable from the sto-
bility stondpoint, Structural integrity tests of the E-5
stabilization chute were initiated late in August.

Ferret Reconnaissance System

Ferret Reconneissonce System poylocds ere being developed
in @ misinam of configurations, The desigation end purpore
of c0ch configurotion is os fellows:
F-1—Composent Test Payleods
F-2—Digital Generel Coverege Payleods
F-—Specitic Minion Peyleads—
Analog signel rececding
F.3—Spetific Mission Peylends—Anclog signal recording

Payload

F-1 Poyload—Checkout ond testing of the F-1 pay-
load is proceeding on schedule at Vandenberg Air
Force Base.

Ground Support Equipment

© The installation and checkout of Point Arguello

TA

Pad No. 1 ground support equipment has been com-

pleted, with minor exceptions. These will have no

effect on the launch schedule. The ATLAS flight
teodiness firing on 23 August demonstrated the
readiness of the ATLAS ground support equipment.

Facilities

© = The orchitectural and engineering phose of the
modifications to accommodale an RED date Process-
ing facility in the satellite test center is complete.
Construction of the required changes is scheduled to
begin in early September, Approximately 70 percent
Of the equipment to be installed in the data process:
ing’ facility is on hand. The over-all effort to hove
this focility ready by mid-September is Progressing
Satisfoctorily,

© The contract for construction of the Point Arguello
diesel generator building was awarded on 29 August.

e Design of the Vandenberg Air Force Base helium
unloading and storege facility hes been initiated
with final design review scheduled for 9 September.


-56R58.

&-5 Payload—Design releoses for the full-scale test
models of the E-5 recovery capsule have been com.
pleted and fabrication of the initial test articles is
Progressing satisfactorily. A thermal mode! of the

E'S payload, for testing in the high eltitude tempere. ‘with he ss cies,
ture simuletor, was completed during the month, © Twor . te
Delivery of this thermal model is programmed fo; hove been conrerse chlo Uni Phan
sorly September. The purpose of these tests was to determine the E-5
© Wind tunnel tests for the purpose of confirming sapsule drag ond oscillation characteristics during
the E-5 recovery copsule basic @erodynamic con- retrieval into the recovery oricraft. B.
figuration are essentially complete. The force oscilla- wos lost during the deployment pl
tion tests at Longley Field, to determine dynamic wos completed. Some dota
stability characteristics in the 2.3-5 Mach range, currently being evaluated,
‘were completed on 10 August. Tests in the transonic :

© Test results of the stability and rote of descent
range are scheduled to begin in early September, choracteristcs of tingle mein porecka, venwe w
© Preparations are continuing for the shock tunnel clustered mein chute configuration Gre still being
fests at high angles of attack and low Reynolds fum. evaluated. Bosed on visual observation of tests com-

Figure 9. Model 1604 computer installation de the Vandenbveg Air Force
Bare dits aquisition aed Processing building. Ti “bigh spd Computer
a especially wall adapted tu the real time Operations ngwiied 10 satellite
Programs, A amilas computer justallation. is located at’ '« Satlire Tt

Page. Delivery of the Payload is not expected until bers to be conducted ot the Cornell Aeronautical
mid-September. Laboratories. These tests Gre programmed to begin
on 3 October. The Gerodynamic/thermodynamic
fests of the oblotive heat shield, originally scheduled
fo begin at the Avco Corporation it
have been delayed because of technical difficulties

in early August,



ENTER ELLIPTICAL ORBIT
PERIGEE OF

a
COAST ELLIPSE ,
-
AGENA \ 4
1ST. <
150. N. MIL

any sone
ro

Figure 2.
Leannchto-orbit trajectory for fii thts 3 and subsequent. From widante system, with borizow scanner, ides attitude,
“boast through seperatio? eee sand control's provided Felocy and dtetonal erate catabled ibe orb
by the ATLAS radio inertial system. The AGENA inertial vebicle orientation,

PROGRAM HISTORY

The MIDAS Program was included in Weapon
System 1171 when WS 117 wos transferred
to the Advanced Research Projects Agency.
ARPA subsequently seperated WS TI7L into
the DISCOVERER, SAMOS ond MIDAS Pro-
grams, with the MIDAS objectives besed on
on infrared reconnaissance system, The

| MIDAS [Missile Defense Alarm System) Pro.
Gram wes directed by ARPA Order No, 38,
doted 5 November 1958 until transferred to
the Air Force on 17 November 1959. A ten
lounch development pian for MIDAS (ws.
239A) hes been @pproved, Additional author.
ization has been obtoined to utilize two DIS.
COVERER flights {designated RM-1 and RM-2)
fo carry background radiometers in support
of MIDAS,

Figure 3.

Propored MIDAS systems, Four satellites Spaced equidistant in each
of two eribopond Planes at 2,000 n.m., altiude. Provides maximum
coverage of USSR with minimum number of satellites.

cz SHORET-



Figure 3.
Schematic of SAMOS system
is tiowal orbit. When the
lite is over the area of
interest the sensing equipment
is tuned on On tion
gutbering). When it leaves
the area of interest the sens
ing epripment is turned off
‘ed ‘isformtiion nd tre).
cue storage).
When the vebicle comes mike
in range of a ground receiv.
ing station, the data will be
read-on! upon command 4 fee
processing and mauumiit to
wiin, encies. is process
is coattenoas repeated dur.

ing the waa lifetioe of the

Fienre 5,

The initial viswal reconnaissance program will use com- stations thru a data link. Ground electronics will recon-
tentional photo tecbniques with axtomatic film proc- vert the signal into photo image form, with « capability
tisiug and TV-tpe electronic image readout to ground of resolving objects 20 feet im length.

a WDLMaa SEGRET Ba



+ horizon

Veapon
sferred
Agency,
7 into
sS Pro-
sed on
n. The
7) Pro-
to, 38,
tred to
+ Aten
3 (WS.
rogram
tofan

Figure 4,
Orbiting satellites detect ii jatie it
Fai af 7 a detect Sia otiation emitted

ene MIDAS satellite detecting ax A
Probabilities of 1.00 indiate ther mare there
MIDAS satelite will legs bef peso eyonn
© ICBA lauacb. These Fenres coe herd es Coe
metric considerations of the family of satellites and

brouad readout station locations.

TECHNICAL HISTORY

The MIDAS infrared reconnaissance poyload Is engi-
Nneered fo use a standard launch vehicle configura-
tion. This consists of a “D” Series ATLAS missile as
the first stage and the AGENA vehicle, powered by
@ Bell Aircraft rocket engine os the second, orbiting
stage {Figure 1}. The total Payload weight is approx-
imately 1,000 pounds.

The first two of the ten RED flights used the AGENA
“A” vehicle programmed to ploce the payload in a

circuler 261 nautical mile orbit. Subsequent flights
will utilize the ATLAS/AGENA “B’ configuration
which will be programmed to place the payload in
© circular 2,000 nautical mile polor orbit.

MIDAS |, tounched in February 1960, did not attain
orbit because of a failure during ATLAS/AGENA sep-
eration.

MIDAS il, leunched in May 1960, was highly suc-
cessful. Performance with respect to programmed

orbital porometers wos outstanding. Useful infrared
data were observed and recorded.



Specific mission of each flight. Figures 2 ond 3 show

@ typical launch Wajectory from Vandenberg Air

Force Bese, and figure 3 shows schematically o typ.

| ical orbit, An additions! objective of this program is
the

r Telemetry ships ore positioned os required by the

FUGHT Venice

The three versions of flight test vehicles used in the
Gre defined in the launch
schedule shown On poge A.5. Specifications for the
{we THOR configurations ond three AGENA configu.
tations used are given on Poge A-T,

nce etl Programs fed fo the salection ofc pie
Once system suited to achieving orbitel injection in a
horizontal attitude, AS o result, an optical inertial
system was for vehicle guidance and a

SAMOS ond MIDAS
AGENA VEHICLE

Son taeso wes

ROLL ~ 04 Decree
PITCH ~ 01 DEGREE

vaw =~] O€cREE

fun. ao
SECTION

SY ‘SEPARATION

LJ
further increase in Performance capebility including
engine restart and extended burn-copobitity,



a —
MIDAS Launch Schedule

6

|
VEHICLE .
CONFIGURATIONS ATUS "D"/AGENA “A”

cet

6

ATLAS “D"'/AGENA “B*

——

MONTHLY PROGRESS—MIDAS Program

Flight Test Progress

@ The second MIDAS flight test vehicle was
launched from Pod 14, Atlantic Missile Range (AMR),
on 24 May. Booster performance was highly satis-
factory, with booster, sustainer, and vernier ‘engine
cutoffs occurring as programmed. Ascent trajectory

‘was near nominal. The separation sequence was sat-
isfoctorily accomplished. Setellite engine ignition
occurred within one second of nominal and ‘engine
shutdown was initiated ot the Proper velocity. The
resulting orbit wos the most perfect circular orbit
achieved by the United States, with on epogee of
280 nautical miles and a perigee of 254 nautical
miles. The orbital life is expected to be 40 months.
Approximotely 75 percent of the test objectives were

Figure 6, Aerial tiew showing Atlantic Missile Range Complex 14 in the fore.
around. The gantry and lanuch stand ave on the right, The blockhoxse is om the deft.

WDLPM-4-222



Figure 6. SAMOS concept, showing reception of commands and transmission 0:

between satellite and ground station; and subsystem functions (schematic).

For economital testirig of ‘coilisonenteed uth
capability visual and ferret payload will be used dur-
ing the early development phase. On later flights
only a visual or ferret system payload will be carried.
These payloads will be housed in the AGENA vehicle
(Figure 1). ‘

Dota collected by the visual payloads will be elec-
tronically fronsmitted in the readout system ond
retrieved in the recovery system. Ferret data will be
transmitted electronically. These systems are com-
posed of the AGENA vehicle, ATLAS booster, launch
facilities, trocking facilities, and a communications
and data processing network. The recovery system
will also include a re-entry capsule and a recovery
force.

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

donthlégs Treereadiod dapendedlliparetbandful life
of four months with a design objective in certain
configurations of one yeor; recovery systems will
have a useful life of fifteen to thirty days.

TECHNICAL DESCRIPTION

Visvol Program—Three versions (E-1, E-2, and E-v,
of visual payloads are being developed. The E-1 Poy-
load is a photo component test payload which is
combined with the F-1 ferret payload. The E-2 photo-
grophic payloed, under development by Eastman
Kodak Company, includes a camera, film Processor,
and electronic readout equipment. The E-5.recover-
able system designed by Lockheed will retoin the
exposed film and the 66-inch focal length camera
developed by Itek Corporation.

Ferret Program—Ferret payloads are being devel-
oped on a progressively more advanced basis from
R&D (F-1) to advanced systems (F-4). The F-2 all-
digital, general coverage poyload will use super-
heterodyne scanning receivers in conjunction with
directional ontennas, an analog to digital converter
and tape recorders {for storage). A programmer will
be used to contro! read-in over areas of interest and
teadout over tracking stations. The F-3 payload will
vse similor receivers with stop-scon capability ond
controflable antennas added. Recording of the actual
signol intercepted (rather than the digital represen-
tation) will be possible with a bandwidth up to éme.
A complex programmer will permit sotellite search
of a given area or frequency range.



Facilities

© Vandenberg Air force Base— Modifications
to accommodate the Model 1604 comput
Vandenberg Air Force Bose dato acquis
. processing building hove been completed.

in the
ond

© Satellite Test Center—Construction of incre-
ment 2 to the Sotellite Test Center was completed on
schedule. Beneficiol Occupancy begon on 16 June
and instalation of equipment is in Progress.

© Point Arguello—installation of ol launch oper.
etions equipment, Propellant loading systems, and
high pressure ond liquid gas systems hos been com.
pleted at launch stand 1, System tests of the focility
cre in progress using ATLAS 57D ond the AGENA

facilities checkout vehicle. Construction of faunch
stond 2 is complete, except for the umbilical mast.
The most is scheduled for completion on 6 July.

@ New Boston, New Hampshire, Station—a
change in concepis of computer type and configura-
tion hes necessitated the design of a modification
to the Dota Acquisition and Processing Building. This
modificotion is scheduled for completion in time to
support the SAMOS lounches.

© Offutt Air Force Base—The construction con-
troct for the interim -dote Processing focility wos
ordered cancelled by the Office of Secretary of
Defense. Pending re-direction of the program, no
further action will be token on sither the interim or
the final facility, -

SHBG IO, tallns the Anus jasluics checkout tabich 00 the ATLAS
_ F7D beester prisn tu systems teste at Pores Aiguelle Lach tant A



Technicol Progress

Second Stage Vehicles

© = The results of on investigation into system ond
equipment performance on DISCOVERER XV were
Presented on 20 September. The Presentation
included anelysis of the various problem areas
encountered; action taken to improve test procedures,
inspections and equipment Specifications; and action
to incorporate improvements in DISCOVERER XVI,

© The XLR-8160-9 engine (serial No. 307) was
fitted with o new thrust chamber and subjected to 0
full duration calibration run. The 240 second firing
was completed without appreciable nozzle throot
erosion, using a titanium uncooled extension which -
hed previously completed o five doy humidity test,
The nozzle extension was in excellent condition fol-
lowing the firing. This test completed the Preliminary
Flight Rating Test for this engine which is now being
prepared for re-acceptance inspection prior to ship-
ment to Arnold Engineering Development Center for
reliability testing,

Figure 2, Air Force technicians adjusting
electrouic checkout equipment during
Might control checkout of an AGENA
sebicle, This activity is taking place in
the Vandenberg Air Force Bate missile
aisembly building.

Figure 3. Change.orer trom AGENA “4” 10 AGENA “BTM in the missile assembly building at
Vandenberg Air Force Base. The AGENA “A? om tie right, is DISCOVERER XV" which wae

heuncéed on 13 cepiembes. Oue muse AGENA “A” remains to be own, On the left is the

AGEN A “B" sekicle seteduled Jur launce en October as DISCOWERE! XV

StGaaT WDLPM4.245 |



——
i
a
————
——S_ z ee
GROSS WEIGHT fhe) 11,809 7.2
YURSI-Be-S — XLRBI-Bo-9 §
}$.400 16000
27 290
120 40
Ne Yes eee
H, Settle (Propellant ’
Pressurization) Paina Antenno
Hydraulic Package
“S$” Band Beacon
AGENA
VEHICLE

ATLAS
BOOSTE!
Infrared Sensor System
Main Engine
BOOSTER—ATLAS ICBM
Weight—Wet 95,100
MIDAS, Configuration Il, AGENA "8" Satellite Foal, BP-1 74,900
‘Oxidizer (LOX) . 172,300
GROSS WEIGHT (ibs.) 262,300
Engine—Ma-2
Twrint fibs. vac) Boos 356,000
‘Svstainer 82,100
Spec. Imp. (eee. vac.) Boost 206
Sustoiner 310

WDLPM-4.234 ~SECRET~ , C1



THRUST CONE
SEPARATION

PARACHUTE
DEPLOYMENT—ABLATION
SHIELD SEPARATION


Biomedical Capsules

@ The Advanced Biomedicol Copsule Study was
completed on 17 June. This Study indicoted the feas-
ibility of developing o copsule copoble of maintain.
ing © chimpanzee in orbit for two doys. The capsule
would be integrated with the SAMOS recovery
vehicle. A final report, preliminory drawings and a
full-scale mockup have been Prepored as port of the
study.

Facilities :
© A von-type telemetry readout ond recording

WDLPM.4-222

installation hos been established on Christmas Island.
This installation will provide monitoring ond record-
ing facilities downrange from Hawaii. The equipment
ot this instollation will monitor all orbital Passes
within the range of the stotion, record oll telemetry
dota from the diagnostic Poyload ond from the
AGENA vehicle. During the recovery poss, this instal-
lation will extend the telemetry reception coverage
south of the equator. An additional ship end five
telemetry equipped circratt will be dispersed between
Howoii ond Christmas Istend to complete the telem-
etry coverage south of Hawaii,

Feanre 4. The Adtanced Biomedical
Cpale mockup (below) with « model
Of the 30-pound chimpaczee and the seat
bastially sattalled. Specim a-recording

Jelemetry equipment are mount on
ihe top of ibe caprade, Forweed eed of
the mockup (left) showing oxygen
spheres, blowers, and coolse! equipment,
This mocknp was constected a3 part of
the Ads suced Biomedical Capsule Study.



BOOSTER—ATLAS ICBM

‘Weight—Wet 18,100
Foal, 29-1 74,900
Oxidiser (101) 372.300
GROSS WEIGHT (hes 262.300
Engine—MA-2
Thevet ios. vec.) Boost 356,000
Suateiner 82,100

Spec. Imp. free. vec) Soot 286
Suctelner 310

AGINA AGENA
S8cOND stAGE pry men
“im 1308 as
Payload equipment 3,
Orbieat 4u13 4753
lapels Propelients Amt 12,950
Fuel (UDMH)
thee ar EN 60 n
GROSS WHIOHT fhe) 18,201 aaa
“Kame UES SS?
mace “g “e
ima, set,
PROGRAM HisToRY
Figure 1.
5 ‘The SAMOS Program wes Included
Artists’ concept of SAMOS satellite,
Line arewing of complete flight im Weapon System 1171 when

vebicle (right) and detailed siew of ws VI7L wos tronsferred to the

basic AGENA upper stage (left).

ATLAS
BoosTER.

StCRET

Advanced Research

Projects
sorly in 1958. ARPA separated
‘WS 1171 into the

the SAMOS objectives based on @
visual ond ferret reconnaissance
system. On 17 November 1959
responsibility for this program wes
fronsferred from ARPA to the Aly
Force by the Secretary of Defense.

PROGRAM MISSION

The primary mission of the SAMOS advanced
reconnaissance system is to Provide visual and .
electronic coverage of the USSR ond its allied
Rations. Efforts include development of hard-
ware to permit:

@. Determination of characteristics of enemy
electronic emissions,

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

© Location and evaluation of defenses,

d. Evaluation of military and industrial
strength.

@. Assessment of high-yield weapons damage,
f. Reconnoitering of troep movements,

9. Location of naval forces throughout the
world,

Bl



SOOSTER—ATLAS Icom

Weight—Wer 15,100
Fost, RPL 74,900
Onidizer (10x) 372.300
GROSS WEIGHT (Ibs) 262.300
Engine-—ma2
‘Tarwst (lbs. vec.) Soest 356,000
Susteiner 82,100
Spec. imp. (set. ver.) Booet 26
Sutteiner 310
AGINA
SECOND STAGE “ae oo
Weigh
Inert 1.508 1495
Peyleed equipment 2 3.058
fe
tmpuise ts a x
Fuel (U0MH)
‘Onldizer (iRFNA)
ther 606 zs
GROSS WEIGHT (es) 11.211 1.420
Engine YURBIHo-S — X1R81-80.9
Thevat, Ibs. (vac) 5400 "6900
‘Spec. tep., vet. (vor) 2
urn Time, sec. 120 200
Figure 1.

Artists’ concept of SAMOS satellite.
Line drawing of complete flight
webicle (right) and detailed view oj
bisic AGENA upper stage (left).

lw [eo [3 [alan

PROGRAM HISTORY

The SAMOS Program was included in Weapon
System 1171 when WS 1171 was transferred to
the Advanced Research Projects Agency early
in 1958. ARPA separated WS 117L into the
DISCOVERER, SAMOS and MIDAS Programs
with the SAMOS objectives based on o visual
ond ferret reconnaissance system. On 17
November 1959 fesponsibility for this program
was transferred from ARPA fo the Air Force
by the Secretary of Defense. The Program was
realigned on 11 August 1960 to emphasize
visual reconnaissance over ferret and physical
recovery of data over electronic readout,

PROGRAM MISSION

The primary mission of the SAMOS advanced
reconnaissance system is to provide visuol ond
electronic coverage of the USSR ond its allied
notions, Efforts include development of hard-
ware to permit: .

&. Verification of known targets, detection of

unknown targets.

b. Location ond evaluation of defenses.

¢. Evatuation of military and industrial

strength,

d. Assessment of high-yield weapons damage.

e. Reconnoitering of troop movements.

f. Location of neval forces throughout the

world.

9. Determination of choracteri
lectronic emissions.



Figure 3.
Schematic of SAMOS sytem
in operational orbit, When the
Hite is over the area of
interest the sensing equipment
is turned on Unfonbanoe
gathering). When it leaves
the area of interest the sens-
ing equipment is twrned of
and ihe Sensing data is proc-
essed (Information storage).
When the ile comes with.
im range of a ground receiv.
ing ‘ison, the data will be
"read-out mpon command for
processing and transmitted to
asing agencies. This process
is continuously repeated dur-
in the asefal | lifetime of the
vebicle.

RB,

ATTITUg

“EG,

Figure 5, : i
The initial visual reconnaissance Program will use con- stations thre a data link. Grownd electronics will recon.

tentional photo techniques with antomatic film proc. vert the signal into photo image form, with a capabilit:
esting oud TV-t3pe electronic image readout to ground of resolving objects 20 feet in lengtb. spavity

wot SORET .

es



Figure 6. SAMOS concept, showing reception of commands and transmission of data

betwee satellite and ground stati

For economical testing of components a ducl-
capability visual ond ferret poylood will be flown
on the first 3 flights, On later flights only a visual
of ferret system payload will be carried. These pay-
loads will be housed in the AGENA vehicle (Figure 1).
Date collected by the visual payloads will be elec-
tronically transmitted in the readout system or physi-

launch facilities, tracking facilities, and a commu-*

nications and data processing network. The recovery
system will include a re-entry capsule and o recovery
force.

ATLAS Series D missiles launched from VAFB will
boost the AGENA vehicle into polor orbits. Injection
into near-circular orbits (Figure 2) will be accom-
plished by the AGENA vehicle rocket engine. A self.
contained guidance system using a horizon reference
scanner will provide altitude stobilization. As the
sotellite travels in an orbit essentially fixed in space
the earth rotates inside the orbit (Figure 3). Each
successive orbit is displaced laterally approximately
23% degrees at the equator, Permitting one vehicle
fo observe the entire earth in a time period depend-
ent upon the width of the crea under surveillance.
Early versions will have a useful life of epproximately
ten days. The readout systems will hove a useful life
of four months with o design objective in certain
configurations of one year; recovery systems will
have a useful life of fifteen to thirty days.

mM SECRET”

jj and subsystem functions (schematic).

TECHNICAL DESCRIPTION

Visual Program —Four versions {E-1, E-2, E-5 and
£-6) of visual payloads cre being developed. The
E-1 payload is a photo component test payload
which is combined with the F-1 ferret payload. The
£2 photographic payload, under development by
Eastman Kodak Company, includes a camera, film
Processor, and electronic readout equipment. The
E-5 recoverable system designed by Lockheed will
retain the exposed film and the 66-inch focal length
camera developed by Itek Corporation. The E-6 pay-
food is a medium resolution, general area coverage,
photographic recoverable subsystem being devel-
oped os en alternate to the E-5. The E-6 is now in
the source selection phase.

Ferret Program —Ferret payloads ore being devel.
oped on & progressively more advanced basis from
RED {F-1] to odvonced systems (F-4). Although only
the F-1 and F-2 are included in the flight test sched-
ule. The F-2 oll-digital, general coverage payload
will use superheterodyne scanning receivers in con-
junction with directional antennas, on enalog to
digital converter and tape recorders (for storage).
A programmer will be used to control read-in over
Greos of interest ond readout over tracking stations,
The F-3 poyload will use similar receivers with stop-
scan capebility and controfiable antennes odded.
Recording of the actual signal intercepted (rather
than the digital representation) will be possible with
@ bondwidth up to éme. A complex programmer will
Permit sotellite search of o given crea or frequency
range.

WDLPM-4-234



Tl

| A. THOR—DM-18 / AGENA “at B. THOR—DM.21 / AGENA "BY C. THOR—DM-21 / AGENA “8”
MB-3 Block 1 / XLR81-Ba.7 MB-3 Block 2/ XLR81-80-9
| 0 Atteined orbit successfully.

| @ Failed to attain orbit,

i Flight His ty

Bet

-

Discovensh AGENA THOR
| Ne, Ne. Ne. Right Dete Remarks
° 10191602 don ENA di fuaction on pad.
| very THOR kes alten pela
1 102216328 Feb 1959 Aieiged orbit sucess, Telemetry received for 314 seconds hier
u 101817013. Aprit Attained orbit . Recovery capzale ejected on 171b orbit
| te rete ie, tle ed 74 wi
7 1020 «1743 dune Lawech, ascest, cad orbital boost successfl. Failed
to ‘chines orkit bocente' of toe performance of wacliks engine.
| Vv 1023 17925 June Same as DISCOVERER ttt,
v 102919213 August A shinies suet sclwed exe apne conn cen
| vl 1028-20019 August Seme as DISCOVERER V.
vii 1051 2067 November Auained orkt sceeisfall, Lach of dooe ed
r TM Siication on orbit and eooarg “1 MOO bower prevesied se
vin 1050 212,20 November Ansinad orbir ly. Malfunction prevested AGENA engi
. shutdown at dereed bled Neen Recovery capsule tjectod bat
tet vecorered.
x 1052-2184 February THOR shat down promarercly. Umbilical cond matt did not erect
| " ee inet dene been causing lott of heliow ponent
x 1054 223 19 February THOR destroyed at T plus 36 s00. by Range Safety Officer,
Atcined orbit saccessfully. Recovery capsule ejected on 11h orbit
| m1 105523415 Ape ia el cy hide iodo 78 wt
achieved.
. » attent, jon, orbital stage ignition were
xu 1053 160-29 dune raccrriad Egg nein coe aud orbit of AGENA aunts
daring orbital stage boon.

Senet

N



AFEMD Actwitie; rr Space, Sep 60

SATELLITE

systems .

SATELLITE SYSTEMS



SECRETE

MONTHLY PROGRESS—DISCOVERER
Program

Flight Test Progress

© DISCOVERER Xi1 was lounched at 2300, GMT, on
29 June from Pad 4 of Complex 75-3, Vondenberg
Air Force Base. The countdown proceeded Satisfac-
torily with minor technical holds becouse of ground
support equipment problems. The major hold wes
caused by weather. The launch, first stoge trajectory,
engine cutoff, end separation were formal. AGENA
engine ignition, thrust ond ‘engine cutoff were also
Formal. However, the satellite failed to achieve orbit.
Telemetry data indicote thot the AGENA vehicle wos
in a pitch down otlitude during engine operotion
causing the vehicle to re-enter the atmosphere. Sub-
sequent investigation has isolated the cause of the
improper pitch attitude to the horizon scanner. A
thorough examination of the horizon sconner opera-
tion and checkout is being conducted to determine
the reason for malfunction and to correct the condi«
fion prior to the launch of DISCOVERER XIII.

©@ DISCOVERER XII corried a diagnostic payload
in addition to the normal recovery equipment. The
Payload contained instrumentation to determine cap-
sule environment and the functioning of separation
and recovery sequence events. A five chanel telem-
etry system was installed to tonsmit the data
obteined to the ground stations. To assure receipt
of aff data, a tape recorder wos Provided to record
the real time events and capsule performatce during
the telemetry “blackout” period which occurs when
the capsule re-enters the atmosphere. After a two-
minute time delay, this stored dota would be trans.
mitted to the ground stations. The high speed of
re-entry induces ionization over the skin of the cap-
sule which effectively blocks telemetry transmission,
An S-band transponder was also Provided to aid in
tracking the capsule from ejection through recovery.
DISCOVERER XIII will Corry on identical diagnostic
copsule.

Technical Progress

Second Stage Vehicles

@ One AGENA “B" vehicle (XLR-81Ba-7 engine) is
in storage following Air Force acceptance. Three

Figure 1, The sheast cone for the diaguostic payload showis
the "cold ger* inf drip mete copa ciewiag
operated valees, and manifolds for each system are shown in

of the photo. The exhaust jets are mounted on the
ausside of the cone, The thrust cone Separates from the pay:
luad priot to parachute. deployment,

other vehicles with XLR-81B0-7 engines hove com-
Pleted hot firing tests ot Sonto Cruz Test Base and
have been retuned to the systems test creo for
Fework and o second system check Prior to Air Force
‘ecceptance. The first two AGENA "8" vehicles using
the XUR-S1B0-9 engine ore feady for hot firing
system testing ot Sonta Cruz Test Base.

© Evalvation and testing of nozzle coatings in on
effort to reduce XLR-81B0-9 engine throat erosion
Continued during the report Period. The test results
using © modified fuel injector have been encourag-
ing. Tests of this injector will continue.

© Testing of the XLR-81B0-9 engine (with 45:1 area
ratio nozzle) continued ot Arnold Engineering Devel-
opment Center. An engine stort ond testort firing
series covering a temperature range of 120 to ~-55
degrees F hos been completed. The engine is mounted
in @ modified test stand which Permits engine gim.
balling.

Recovery System Component Test Program

© Extensive examination of the results of DISCOV-
ERER flight | through Xt hes indicoted the Possibility
of tumbling and/or precession of the capsule upon
separation from the AGENA vehicle because one or
more of the spin/de-spin rockets failed to fire prop-
erty. To correct this condition a “cold gas” spin/de-
spin system was incorporated into the DISCOVERER
Xi paylood. The “cold ges" system contains two
seporate subsystems each supplying o maximum of
195 pounds thrust with a firing duration of 0.8 sec-
‘onds. Each system contains a gas bottle (containing
@ nitrogen and freon 90s mixture}, a manifold, o
squib operated valve, ond exhoust jets.



A THOR-Dm 18 7 AGENA “An

8. THOR—DM-21 /AGENA ba Sad C. THOR—DM.21 AGENA “8
MB-3 Block 1 XL281-80-7 MB-3 Block 2/ xiR8}-Be.9

0 Atained orbit successfully,
© Filed to attain orbit,

Flight rn

Ne, Ne. x Plight Dete femerks
o 1019 160 21 Janvory ENA function .
THOR denne Hall fale
! 1022 163 28 Feb 1959 tig orbit successfully, Telemetry received for 314 seconds after
t 10181703 “Attained orbis ly. Recovery capsule ejected on 1915
April was nes rove: i in ca ne el om 1H rh
a 1020 174 “3d Launch, A it .
“oe to athieve oni bere Flow promane oii Fale
Nv 1023 179 25 June Same as DISCOVERER 111.
t 192 ned
v 029 13 August a bol an te eee sally ahleved excep eapiule recovery after
vi 1028 200 19 August Same as DISCOVERER V,
vil 1051 206 7 iber is fully, Lack
Novem: iced, be pccenh ly, Laci of M0O-eyI0 power prevented s10-
vill 1050 212 20 November rsfuelly. Mal} Prevented AGENA engin
iteadetoe cae fal soley haters po aha
. ‘mot recovered,
Xx 1052 218 4 THOR shas de Petmatarely, Umbilical cond mass did retract,
Febery FEQR tet dws om omg ler of ben poe
x 1054 223 19 February THOR destroyed a2 T plas $6 se. by Range Safety Offcer.
Attained orbit pale 7th orbit
xt 1055 234 15 April oon pred all. fecerery Pd ejected on Pollo
abieved, 7
xit 1053 160 29 June

Lawach, ascent, ation, coatt and orbital stage ignition were
successful, Failed Me" achiere orbit because of AGERA atinde
during orbital Hage boost.



Figure viel Actist's concept £, MIDAS
is tbo

eerie es ee Fi bekt ats

cond sage

basic AG.
vente ts

THERMAL/DATA LINK LNOSE CONEN-TM EXi EQUIP OXIDIZERTM- FUEL
SHIELD ANTENNA — SEPARATION .ANTENNA COMPT. TANK TANK

NOTE: AGENA “A configuration sncopt soosren—amias ican
for solor pedéies (AQENA “3” only), ‘Weight—Wet 15,100
Foal, a9.) 74,900
' Ontdicer ton) 172.300
GROSS WEIGHT (the) 262,300
Engine—MA-2
Thrvst {lbs vee) Beast 356,000

Susteiner £2,100
‘Spee. imp, (set. vec) Soest 106

Susteiner 310
ses



Figure oie A ie poiaPiale ee (lei) es suspended
frou ry Tit to
1000 foore inde! Closenp¢ tabese

he eit capsule and stem lemetey de ool pment

release ‘sentads is veteited,
alae shield which protects the

eyes Renerated of dating
igh speed poke date the at
41 shown. The exteradl surkace el of the
shield peels off wader the intense beat of
friction, thus dissipatin the bet and
protecting the le. Fe capsule bo]
Parachat wicined within

shield. Aeris righ ofite tapsule

during descent over lexico. The
S$00 ne, Sehlayed. at appre: vals
.000 fees altis ioe rt inmedia



Frome 3. Asteu't conception uf Al
satellite tvight; eM rag! below
comaplete thorttite fiat! talach. tr
Wad AGENA °B" svemud ware scbic
tbefty,

AGINA
ae “30

. Inert . 1534 1763
Poyleed equipment 3,246 1641
Orbitet 4790 3.404
Impulse Propellonts 6423 12,950
fuel (UDMH}

Oxidizer (IRFNA)
Other 608 730
11,009

GROSS WEIGHT ibs.) DAlry
YUREI-Bo-S — XLRBI-80-9

13600 16,000

Hy Bottle (Propellant
Pressurization) VHF/UHF
Command Antenna

Hydroulic Package

N, Bottle

“S$” Band Beacon:

“G"" Payload
Infrored Sensor System

Gos Jet L Sotar Arrey

Main Engine

BOOsTER—ANIAS ICBM

Waight—Wet
MIDAS, Configuration It, AGENA "B” Satellite Poet, Pt
Osidizer (10x)
~ GROSS WEIGHT (ibs.)

Engine—Ma.2

Thus! (las, vec) Boost
Sustoiner

Spee. tmp. (sec. vee.) Boo

tel /=[=]3

AGENA
VEHICLE

ATLAS
booste

15,100
74,900
172,300
262,200

356.000
82,100
rid

Sustoiner 310.



SECRETTM

Telemetry ships are positioned as required by the
specific mission of each flight. Figures 2 and 3 show
@ typical launch trajectory from Vandenberg Air
Force Base, ond figure 3 shows schematically a typ-
ical orbit. An additional objective of this program is
the development of o controlled re-entry ond recov-
ery capability for the payload capsule (Figure 4).
An impect orea has been estoblished near the
Hewaiian islands, ond o recovery force activated.
Techniques have been developed for cerial recovery
by C-119 aircraft and for sea recovery by Navy
surface vessels. The recovery phase of the Program
hos provided advances in fe-entry vehicle techno!-
ogy. This information will be used in support of more
advanced projects, including the return of a manned
satellite from orbit,

FUGHT VEHICLE

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

AGENA VEHICLE DEVELOPMENT

The AGENA vehicle wos originally designed by the
Air Force as the basic satellite vehicle for Advanced
Military Reconnaissance Sotellite Systems Programs,
Basic design was based on use of the ATLAS ICBM
@s the first stage. ATLAS trajectory choracteristics ond
the stringent eccentricity requirements of the
edvenced programs led to the selection of a guid-
ance system suited to achieving orbitel injection in a
horizontal attitude. As a resulf, an optical inertial
system wos developed for vehicle guidance and a

SAMOS and MIDAS
AGENA VEHICLE

PERFORMANCE

TORQUE

WHEEL Pacxace CAPABILITIES «= = <
ALTITUDE
200-20,000 mies
ATTITUDE

preted ROLL - 01 DEGREE

PITCH ~ 01 DEGREE
Yaw ~1 DEGREE

SECRET

AN sa

uN
[ SECTION
A

a 1 PLANE
Ss al

‘SPHERES.

ULLAGE ROCKETS
rROGEN
SPHERE (U0eme)

gos {et system for orbitol attitude control. An urgent
need for attcining higher altitude orbits resulted in
development of the AGENA “B" versions. The YLR8}
8a-5 version of the LR81-Ba-3 engine (Bell Hustler
engine developed for 8-58 Gircraft) is used on
AGENA “A vehicles. The YLR81-B0-5 version of this
engine wes developed to provide increased perform-
ence through the use of unsymmetrical di-methyt
hydrozine {UDMH) fuel instead of JP-4,

Eorly AGENA “8” vehicles will use the YLR81-Bo-7
version of this engine. The mojority of AGENA “B”
vehicles will use the XLRB1-Ba-9 engine incorporating
© nozzle expansion ratio of 45:1, and providing a
further increase in performance capobility including
‘engine restart ond extended burn capability,

UNES OF SIGHT—HORIZON SENSING

WDLPM-4-234



Ant

A. — THOR—DM-18 / AGENA "A" 8. THOR—DM-21 / AGENA “B” C. THOR—DM-21 / AGENA "B”
MB-3 Block 1 / XLR81-Bo-7 MB-3 Block 2/7 XLR81-Ba-9

@ Attained orbit successfully. A Faited to ottain orbit,

Flight History LS

DISCOVERER AGENA mor Flight Dete fn us
0 101 160 ad 1959 AGENA destroyed by malfunci ’
BI Janwory 1959 AGEN A dered by ll porate ral
i) 1022 163 28 Februcry Guise orbit successfully, Telemetry eeceived for 314 seconds after
vo
0 1018 i Attained orbit saccessfulls, R ule ejected on 171b orb
° 1703 Apel ‘rer notrecoverd: All objector exetp ae ee fe rash arbit
i} 1020 74 3h Lauach, ascent, seperation, coast and orbital boott successful. Failed
“ne to whe orbit because Of lows poten fee engine.
Vv 1023 179 25 June Seme at DISCOVERER I!!.
v 1029 19213 August AL hietves gucnttlly achieved exept capisle recovery ahr
vi 1028 200 19 August Same as DISCOVERER V.
vil 1051 206 7 November "Attained orbit sarceusfally Lack of 400-cycle power prevented sta-
Gitisation on orbit and recovery.
vin 1050 212 20Nevember Attained orbit successfully, Malfanctien presented AGENA engi
*  Ghaadowe at desired bebdad tooth Reeer ee AGENA rating
‘nol recovered.
x 105 2 F THOR shut down prematurely. Umbilical cord mast did 1.
8 4 February 1960 THOR she dows prom ‘enting lass of belinm premieres 7%
x 1054 22319 Fabruory THOR destroyed ot T plas 36 ser. by Renge Selety Oftcer
xl 1055 44 Attained orbit successfully, R ule ejected on 171b orbi
2 5 Apel tay aot acotered, All objecdoe? extent Meee on 7 enki
sbieted.
xi 1053 160294 Lanech, ascent, seperation, couit end orbital sage igniti
29 June saccessial Failed’ se achieve orbs beccese of GRC
: during orbital stage boost.
xt 1057 231 Atrsined orbit smccess{ally, Recovery caprate gietted on 171 orbit.
10 August ine ara recovered after « weer impact ab seslilble tee:
All objectives except the airborne recovery cere succrnifally achieeed,
XV 1056 23718 August Attained orbit successfally. Ri tale ajected on the 17th orbit
augue and seay saccentfully rcoteved by thc arbors forts All onc
: ‘accesifully acherred
xv 1058 246 AB September — Artained orbit successfully. Election and recotery sequence were

sormal. Capsule impact occurred south of the recoréry forces: located
bat lost prior to berne retrieved.

wou Shaner | as



AED Activities n Space, Jol 60° _pzggumee -

SATELLITE

systems

SATELLITE SYSTEMS

DISCOVERER

SAMOS

MIDAS

COMMUNICATIONS
SATELUTE



REBRMD Actwities mM Spack Jin —— .

SATELLITE

Sysfems

DISCOVERER

SAMOS

MIDAS

COMMUNICATIONS
SATELLITE



MONTHLY PROGRESS_Discovenee Program
Flight Test Progress

DISCOVERER xy

© DISCOVERER xv wos lounched from Vandenberg
Air Force Bose of 1515 PDT on 13 September and

PARAMETER NOMINAL ACTUAL
Azimuth, degree 172.0 175.2
Perigee, stotute mi 120 129
Apogee, stotute miles 410 478
Injection Angle 0.2
Eccentricity 0.0371 0.04
Period, minutes 93.44 94.2

TABLE 1, Discoverer xv Programmed

Orbital Parameters

impact point Predicted prior to capsule ejection. Sub.
sequent anatysis indicates that the roll rate Gyro wes
Rot property restraining the rote Of satellite roll
movements to the Proper frequency. This coused the
Satellite to roll between limits foster than Formal and
resulted in higher thon Rormal contro! 998 expen.
dit

© The capsule descent wos tracked by the Hewaiion
tracking station Until re-entry; @ Computer run of this

AS

SEGWEF.

DISCOVERER xvi

© DISCOVERER xvi is scheduled for launch from
Vandenberg Air Force Base in October. This will be

checks were completed during
has been installed on the
is an improved version

t
fanks which form ort of the satellite skin ond having
double the Propellant capacity,

* The increased Payload Sapobility of the AGENA
“BY will Permit use of extra bott

from previous Discoverer vehicles. A comparison
Of predicted Porometers for DISCOVERER xy and
DISCOVERER XVI are shown in Table fi,

onegyaan core
(AGENA “ATMnageNa —"
ASCENT PARAMETERS
THOR Burnout Time,
seconds from iiftoft 163 163
THOR Velocity at Burnout,
fps . 13,660 10,610
AGENA Ignition Time,
seconds from liftoff 269 237
AGENA Burn Time, Seconds v7 240

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

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

TABLE Ii, Comparison of Ascent ond Orbital
Perameters for AGENA “A” and AGENA "BY
Satellites

WDLPM-4.245



The DISCOVERER Program consists of the design,

development and flight ing of 37 two-stage D
vehicles, using the THOR IRBM os the first stage

booster and the AGENA as the second stoge, satellite

vehicle. The program wes established early in 1958 e
under d:rection of the Advanced Research Project's LY]
Agency, with technical management assigned to

AFBMD. On 14 November 1959, program respon- s

sibility wes transferred from ARPA to the Air Force
by the Secretary of Defense. Prime contractor for the
Program is Lockheed Missile and Space Division.
The DISCOVERER Program will perform spoce

* research in support of the advanced military recon-
noissonce seteliite programs.

€
. °
PROGRAM OBJECTIVES
fo) Flight test of the satellite vehicle airframe, pro- v .
e

pulston, guidance and control systems, auxiliory
power supply, and telemetry, tracking and com-
mond equipment.

(b) Attaining satellite stabilization in orbit.
{c) Obtaining satellite internal thermal environment

dete. r
(d) Testing of techniques for recovery of a copsule
ejected from the orbiting satellite. e
{e) Testing of ground support equipment‘and devel-
opment of personnel proficiency.
{f) Conducting bio-medical experiments with mice Fr
and smail primates, including injection into orbit,
re-entry and recovery. . AOENA
SECOND STAGE ord ”
. Weight—
PROGRAM SUMMARY inert 1262 tae 1346
Early lounches confirmed vehicle flight and satellite reeetewtomet = CE
orbit capabilities, developed system reliability, and Impulse propellonts 6,525 12.950 12,950
established ground support, tracking and data acqui- ‘Other Zz su eit)
sition requirements. Later in the program, biomedical TOTAL WHOHT 0462 15,676 13722
and advanced engineering payloads will be flight a anronl vee. epenad apenas append
tested to obtain support dato for more advanced ‘Spec. Imp.-cec., voc. wz 7 290
spoce systems programs. DISCOVERER vehicles ore urn time-cec, 120 240 0
launched from Vandenberg Air Force Base, with ‘wor soosTeR banal bae2t
overall operationcl control exercised by the Sotellite aor pony sm
Test Center, Palo Alto, California. Onidizae 101) 04200 am
GROSS WEIGHT {tbs} 108,850 108,400
Tracking end command functions ore performed by Engine ms-3 Ma
the stations listed in the Table on page A-4. A history Sock 1 Mock 2
of DISCOVERER flight to date is given on page A-S. See tow ee ft ‘we ‘ua
_ “era Time, vec. 163 10
wourM, SORET
. Al



Figure 2. Typical SAMOS trajectory, launch: to-orbit,

Ferret Reconnaissance...

READOUT+

Stee b

oct foe



BOOsTIN—AnLAs icom
Weight—Wet 15,100
Foal, §9-1 74,900
Oxidiser (0K) 172.200
GROSS WEIGHT (he) 262.300
Engine—MA-?
‘Thrwst (os. vec.) Boost 256,000
Suateiner 42,100
Spec, Imp. (ver, vee) Boost 26°
Seateiner 310

AGEMA = AGENA
SECOND stacE “an 7”

inert 1508 aes

2
Orbe! 4n3 4753
Impulce Propetionts 6402 12,990

ral

ee
i GROSS WHOHT te) T1211 18420

Engine VURG-Be-S — XLRBI-80-9
‘Thewst, Nes. tvee) 18,600 16,000
‘Spec. imp., sec. (vec) a7 290
Burn Time, sec. 120 240

Figure 1.
Artists’ concept of SAMOS satellite. The SAMOS Program was included
Line arauiee oh repo flight in Weapon System 117L when
gable (igh end detailed view of WS 1171 was transferred to the
vA upper stage (left). Advanced Research Projects Agency

early in 1958. ARPA separated

WS 1171 into the DISCOVERER,

basic AG!

The primary mission of the SAMOS advanced
reconnaissance system is to provide visual ond
electronic coverage of the USSR and its allied
Nations. Efforts Include development of hard-
wore to permit:

a. Determination of characteristics of enemy
electronic emissions,

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

¢. Location and evaluation of defenses.

d. Evaluation of military and industrial
strength.

©. Assessment of high-yield weapons damoge.
f. Reconnoitering of troop movements.

@. Location af naval forces throughout the
world,

Bl



SATELLITE IN ORBIT

rae \
60°
YW PITCH

7 DOWN

Curing it seventeenth exbit fepproximately 26 and three-quarter hour
citer launch) the AGENA vehicle pitches note down and coveule serene,

in its elliptical orbit round the earth. The “cold 90" spin system operates,
the retro rocket fires and the “cold gas” de-spin system operates New
the thrust cone seporates. The thrust cone contains the spin/de-spin system

55,000 feet ond the capsule, sending out a signal on which the recovery
Gircraft “home,” descends toward the earth it left only the doy before.
‘On recovery, the weight of the copsule is Opproximately one-third what it
was at the time of seperation. thems that are no longer needed are ejected
to reduce the capsule weight and Permit recovery, .

SEGRET



SCANNING TELEMETER |
SYNCHRONIZER, neceveR”
MATT Figare 3.
JH Sea etc cede
NoeNeaTORS ifroed mrmadiraly Senet!
re
8 | crown ise tr displayed att ate, The |
STABILIZED with a map overlay. The chart below
OISPL Ay shows dae flew from the readoxt

PRESENTATION The MIDAS Control ef bencies or |

UNIT tbe asin using eames be a seving 4 corre.
determine when an ipo sin ed bas

been launched.

SATELLT LONG PERSISTENCE C.RT.
Pasirion] CE CAT.

ICBM ATTACK SITUATION

PRESIDENT OF U.S,
DEPARTMENT OF DEFENSE

OTHER us NORAD OTHER ALLIED
I. GOVERNMENT AGENCIES Tai aS OPERATIONS aarat CovERNae

MIDAS TRACKING a
CONTROL CENTER

|

|

|

|

|

ols |
. |

|
|

|

|

ry

SPACE VEHICLE NETWORK

CONCEPT
The MIDAS system is designed to provide three strategically located readout stations.
continuous infrared reconncissance of the The readout, stetions transmit the data
Soviet Union. Surveillance will be con- directly to the MIDAS Contro} Center where
ducted by eight satellite vehicles in accu- It is processed, displayed, and evaluated
rately positioned orbits {Figure 3). The oreo (Figure 5.) Hf on attack is determined to
under surveillance must be in line-of-sight be underway, the intelligence is communi-
view of the scanning satellite. Mission capa- tated to a central Department of Defense
bilities are shown in Figure 4. The system is Command Post for feley to the President
designed to accomplish instontoneous read- ‘ond al! national retaliatory and defense
out of acquired dota by at least one of agencies.

SECRET WOLPM-4.228



coe » SECRET
Powered Flight Trajectory
®

FUEL ano
mMozER
soto

SPanaTion
ANE

a]
tenes

“BE Rockets
JOeny

febem tic Presentation ite teajecory fot, lauec,
from Peele IS A tied mn jorwed
ip tation anda it of eteipmens ang 5) each siatig
4s gen OW bage Ans,

gent
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ster

“this
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athyt

ge
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we
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HT Paty

sPsale betcan tt a
Tae eeanery forte iz deployed ta the ferotery Capact) ar

SECRET—

PM-4.234 WDLPM-4.234



These vehicles will be moved to the Vandenberg Air
Force Sase missile assembly building os required for
launch. The first two AGENA “B" vehicles using the
XLR-81Bo-9 engine ore undergoing hot firing accept-
ance tests ot Santa Cruz Test Base.

RE Interference Test Program

@ The couse of improper horizon scanner opera-
fion during the DISCOVERER XiI flight was deter-
mined to be RF interference from the satellite
telemetry tronsmitter. A modification has been incor-
Porated to correct this condition. Subsequent testing

has revealed on RF interference with the sconner at
any frequency or transmitter power level.

Recovery System Component Test Program

© The third ond fourth successful belloon drops of
the recovery system series were made at Holloman
Air Force Bose on 23 ond 27 July. The retro rocket
‘ond spin/de-spin systems functioned satisfactorily.
These were the second ond third successful dynamic
tests of the “cold gos” spin system. In both test choff
was dispensed from the pilot chute deployment bag
ond did not contact the main chute, indicating that .
the prior interference problem hos been solved.

~~



Telemetry ships are positioned os required by the
specific mission of each flight. Figures 2 and 3 show
@ typical founch trojectory. from Vandenberg Air
Force Base, ond figure 3 shows schematically a typ-
ical orbit. An additional objective of this program is
the development of a controlled re-entry and recov-
ery copebility for the paylood copsule (Figure 4).
An impact crea hos been established necr the
Hawaiian Islands, and a recovery force octivated.
Techniques hove been developed for aerial recovery
by C-119 aircraft and for sea recovery by Navy
surfoce vessels. The recovery phose of the Program
has provided advances in re-entry vehicle technol-
Ogy. This information will be used in support of more
advenced projects, including the return of o manned
satellite from orbit.

FLIGHT VEHICLE

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

AGENA VEHICLE DEVELOPMENT

The AGENA vehicle was originally designed by the
Air Force os the basic satellite vehicle for Advanced
Military Reconnaissonce Satellite Systems Programs.
Basie design wos based on use of the ATLAS ICBM
@s the first stage. ATLAS trajectory characteristics and
the stringent eccentricity requirements of the
advanced programs fed to the selection of o guid.
ance system suited to achieving orbital injection in a
horizontal attitude. As a result, an optical inertio!
system was developed for vehicle guidance and a

SAMOS and MIDAS
AGENA VEHICLE

ROLL ~ 0.1 DEGREE
PITCH - 01 DEGREE
yaw =  OEGREE

FUEL AND
Ca)

n TANK
‘SECTION

—,

a
PLANE

. ama
SPHERES

ULLAGE ROCKETS

ane (vam
905 [et system for orbital attitude control. An urgent
need for attaining higher altitude orbits resulted in
development of the AGENA “B” versions. The YLR81
80-5 version of the LRB1-Ba-3 engine (Bell Hustler
engine developed for 8-58 cireroft) is used on
AGENA “A" vehicles. The YIR81-Ba-5 version of this,
engine was developed to provide increased perform-
ance through the use of unsymmetrical di-methyt
hydrozine (UOMH} fuel instead of JP-4.

Early AGENA “B” vehicles will use the YLR8)-Ba-7
version of this engine. The majority of AGENA “B"
vehicles will use the XLRO1-Ba-9 engine incorporating
© nozzle exponsion ratio of 45:1, and providing a
further increase in performance copobility including
engine restort and extended bum-capobility.



Monthly Progress—DISCOVERER Program
Flight Test Progress

© The lounch of DISCOVERER XIII is scheduled for
10 August. DISCOVERER XIV is scheduled for 18
August.

© DISCOVERER Xt! will carry 0 diagnostic pay-
load in addition to the normol fecovery equipment.
This poyload contains instrumentation to determine
capsule environment and the functioning of separo-
fion and recovery sequence events. A five-chonnel
telemetry system is installed to transmit this data. To
@ssure receipt of all dato, a tope recorder is Pro-
vided to record the real time events ond capsule

berformance during the telemetry “blackout” period
which occurs when the Capsule re-enters the atmos-
Phere. After a two-minute time delay, this stored data
will be transmitted. The high speed of te-entry
induces ionization over the skin of the copsule which
effectively blocks telemetry transmission, An S-bond
transponder is also provided to aid in tracking the
copsule from ejection through recovery.

Technicel Progress
Second Stage Vehicles

©@ = Three AGENA “B" vehicles (X8-81-80-7 engines)
ore now in storage following Air Force accepiance.

Figure 1. DISCOVERER XIII AGENA “A” cebicle (No. 1059) undergoing
systems tests in the missile assembly building at Vandeubsrg Air Force Ban.

‘ollowing these checks the faiings will be
transported ta the Lannch pad for wustallaion

dustalled and the rebule will bi.
ow the THOR bouts, DISCOV.

ERER XIII is cebcduled four launch on 10 August.

WDLPM.4.228


SEGRE

© Installation of a DISCOVERER ground station at
the New Boston, New Hampshire, facility wos com-
pleted and checked out on 17 August. Installation of
equipment was storted in duly. The station hes the
capability for Verlort radar tracking, command ond

telemetry reception. Construction of support facilities
is on schedule. The initial increment of support facili-
fies was accepted on 2 August with the remainder
scheduled for completion on 7 September.



fier

© Drop testing of the DISCOVERER capsules con-
tinved throughout the report period ot Holloman Air
Force Bose, New Mexico. Ori ily scheduled for
nine drops, the tes! series hos been extended to per-
mit field testing of the capsule porachute system ond
testing of retrofiring system. Solid Propellont rocket
spin/de-spin systems tests were conducted on 24
May. “Cold gas” systems tests were conducted on
23 June. The porochute system tests storied Prior to
the solid propellont rocket test ond are still in
progress.

©@ For each of the drop tests, the capsule is carried

to 100,000 feet altitude. On commond from the
ground, the capsule is released from o fairing which
simulates the AGENA vehicle, During the tetrofiring
system drop, the ejection progrommer within the cop-

sule fires the spin system, the retro rocket, and the

de-spin system in the normal ejection sequence. Pora-
chute deployment is also controlled by the ejection
Programmer. These capsules are fully instrumented
1 monitor capsute performance ond contain telem-
etry equipment to transmit the data obtained. in the
Porochute deployment tests the Mach and dynamic
loading conditions encountered in actual recoveries
ore experienced.

Figare 2. DISCOVERER diagnostic fish pestosd shown during system tes

prior to shipment 10 Vandenberg Air Force Base. The equipment contareed ia this
Payload monitors the ce of the ejection and recot ery system components
tnd tlemeters thit data to the gronud stations,

os


Rasta implifed version 0; ind presen.
Send Ce
Scammung ‘TELMETER reconnaissance

ne, ———— Ractiven data is displayed om «TV monitor
GUUTNAL ssonaa with a map overlay. The chart below
HE Hive shows data flow from the readout
Wornnua, pase Sations to decision-makin, ‘agencies,
Centnarons The MIDAS Control Comer or
» other wsing agencies basing a corre-
+ @aounp lated grownd stabilized display, can
Stamuzes determine when an actual attach bas

oemay been launched:

The MIDAS system is designed to provide
continuous infrared feconnaissance of the
Soviet Union. Surveillance will be con-
ducted by eight satellite vehicles in occu-
rately positioned orbits (Figure 3}. The area
under surveilionce must be in line-of-sight
view of the scanning satellite. Mission capa-
bilities are shown in Figure 4. The system is
designed to ‘@ccomplish instantoneous read.
Out of acquired dota by at least one of

ti Seats car .

Figure 5,

three strategically tocated readout stations.
The readout stations fransmit the dote
direcity to the MIDAS Control Center where
it is processed, displayed, and evalvated
(Figure 5.) it on Gltack is determined to
be underway, the intelligence is communi-
cated to a central Deportment of Defense
Command Post for teloy to the President
‘and oll national retoliatory and defense
agencies,

WDLPM-4.222



ce ao

GROUND SuPPORT FACILITIES

Facility Equipment®* Flight Function

Satellite A Over-all control, convert tracking stations date to obtain a Pre.

Test Center dicted orbit and generate subsequent ephemerides issue acqui-
sition data to tracking stations for subsequent passes, predict
recovery dota.

Vandenberg AFB BCDEFGHIIK Launch, ascent and orbital tracking, telemetry reception, trajec-
tory measurements including time to ignite second stage.

Point Mugu BCDEFGHUKL Ascent tracking and telemetry data reception, transmits com-
mand to ignite and shut down AGENA (via guidence computer).

Telemetry Ship OF Final stoge ascent tracking and telemetry data reception.

(v1, Joe E. Mann) .

New Boston, . BDEFGHUK Orbitol tracking and telemetry dota reception.

New Hompshire

(tracking station)

Kodiok, Aloske BOEFGHIIK Orbital tracking and telemetry data reception, including first pass

ttracking stetion) ecquisition, recovery copsule jection ond impact prediction,

Koena Point, BCDEFGHIJK

Ochu, Hawaii .

{tracking station)

Hickom AFB

Over-all direction of capsule recovery operations,

Ochu, Howali
quipment

A. ZUNIVAC 1103-4 digitel computers H. Plot beards for redar aed TLM-18 racking dete

& VERLORT (Modified Mod 11) rodor |. Conversion equipment for teletype Wonsmission of roder,
C. TLM-18 self-tracking telemetering entenno TM-19 ond doppler trecting data in hinery format

©. Teisbelin entenna, + Acquisition programmer fer pre-cequisition direction of

E, Doppler range detection equipment ontennes
¥. Telemetry tope recording equipment K. Ground commend to seteltite tronsmitsion equipment

G. Telemetry decommutotors for real time dete Presentation

1 Guidence computer

Orbital tracking and telemetry data reception. |



Figure 6 Crermen abound seeuter) ane
sraft check bouk ow scores) tance
Priar to harness deployment.

Air Forte C-119 patrolling iw recor ery
ares north of Hawaii with capsule recor>
ory barnes extended.

WDLPM-4-234


SEGRE

The DISCOVERER Program consists of the design,
development and flight testing of 37 two-stage
vehicles, using the THOR IRBM as the first Stage
booster and the AGENA os the second stage, satellite

by the Secretary of Defense. Prime contractor for the
Program is Lockheed Missile and Space Division,
The DISCOVERER Program will Perform space
Feseorch in support of the advanced military recon-
Reissonce satellite Progroms,

PROGRAM OBJECTIVES

(a) Flight test of the sotellite vehicle Girframe, pro-
Pulsion, guidance and control stems, auxiliory
Power supply, and telemetry, tracking and com.
mand equipment.

{b} Attaining sctellite stabilization in orbit,

{cl Obtaining sotellite internal thermal environment
dota,

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

LO} Testing of Qround support equipment and devel.
pment of personne! Proficiency,

(f} Conducting bio. edical experiments with mice
‘ond smail Primates, including injection into orbit,

fe-entry and recovery,

PROGRAM SUMMARY

Eorly lounches confirmed vehicle’ flight and sotellite
orbit copobilities, developed system reliability, ond
established ground Support, tracking and dato ecqui-
sition requirements. Later in the Program, biomedical
and advanced engineering payloads will be flight
tested to obtain support data for more edvanced
Space systems programs, DISCOVERER vehicles ore
lounched from Vandenberg Air Force Bose, with
Overall operational control exercised by the Sotellite
Test Center, Sunnyvale, Colifornia

Tracking and commond functions are Performed by
the stations listed in the Table on poge A-4, A history
of DISCOVERER flight to date is given on Page A-5.

WDLPM-4.245

@i¢lola

r
AGENA AGINA
SECOND stage “a ”
Weight :
tnert 1,262 1320 1,346
Pevtood equipment = ‘497 7 5
Orbital We 2215 2216
Impeice propettonts 6,525 12.950 12,930
Other 7 su su
TOTAL weiGut 8662 15476 13722

Engine Model

YLRBI.Be.5 XURB3-Bo-7  X1R81.80.9

Thewst-thes., vee. 13,600 15.600 16,000

‘Spec. Imp.-tec., vac, a7
Burn time-tec. 20
THOR BOOSTER om.18
Weight—Dry + 6980
Fuet 33,700
Onidizer OK) $4200
GROSS WEIGHT Obs) 108.850
Engi a3
“ne Bock 1
152,000
78

163

77 290
240 240

m2
6.500
33700
68,200
108,400
8-3
Block
167,000
248.3
iy



I

October. This equipment will be installed in the Satel- Donnelly Dome microwave relay station is scheduled
lite Test Center; a second unit will be installed in the for completion on 15 December. Beneficial eceu-
Vondenberg Air Force Base Trocking station. The Pancy of the remaining North Pacific communications

late delivery of the equipment for the Sotellite Test

Center will not offect the scheduled octivation date. GY
Some revision of the integration activity will be

required; however, this will not affect the MIDAS
launch schedule. Delays in delivering the second
unit of ground station equipment, however, will cause
some slippage in the Vandenberg Air Force Base
tracking station activation date for support of MIDAS
flights.

Facilities

© A detailed evelvation of lounch pod require-
ments for the MIDAS operetional phase has been
occomplished. This study indicates the need for a
three-pad launch complex during the establishment
of the operational network, and a requirement for
from two-to-three Pads for maintaining the MIDAS

stations is programmed for 1 January 1961,

satellite network once the buildup phase has been © All New Boston station support focilities located
completed. on Grenier Field, New Hampshire, were completed
© Final acceptance, of North Pacific station tech. and accepted during the seport Period. Support facil-
nical facilities at Donnelly Flats, Alaska, was accom- ities on the New Boston station Gre on schedule.
plished on 29 September. The heated vehicle storage Design of the data ocquisition and Processing
building of Fort Greely is scheduled for completion building modification hos been completed ond c
on 31 October. Completion of the combined dormi- construction contract is Presently being negotiated,
fory end dining halt facility, except for exterior area Completion is scheduled on an incremental basis
grading, will be completed on 30 December. The with final completion scheduled for 1 January 1961.

Figure 8. Overall tuw_of the MIDAS ground equipment curently
eustalled va the Satelite Tot Center, The drawer led cut bonses the
ontitlagrape equipment, The equipment racks in the ves house the tape
recorder mitallacon,



2
2
a
=
2
a
=



Seam,

MONTHLY PROGRESS — MIDAS Program

Program Administration

© As a result of recent investigations by Space
Technology Laboratories on the significance of the
high energy tai! of Von Allen protons, ond their
potential effect on long-life satellites, Lockheed has
been requested to develop special instrumentation to
be carried on MIDAS flights. Controry to the present
theory that the damage cross section is inversely
Proportional to energy, evidence has been found
that solar photovoltaic cells may be degraded ot o
much higher rate by high energy protons, e.9., 700
MEV. A comprehensive Program has been initiated
to determine the sensitivity of selected ‘components to
high energy proton radiation and to determine the
quantitative and quolitotive characteristics of the
Van Allen radiation at MIDAS flight altitudes.

Flight Test Progress

© The vehicle for the third MIDAS flight is currently
in the systems test phese of checkout. This is the
first MIDAS vehicle to have restart capability. Because
of problems which developed in the horizon sen-
sor and related checkout equipment, this vehicle is
behind schedule. Based on delivery of a reworked
horizon sensor on 15 October, it is scheduled to
complete the systems test phase on 12 December.

The scheduled launch date for this flight remains 28

” February 1961.

Technical Progress

Second Stage Vehicles

© Assembly of the AGENA “BY vehicles for the
fourth and fifth MIDAS flights is proceeding on
schedule. The vehicle scheduled for the fourth MIDAS
flight is new in final ‘ossembly.

latrared Scanner Units

latrored scanner units for flights 3, 4 and 5 are being menvfoc-
tured by Beird-Atemic, inc., and for Hights 6,7 and 8 by Aerojet-
‘Generel Corporetion.

© The infrared detector payload scheduled to be
corried on the third MIDAS flight has been delivered,
Acceptance testing of this payload will be completed
in early October. The second flight payload is sched-
uled for delivery on 15 October. Two more Payloads,
one for bockup purposes, remain to be delivered.

© Temperature profile tests of the engineering test
model of the Baird-Atomie configuration are in prog-
ress in the High Altitude Temperature Simulation
Chamber, .

Ground Suppor! Equipment

© Delivery of the initiot Baird-Atomic ground infra-
ted data display equipment is scheduled for 15

Figure 6. A backgromad radiometer of the type tu be cared on
DISCOVERER tigtts RM-1 aud RA-2, The primary function of
there frette will be 10 proride backgroned radiation litt for wie se
future MIDAS sights, Tice uinogen spheres are Part af the xitrogen-
fa conteng site wbied couls the sensitive clemest of tbe

Fadsome ter,

SSEGRET:



Lesdeny ane ef the telemetry tans into
ait fur andi to the new DISCOV
tation lt New Bustue, New Hamp.

shee,

WwoLPM4.734 SEGAL... mar



&. Aerial siew (opposite

ioe 4 the Vandenberg Air. Force Bass

and data axesistion station. The
TIM. 18 VHE exten, i in the spber
eit a ihe picture and
caionne i in ‘owe,
rele ite taal racking antenna and
control building (abose,

) at Vandenberg
Air Force pid Sixty-foot cateuna it
she baci Closexp (right) of ‘the
efor JHE tracing, and date antenna.
je tracker console te (below) with
yanent racks in the background, This
equipment is undergoing systems inte-
gration tests,



attitude,
orbit and

Weapon
nsferred
Agency.
171 into
JAS Pro-
‘sed on
em. The
3m) Pro-
No. 38,
‘erred to
9. A ten
AS (WS.
al author.
two DIS.
nd RM-2)
1 support

SLPM-4.234

Figure 4.

Orbiting satellites detect jufrared radiation eminted
vet ICBMs in powered flight. Data telem.

Justentaneously to MIDAS

north readc

abproximately she sumber Of missiles launched and

‘each location, divection of travel aad bern

al ragteristics, Pra vies of yt thes 1.00 on
re mad indicate the probability of

ene MIDAS satellite detecting an 1 denne,
dlities of 1.00 indicate that mere one

AMIDAS ieilte il ale 1s be im position to detect

aares | on gro.
metric considerations of 11 family of satellites‘and
bound readout station locations.

Control Center
lout stations. Decoded data rereal

at least

dauncb. There figures are

TECHNICAL HISTORY

The MIDAS infrared reconnaissance payload is engi-
Reered to use a standard launch vehicle configura.
tion. This consists of an ATLAS missile as the first
stage and the AGENA vehicle, powered by a Bell
Aircraft rocket engine os the second, orbiting stage
(Figure 1). The final configuration payload weight
will be approximately 1,000 pounds.

The first two of the ten R&D flights used the AGENA
“A" and ATLAS “D" vehicle programmed to ploce
the payload In a circular 261 nautical mile orbit,
Subsequent R&D flights will utilize the ATLAS “D7

WDLPM-4.234

SHOREE

AGENA “3” configuration which will be programmed
$9 place the payloed in a cirevler 2,000 nautical mile
polar orbit,

MIDAS 3, launched in February 1960, did not attain
orbit becouse of a failure during ATLAS/AGENA
separation,

MIDAS II, launched in May 1960, was highly success.
ful. Performance with Tespect to programmed orbital
Porameters wos outstanding. Useful infrared date
were observed and recorded.


seo!
mL verses

Figure 9. Checking Programmable Integrated Con.
trol Equi (hic control cabinet ion.
Fie Kerr's tchedaled for temaliaton ot Venden:
berg Air Force Base in September.

progressing on schedule at the contractors facility.
Functional checkout and compatibility tésts of set
No. 1 are now in progress. Delivery to the Vanden-
berg Air Force Base tracking ond acquisition station
ts scheduled for September. Set No. 2, scheduled
for delivery to the Satellite Test Center 60 days after
completion of Set No. }, is in final assembly.

Ferret Reconnaissance System

@ Ferret Reconnoissance System payloads are being
developed in a minimum number of configurations.
The designation and purpose of each configuration
is as follows:

F-1—Component Test Payloads
F.2—Digital General Coverage Payloads

F-3—Specific Mission Payloads—Analog
Presentation

Figure 10, Adjusting the checkout console signal
generator during functional testing of the F-1 pay-
fosd. These sests comsist of checking load
vesdout against calibrated inputs, The telemetry
monitoring equipment is in the left-hand section
of the contole.

Payloods

F-1 Payloads—The F-1 payload, previously deleted
from the first SAMOS flight, was reinstated on 26
July. Checkout and testing of the payload has been
occelersted at Vondenberg Air Force Base.

Ground Support Equipment

@ The F-1 operating console has been delivered

fo the data acquisition and processing building ot
Vandenberg Air Force Base.

Facilities

© Construction of ol facilities required for the first
SAMOS flight .is complete, and installation and
checkout of equipment are progressing at o rate
compatible with the scheduled launch date. Systems
testing of the Pad 1 complex a! Point Arguello wos
completed late in July.

@ Bid opening for the Point Arguello diese! gen-
erator building wos held on 26 July. A total of
twelve bids ranging from $184,000 to $249,000
were received.

@ The SAMOS !aborotory building ot Vandenberg
Air Force Base was completed ond accepted on 18
July, with minor deficiencies remaining to be cor-
tected. Design of the Vandenberg Air Force Base
helium unloading and storage facility has been initi-
ated with design completion scheduled in eorly



Figure 3. DISCOVERER XIII during
bre-dawe countdown ow 10 August. prior ,
to evection (above) and during serricing
operations following erection om laxuel
bad (igh). Ie top tiew, the blanket

darrounding the note cone provides air
conditioning for capsule electronics dur-
a countdown to prevent ouerbeatiug.
The black dome feed from she
bisekes is part of the ablative shicld
which surrounds and protects the capsule
during re-entry,



ais

PATH

-228

z
e
;
{
E
W

HH
ifs

iif
He

Orbital Trajectory

Schematic preseutation of orbital trajectory followin, Lennch
front Vandenberg Air Force Bute. Functions Performed by
each station and a listing of equipment used by each station,
ds givem on page Ad,

RECOVERY CAPABILITY

This objective was added 10 the Program
ds, the fe ons ceed cb
fabs aud orbit objectives success{ully.
Ui tectades the orientation of the satellite
rebicle to permit a recovers le capsule to
be sietied from she ‘ease section of the
AGENA sebicle. Ejection is Programmed
4o otter au command on the 17th orbir,
fer capsule impact within the predeter.
Mined recovers area south af Hage,
Aireratt and surface vessels ave deployed
within the wes aca seenvery forte,

fommand ts seni to the satellite by the
, P tb orbit. The rebicle
sir bosition (300 inset) 10 permit ejection to oe

rjector) ow the 1715 orbit. TI retorery 6:
tale Parachute is activated at about 30,000 feet. and ihe
imits ¢ vadio sigwal for traching Purposes,
eeorery force is deployed in the recovery lineer} ee

A3



GiGnttT—

++» SEA RECOVERY OF CAPSULE

‘WDLPM-4.234



SEGREF

dota indicoted a 2.75 percent shift in the power
level. The engine was tom down for exomination.
Tests of this engine ore expected to resume eorly in
September.

© The first XUR-8180.9 engine (serial number 316)
delivered with flight configuration hardwore, hos
successtully completed acceptance testing. One
‘engine (serial number 317) has been hot fired but
©peration was unstable ond the power level dropped,
Analysis disclosed that the gas generator venturies
required resizing ond thot the oxidizer filter was
improperly installed, This engine is now being pre-
ered for final acceptance testing,

Balloon Drop Test Program

© The drop test Program continued at Holloman
Air Force Bose with two test attempts on 4 August.

The first balloon burst Gt 30,000 feet, before the
planned drop of the Mark IV capsule, however, the
equipment was recovered successfully. On the second

capsule is similor to the recently recovered cap-
sules but contains on improved programmer and
other modified components,

Facilities

© Acceptonce of the Gir conditioning system modi-
fication for the Vondenberg Air Force Base data
acquisition and Processing building was made fol.
lowing successful completion of on equipment ‘test
tun,

Figure 8. Vans installed slougside facilities buildings a1 new DIS.

COVERER gromwd stative at New Boston, New Hampshire,

i

’



A "BY
orating
ding a
luding

LPM-4-222

lt
if

87

ao
Powered Flight Trajectory e “SECREY. so Wa See

H
af

ill;
hie

uk
Hitt

Schematic precentatiun af orbital srajectory following launch
rom Vandenberg Ain Force Base Brig Perlormed by

$fch station snd a living of equipment ied by tb mene
OS Riven ow page Acd,

RECOVERY CAPABILITY

This objective was added to the Program
after she frit launch achieved vebicle
light aud orbit objectives successfully,
4s includes the orientation of the asellive
rebicle to permit a secorerable tapsule to
be ciected from the ‘eose section of the
AGENA sebicle. Ejection iz Programmed
40 occar aw command on the 17th orbit.
capsule impsct within the Predeter.
recovery ares somth of Hawaii,
ralt aud surface vessels are deployed
iw the area ata vecorery force.

Capsule ejection command is seat to the satellite by she
Kodiak, Alaska station on she 1616 orbit. The vehicle
seorients its. position (see inset) to Permit ejection to occur
On 4 re-entry deajettory on the 171b orbit, The secorery ca|
sale peachuie 4 activated at about 30,000 feet, ent
se le beacon transmits « radio signal for tracking purposes.
recovery force is deployed in the secorery (imbecth wag,

WDLPM.4222 SECRET AS



AFGM)) Actwities in SPACE Fas 66
‘ $ bila ey, .

SATELLITE

- systems

—“s TY :
an 9 Nig

" DISCOVERER

SAMOS

MIDAS

COMMUNICATIONS
_ + SATELLITE



60

STF IMIAIMIJ/U[AISTOINIDI UI FIMIAIM J[JlalSlOIN| OfulFimlaimlslulalsloin| o

6l 62

Y 1 yt Le)

ATLAS “D“/AGENA ““B”’
on

1 1 y ft
CONFIGURATIONS | _ATLAS "D"/AGENA “A” _
MIDAS Launch Schedule

Monthly Progress—MIDAS Program

Program Administration

© The Air Force Bollistic Missile Committee hos
authorized two additional MIDAS flights, designated
RM-1 and RM-2, These flights will be THOR-boosted
and will use AGENA “B” vehicles currently in the
DISCOVERER Program. A background radiometer
will be carried rather than an infrored missile detec-

tion payload. These flights will provide infrared
background measurements for a wide variety of con-
ditions, es may exist between arctic ond tropical
regions. They will assist in determining the magni-
tude of background radiance in the 2.7 and 4.3
micron absorption range ond in establishing the
spatial and spectral background characteristics which
must be known for current os well as future MIDAS
requirements,

Figure 6, MIDAS ground Fi

the Vandenberg Air Force

WDLPM-4-228

sentation console installed in
bockbouse.

SteniT os



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

Ferret Reconnaissance...

Figure 4. The Perret reconnaissance syitem will gather deta from electronic emissions over reas of interest.

TyAl



i
| CONFIGURATIONS

—SRCRET

m

VEHICLE at uae
ATLAS "D'/AGENA

inn ii

~

ATLAS “D'ZAGENA "B"

SAMOS Launch Schedule

MONTHLY PROGRESS—SAMOS Program
Technicol Progress

Second Stage Vehicles

© System checks of the AGENA vehicle ond the
duo! payloed for the first SAMOS flight were com-
pleted satisfactorily on } June. The quality assuronce
inspection ond weighting operations were completed
Prior fo shipping the AGENA vehicle to Santa Cruz
Test Bese for captive hot firing tests. The vehicle wos
installed in the test stond, the payloads were deliv-

ered, and the sysiems tests which Precede hot, firings
were accomplished. Captive hot firing tests were con-
ducted on 30 June.

© Modification providing improvement in payload
Quxiliory real time command capobility (through
increased backup to the sirborne communications
‘equipment sequence programmer) are essentially
complete for the second AGENA “A’ vehicle, Lack
of @ UHF narrow bend transmitter continued to ham-
per checkout. Subsystem testing is being occom-
plished with « prototype norrow band transmitter,

Fixure 7. First SAMOS AGENA “A” vebicle ducing systems testing, Techeician at far right is adjust

1g the UHF erownd trausmitter 10 simulate
Bite) .

seus to the 16 the technician om bis le

WDLPM-4-222

encies of the rebicle ie orbit, Command:

fs ase being

“bese tess were completed ow 1 June.

~SEGREE


Figure 3. Helieupter recoter DISCOV:
ERER X11 capeule frum sa month
oh Hawaii. Frogmin iampe jate tes
tabote) to secure recover} Retr te eap-
twle. The capsule is rekud ww bs 6
balicupter winch trighs) vad the frog.
ma returned tw the belitupter trap

Photo. uppustte pags). The eapinte as
fiom the buds

shown prierte remetal dum ee
copter Abuttum Pluie, appusite paged.
tullonwing it: stain tu the recuter} torte
hip Hani

DISCOVERER Xiil...



Photograph of vecotery baewess
uganing capsile aud parsebaie,
tebe from within C-119 fuselage
on the third recovery attemps,

fed dete C19
#6 Of the nent.



© The first set of E-1/E-2 ground reconstruction
electronics (GRE) equipment, primary record comero,
ond repeoter kinescope hos been delivered to the
Vandenberg Air Force Base missile assembly byild-
ing. The second set of GRE ‘equipment (bockup for
the first set) was used for compat ity test with the
Operating console. At the conclusion of these tests
the operating console ond the GRE equipment will
be shipped to the Vandenberg tracking ond acquisi-
tion station.

© The 44-inch collimator, to be used for the £2
payload alignment ond checkout, has been com.
pleted and will be delivered in July.

Ferret Reconnaissance Systems

@ Ferret reconnaissance system payloads are being
developed in o minimum number of configurations.
The designation and purpose of each configuration
is as follows:

FIRED Test Poyloods

F-2—Digitel General Coveroge Poyloods

F-3—Specitic Mission Peyloads—Anelog Prerentation
F-t—Technical Anatysis (study stage only!

Payloods

© F-2 Payloads—The testing and assembly of
components for the initiel F-2 poyloods continues on
schedule.

Ground Suppert Equipment

© The first F-2 checkout console has been com-
pleted and competibility tests, using a service test
model F-2 payload, are being conducted.

© The logic design for the F-2 data conversion and
evaluation equipment hos been completed. This
equipment will be insiolled in the Satellite Test
Center.

@ The mojor portion of the telemetry data moni-
toring equipment was delivered to Airborne instru-
ments Laboratory on 15 June. This equipment will be
incorporoted into the F-2 evaluation ond command
complex for the Vandenberg Air Force Bose and
New Boston tracking and acquisition stations,

Figure 9. The jirst et uf E-I/E-2 ground recoustraction electronics (GRE) cqnip-
went installed ta the Vandeuberg Air Furce Buse missile assembly building.

WDLPM.-4-222



cook
Telemetry ships are positioned os required by the
specific mission of each flight, Figures 2 ond 3 show .
© typical lounch trajectory from Vandenberg Air aowna sa
Force Base, and figure 3 shows schematically « typ-
ical orbit. An edditionol objective of this Program is
the development of a controlied re-entry and recov.
ery copability for the Paylocd capsule (Figure 4).
An impact area hos been established necr the
Howolion Islands, and a fecovery force activated.
Techniques have been Geveloped for ceria! recovery . .
by C-119 aircraft ond for Seo recovery by Novy : i
surface vessels. The recovery phase of the Program } : [ruc ano
has provided advances in fe-entry vehicle technol. ‘ ! Sucen
O6Y. This information will be used in support of more N — SECTION
advanced projects, including the return of «manned tH |
satellite from orbit, i
FUGHT VEHICLE . ; ry sf —seransron
The three versions of flight test vehicles used in the a) Pt N
DISCOVERER Program ore defined in the lounch .
schedule shown on page A-5. Specifications for the
two THOR configurations and three AGENA configu- - ua
rations used are given on page A-1. srvenes
AGENA VEHICLE DEVELOPMENT wen
The AGENA vehicle was originally designed by the
Air Force es the basic sotellite vehicle for Advanced 98 jet system for orbital attitude control. An urgent
Military Reconnaissance Satellite Systems Progroms, need for attaining higher oititude orbits resulted in
Bosic design wos based On use of the ATLAS ICBM development of the AGENA "'B" versions, The YLR81
Os the first stage. ATLAS tralectory characteristics ond Ba-5 version of the LR81-Bo-3 engine (Bell Hustler
the stringent eccentricity requirements of the engine developed for 8-58 Sircratt) is used on
Sdvanced programs led to the selection of o guid. AGENA "AW vehicles. The YLR81-80-5 version of this
‘Once system suited to achieving orbital injection ino engine was developed to provide increased perform.
horizontal attitude. As o result, an optical inertial ance through the use of unsymmetrical di-methy!
system was developed for vehicle guidance ond a hydrazine (UDMH} fuel instead of JP-4,
Early AGENA “B” vehicles will use the YLR81-Ba-7
SAMOS ond MIDAS version of this engine. The mojority of AGENA “g
AGENA VEHICLE vehicles wilt use the XLR81-Ba-9 engine incorporating
GAS JET © nozzle expansion ratio of 45:1, and providing o

further increase in performance capability including
engine restart and extended burn-copability,

PERFORMANCE,
CAPABILITIES

200~20,000 mes
ATTITUDE
ROLL ~ 04 DeonEE

PITCH - 01 DEGREE
VW ~1 DEGREE

, tINES OF SHGHT—HORZON SENSING CENFIB:
-SECRET-4 vous



E-2 Payloods—Initial E-2 payload component testing
and assembly is progressing satisfactorily qt Eastman
Kodak. All components for the first flight payload
{to be carried on the fourth SAMOS fiight) ore
assembled and component qualification tests ore
underway prior to final payload assembly. Environ-
mental tests of the thermal mock-up in the high alti-
tude temperature simulator indicate that successful
environmental contro! of critical components can be
achieved under both hot and cold orbital conditions.

E-5 Payload—Development of the E-5 recovery pay-
load continues on schedule. Design releases for the
full-scale test models cre necring completion ond
fabrication of the initial test capsules is in progress.
Wind tunnel tests of the cerodynamic configuration
hove been completed, except for the shock tunnel
tests now being conducted at Cornell Aeronautical
Leboratories. Aerodynamic/thermodynamic tests of
the ablative heat shield ore scheduled to begin at
the Aveo Corporation test facility in early August. A
series of drop tests were initiated on 11 July at B
Centro, California to evaluate the merits of a single
large parachute ond a cluster of three smaller para-
chutes to determine the most suitable configuration
for copsule final descent. Tests to determine capsule

drag ond oscillotion characteristics during retrieval
into a recovery aircraft have started at Edwards
Air Force Base.

_ Ground Support Equipment

@ Delivery of major items of ground equipment to
Vandenberg Air Force Base in support of the initial
SAMOS flights is now complete. The electronics pack-
age for the visual reconnaissance poyload vecuum
fest chamber wos shipped to the missile assembly
building on 20 July.

@ Installation of the E-1 operating console, the sec-
ond set of E-1/€-2 visual reconnaissance ground
reconstruction electronics equipment, and two pri-
mory record cameras in the Vondenberg Air Force
Base data acquisition and processing building were
completed during the report period. Installation of
the UHF equipment required for initial SAMOS oper-
ations at the Vandenberg Air Force Base tracking
end acquisition station is complete, and the equip-
ment is undergoing systems integration. Also com-
pleted was the installation of the Model 1604
computer.

@ Assembly and checkout of the Progrommable

Integrated Control Equipment (PICE), to be available
for the third and subsequent SAMOS flights, ore

Bs a.



SCANNING
SYNCHRONIZER,

Hg 3. ,

im plified version 0} ind presen.
sation ped (left) Sor display of
infrored ee recomnaisiance data. The
data is displayed on a TV monitor
with a map overlay. The chart below
shows data flow from the readout
Stations to sistianmeking agencies.

PRESENTATION The MIDAS Control
UNIT other using agencies having a corre.
lated ground stabilized display, can
determine bas

enter, or

swhen an actual attach
been launched.

MIDAS ALARM EMPLOYMENT

PRESIDENT OF U.S,

DEPARTMENT OF DEFENSE |

NORAD
OTHER Us . — = OTHER ALUED
GOVERNMENT AGENCIES MIDAS “OPERATIONS CENTER] GOVERNMENTS
MIDAS TRACKING &
CONTROL CENTER
READOUT STATIONS /
SPACE VEHICLE NETWORK
CONCEPT
The MIDAS system is designed to provide three strategically located readout stations.
continuous infrared reconnaissance of the The readout stations transmit the dota
. e ditectly to the MIDAS Tracking and Con-
5 if ill 1°
ee Ueion sy unitence eee oe el Center whan es Processed. itis then |
ied by eight satellite vehicles in accu- displayed ond evaluated in the MIDAS
rotely positioned orbits {Figure 3). The area tions Center (Fi gure 5). If on "
inder survsillonce must be in fine-ofsight determined to be underway, the intent |
view of the scanning satellite. Mission capa- gence is communicated to a centrol Depart.
bilities are shown in Figure 4. The system is ment of Defense Command Post for relay to
designed to accomplish instantoneous read. the President and oll nationel retalictory |
out of ecquired dato by at least one of ond defense agencies.
SECRET * WDLPM4204 |



The DISCOVERER Program consists of the design,
development and flight testing of 35 two-stage
vehictes, using the THOR IRBM as the first stage
booster and the AGENA as the second stage, satellite
vehicle. The program wos ‘estoblished early in 1958
under direction of the Advanced Research Project's
Agency, with technical Management ossigned to
AFBMD. On 14 November 1959, progrom respon-
sibility wos tronsferred from ARPA to the Air Force
by the Secretary of Defense. Prime contractor for the
Program is Lockheed Missile ond Space Division.
The DISCOVERER Program will perform space
fesearch in support of the advanced military recon-
Aaissonce satellite Programs,

PROGRAM OBJECTIVES

(0) Flight test of the satellite vehicle cirframe, pro-
bulsion, guidance and control systems, ouxiliery
Power supply, and telemetry, tracking and com-
mend equipment.

(b) Attaining satelite stabilization in orbit,

(ce) Obtaining sotelite internal thermal environment
data.

(d) Testing of techniques for fecovery of a capsule
tiected from the orbiting satellite,

fe} Testing of ground Support equipment and devel-
pment of personnel proficiency.

(f) Conducting bio-medical experiments with mice
and small primotes, including injection into orbit,
re-entry and recovery. .

PROGRAM SUMMARY

Eorly launches confirmed vehicle flight ond satellite
orbit capabilities, developed system reliability, and
established ground support, tracking and data acqui-
sition requirements. Later in the program, biomedico!
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
‘overall operational control exercised by the Satellite
Tes! Center, Palo Alto, California.

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

WDLPM.-4-228

®@;<€lola

SECOND Stags

Weigt—
faart
Payleed equipment
Orbite!

tmpulse prepetients

Other

TOTAL WEIGHT
Engine Mode!

AGmNA
erty “a
1,262 1328 1346
2 a ws,
179 2.215 2216
6528 12,950 12,930
28 su it
9462 18476 15722
VURBIDe-S KURBIB07  XLR1 tap
15,400 15,400 16,000
77 277 290
120 0 20
Dm-38 Bm-21
6,950 6.500
33,700 33,700
2 8
Ma3 iy
Bleck Block 2
182000 167,000
1078 203
163 ry



The DISCOVERER Program consists of the design,
development ond flight testing of 33 two-stage
vehicles, using the THOR IRBM os the first stage
booster and the AGENA os the second stage, sctellite
vehicle. The program was ‘established early in 1958
under direction of the Advanced Research Project's
Agency, with technical management assigned to
AFBMD. On 14 November 1959, program respon-
sibility wes tronsferred from ARPA to the Air Force
by the Secretary of Defense. ime contractor for the
program is Lockheed Missile ond Space Division.
The DISCOVERER Program will Perform spoce
research in support of the advanced military recon-
feissonce satellite Programs.

PROGRAM OBJECTIVES

fe} Flight test of the satellite vehicle cirframe, pro-
Pulsion, guidance ond contro! systems, ouxiliory
Power supply, and telemetry, tracking and com-
mand equipment.

fb} Attaining setellite stobilization in orbit,

{cl Obtaining satellite internal thermal environment
date.

{d) Testing of techniques for fecovery of a copsule
ejected from the orbiting sotellite.

le} Testing of ground Support equipment and devel-
opment of personnel proficiency.

(f) Conducting bio-medice! experiments with mice
and small primates, ineluding injection into orbit,
fe-entry and recovery,

PROGRAM SUMMARY

Eorly lounches confirmed vehicle flight and satellite
orbit capabilities, developed system reliability, and
established ground support, tracking ond data ecqui-
sition requirements. Later in the Progrom, biomedical
and advanced engineering payloads will be flight
tested to obtain support data for more advanced
Space systems programs. DISCOVERER vehicles ore
launched from Vandenberg Air Force Bose, with
overall operational control exercised by the Satellite
Test Center, Polo Alto, California,

Tracking and command functions are performed by
the stations listed in the Table on page A-4.4 history
of DISCOVERER flight to dete is given on poge A-S.

i
s
€
°
Vv
e
r
e
r
SRCOND sTAGE “an -
Weight
faert * 1,262 1aae 16
Peyiead equipment = _ 497. a7 OF
Orbital Ws 2.25 2216
Impulse prepetions 6,525 12.950 12,950
Other 378 su Fit}
TOTAL wHGHT 62 15476 18722
Engine Medel YUREI-Bo-S = XiR81.00.7  21881-50-9
Tarvst-ths., vee. 18.600 15,400 16,000
Spec. Imp.-tec, woe, 27, 7 290
Bern time-s0c. 120 240 240
THOR soosteR om-18 BM.2t
Welght—Ory 6.950 6.500
Foot 33,700 33,700
Oxidizer (Ox) 68.200 88.200
GROSS WEIGHT fits) 108.850 108,400
e Cy)
fosine Bleck 1 tec?
Tarwst, oe, (SL) 152,000 167,000

Spec. imp, set. (5.4) 78 248.3
be 163



Sotellite Test Center ABC

Vandenberg Air Force ABCEFGHIJKLMPTU

Bose [tracking and
data acquisition
station)

Telemetry ships IKMS

Vandenberg AFB NO.

Northeast Station - CDEFHMPOR

{New Boston, New
Hampshire} :

Oahu, Hawaii

Kodiak, Alaska HIKLMTU
Point Mugu Hi
Point Arguello v

“Equipment

A. Medel 1604 Computer

Ground Preventetion Eauipment

Date Distribvtion Eavipment (FICE

Dete Conversion Eaviament

VHF Tracking Equipment

UNF Telemetry ond Deve Acauitition Eavioment
UME Command Antenna

. VERLORT (Mod 11] Reger

-"3OTMmone

¢
K Telemetry Recesving ond Recording Eaupmee

ST

ATLAS “D"/AGENA "A" . ATLAS “D"/AGENA “B"

Koena Point, ~ ~HIKIMTU-

il

MIDAS Launch Schedule

Facility Equipment* Flight Function

Operations contro! center of thie system during the R&D program.
Directs tracking station Operations, controls satellite Programming
‘ond communication system utilization, Receives ond stores key
vehicle and station dato, determines vehicles ephemerides and
generctes acquisition and trocking date to tracking stations,
Analyzes systems operation and telemetry and payload dato. -

Provides launch and ascent tracking, receives ond records telem-
etry data ond trajectory measurements. Gathers payloed doto,
telemetry and tracking dato and transmits this dota to the Satel-
lite Test Center. :

Ascent tracking and telemetry dato reception through AGENA
first burn period.

Provides ground rodio guidance system for booster guidance
during the launch phase.

Provides orbital tracking. Gathers Payload dato, telemetry and
tracking dota and transmits this dota to the Satellite Test Center.

Gothers supplemental Verlot tracking data during orbital posses.

Gathers supplemental Verlort tracking date during orbital Passes,
Ascent tracking for range safety; backup function.

Motes vehicles, performs final system checkout, prepares vehicle
for lounch and launches vehicle. . .

4, Plot Beerds for Rador ond TLM-18 Treching Dete
‘M. Doppler Dete Gathering Equipment

NN. AN/GOR.2 (OA-2] Tracking ond Monopulte Roder
©. AN/GRS-2 (XAA.2} Rote Measuring Systeme

°. Timing (ww) Equipment
9.
a
$s.
1
u

. VIF M/F Dete Aegi Equipment
vi VFM Dete Acquisition Equipment
High Frequency Radio Communications ond Teletype Circsits
Acquisition Progrommer for pre-ocavitition Dnrection ef Antenne:
- Conversion Equipment fer Teletype Trantmuven of Rader, TM.18
ond Depaler Tracking Date in Binary Format
V. Complete Levach Focilities

GROUND SUPPORT FACILITIES

WDLPM-4-245

SEGRE



Orbital Traj ctory
"Ps

Scbemeati

ezentation of erbinl Waestory following lensch
from Vandenberg Buse, Fanciions performed b3
cach station aud a listing of equipment aied by each sation.
it giten on page Add.

e RECOVERY CAPABILITY
g This objectir added to the rd
he fest leanth acbiored wehine

fier si
4, tht and orbit objectives successfully.
Ii nclades the orieatetion of the cacti
rebicle to permit a recorerable tapsule to
ciected from the nose section of the
IGENA rebicle. Ejection is programmed
40 occur on command on the 1716 orbit,
for capsule impact within the predeter.
tained recorery area south of Hawsii,
Airecalt and surface vessels ave deployed
within the aves asa recorery force,

CAPSULE RECOVERY SEQUENCE

PATH Soprale erection command is sent 10 the sate
Chiniak,

lite by the

. Alaska. station on the 16tb orbit. The vebicle

feorteats its position (see inet) 12 beret of ion $0 occur

Om 3 re-entry trajectory om the 171i it, recorery tap-
tale parachute ts attiested at abost 50,000 feet

capsule beacon transmits a vadio signal Jor racking Parpotes

The recusery force is deployed ia the recovery (impact) area.

tise ora SEGRET- ns



ORBITAL, |

COMPUTER
COMPUTER sumpaLieD
REACTION JETS
amin
asain
SLUPSE (300
STATUTE MILES)
ae NaS ma

Figure 2. Typical SAMOS trajectory, laxuch- t0-orbit. \

Ferret Reconnaissance...



S phe abate map indi rate the

satellites detect paaliotar radiation emitted
ES by Sariet ICBA's in light. Data telem-
wed fusantencously te rer niDas ¢ Control Center
via far worth reade data reveal
. approximately the aber of of ‘aia launched and
Lesath location, ction of and burning
» ehsvacteristics, Probabilities of lest shan 1.00 on
ility of wt least
ene MIDAS satell jetecting an I
Pr..bsbilitics of 1.00 indicate more then one
MIDAS satellite will always be in position odes

en ICBM Linach, These figures ave bas
of the family of aelltes oad

teadout station locations. .

—

TECHNICAL HISTORY

‘The MIDAS infrared reconnaissance payload is engi-
heered to use o standard founch vehicle configura-
tion, This consists of an ATLAS missile as the first
stage and the AGENA vehicle, powered by a Bell
Aircraft rocket engine os the second, orbiting stage
{Figure 1). The total payload weight is approximately
1,000 pounds.

The first two of the ten R&D flights used the AGENA
“A" ond ATLAS “D" vehicle programmed to place
the payload in @ circular 261 nautical mile orbit.
Subsequent R&D flights will utilize the ATLAS “D"/

WDLPM-4.228

AGENA “8” configuration which will be programmed
fo place the payload in a circular 2,000 nautical mile
potar orbit.

MIDAS I, launched in February 1960, did not attain
orbit because of a failure during ATLAS/AGENA
seperation.

MIDAS Il, launched in May 1960, wos highly success-
ful. Performance with respect to programmed orbital
parameters was outstanding. Useful infrared data
ware observed and recorded.

Spans -


attitude,
obit and

Wecopon
ansferred

Agency.
17L into

No. 38,
ferred to
59. A ten
aS (WS-
ol author.
+ two DIS.
and RM-2)
® support

DLPM-4-245

Figure 4.

Orbiting satellites detect infrared radiation emitted
by Sovset ICBMs in powered flight. Dats telem-
tered instantaneously to MIDAS Control Center
tia far north readout stations. Decoded data reteal
approximately the unmber of missiles launcaed and
Lanach location, direction of travel and. barving
characteristics, Probabilities of less shiz 1.00 on
the abore map indicate the Probability of ot least
ene MIDAS satellite detecting aw ICBM lanuch,
Probabilities of 1.00 indicate thst more then ene
MIDAS satellite will always be in Position to detect

ICBM Lennch. These heures ere based
metric considerations of the jamily of satellis
ground readout station locatic

on geo-
ites and
ious.

TECHNICAL HISTORY

The MIDAS infrared reconnoissonce payload is engi-
neered to use o standard launch vehicle configuro-
tion, This consists of an ATLAS missile os the first
stage and the AGENA vehicle, powered by o Bell
Aircraft rocket engine as the second, orbiting stoge
(Figure 1). The final configuration payloed weight
will be approximately 1,000 pounds.

The first two of the ten R&D flights used the AGENA
“A” and ATLAS “D* vehicle Programmed to place
the payload in a circular 261 nautical mile orbit.
Subsequent R&D flights will utilize the ATLAS “D"/

WDLPM-4-245

CONDITIONS:
2.000 a.m. ohitude
we orthogonal peter
‘erbitel plones, four
eavi-speced sateltites

oe

AGENA “8” configuration which will be programmed
to ploce the payload in o circular 2,000 nautical mile
polar orbit,

MIDAS I, founched in February 1960, did not attain
orbit because of a foilure during ATLAS/AGENA
seporotion. : 7

MIDAS II, Launched in May 1960, was highly success-
ful. Performance with respect to programmed orbital
Porometers was outstanding. Useful infrared deta
ware observed and recorded.

SECREX...

ce


ShGRET—

Facility Equipment* Flight Function
Sotellite A Over-cll control, convert irecking stations data to obtain o pre-
Test Center dicted orbit and generate subsequent ephemerides issue acquisi-

tion data to tracking stations for subsequent passes, predict
recovery area.

Vandenberg AFB BCDEFGHIUK Launch, ascent. end orbitel tracking, telemetry reception, trajectory
mecsurements including time to ignite second stage.

Point Mugu BCOEFGHUKL ‘Ascent tracking ond telemetry date reception, tronsmits commend
to ignite and shut down AGENA {vie guidance computer).

Telemetry Ship DF Final stage ascent tracking and telemetry dato reception.

(Pvt. Joe E. Mann}

Kodiak, Alaska BDEFGHUK Orbital tracking and telemetry data reception, including first poss

{tracking station) acquisition, recovery capsule ejection ond impact prediction.

Koena Point, BCDEFGHUK Orbital tracking and telemetry data reception.

Oahu, Howell

Hickam AFS, Over-all direction of capsule recovery operations.

Oshu, Hewalt

*Equipment ’ .

A. 2UNIVAC 1103-4 digital computers H. Plot hoords for redor ond TLM-18 trecking dete

1. VERLORT (Modified Mod ti) sedor |. Conversion equipment for teletype transmission of rodor,

C. TLM-18 self-trocking telemetering ontenne TUM-18 and doppler trocking date in binary format

D. Tichelin ontenna . 4, Acquisition progrommer for pre-sequisition direction of

E. Doppler senge detection equipment onternas

4. Telemetry tepe recording equipment

G. Telemetry decommutators for teal time dots preventotion

x, Grownd command 10 setellits transmission equipment
L. Gvidence computer

GROUND SUPPORT FACILITIES

(tracking stetion) |





Figure 3.

Schematic of SAMOS system
im operational orbit. W ben the
satellite is over the avea of
interest the sensing equipment
turned on 4 je
gathering). When it leaves
the area of interest the 4
ing equipment is turned 0,
a ie sexing data is proc.
essed (Information storage).
When the vebicle comes si
in range of a receiv.
ing station, the data will be
read-out upon command for
processing and transmitted to
asing agencies. This process
is continuously repeated dur-
ing the azefal | Lifetime of the

PHOTOGRAPH

- xy ° ad, 3
Visual reconnaissance soe Bee

US.S.R.

RECORD PROCESS

Figure 5.
The initial visual reconnaissance program will use con- stations thru a data link. Ground electronics will recon.
tentional photo techniques with automatic film proc. vert the signal into photo image forms, with a capability
casing aud-TV-1ype electronic image readout 7) growed * prolving objects 20 feet im length.

2 WDLPM-4-222

BS



PARAMETER NOMINAL ACTUAL
Apogee, Statute Miles 428 500
Perigee, Statute Miles 118 Wy
Eccentricity . 0.037 0.046
Period, Minimum . 93.4 94.5
Inclination Angle, Degree 79.6 19.6
Injection Altitude, Statute Miles 118 18
Injection Angle, Minimum 0 —0.22
Injection Velocity, ft/sec 26,150

TABLE Il. DISCOVERER XIV Orbital Parameters

© On the first pass over Kodiak, telemetry data
indicated on abnormal satellite attitude, stop indi.
cations by the horizon sconner and excessive con-
trol gas consumption, The satelite stabilized in its
Proper ottitude on subsequent posses and orbited as
planned.

ery force, homed on the CW beacon signol ond visu.

PDT, the heoks on the special Gir-recovery geor
snegged the nylon canopy. The chute and capsule
were carefully reeled in and at 1623 PST were safely
aboard the aircraft. The copsule is presently being
analyzed af the contractor's facility,

Technical Progress
Second Stoge Vehicles

© Only two DISCOVERER AGENA “A” vehicles
remain to be flown, DISCOVERER XV is at Vanden.
berg Air Force Base in preparation for a September
lounch. The remaining vehicle is at Sunnyvale for
modifications incorporatis 9 the improvements from
the latest flight tests,

@ssembly building. An additional AGENA “Bg hes
been accepted by the Air Force and is ewaiting
shipment to Vondenberg Air Force Bese. Three vehi-
cles have completed their test firings at Santa Cruz
Test Bose ond are being readied for Air Force accept.
ance inspections,

© Phose 2 of the Preliminary Flight Rating Tests
{PFRT) on the XLR-81B0.9 engine (serial number 306)
were initiated during August. After being retro-
fitted with flight configuration components the engine
was installed on the Bell Test Center vertical test
stond for initiation of stort-stop and malfunction tests.
A 30-second restart firing was accomplished, but test

© The DISCOVERER is the first satellite of major
size (above 1,000 Pounds) orbited by the United
States.

© The DISCOVERER is the first satellite to be
Placed in orbit over the north and south pole,

© The DISCOVERER was the first satellite to be

reoriented on orbit into a Programmed stititude.

TABLE III. Space FIRSTS achieved in DISCOVERER Program.

©@ The DISCOVERER was the first satellite to be
maintained ina stable eorth-referenced attitude
while on orbit,

© The first man-made object ever recovered
after a sustained Period in space was the cap-

sule ejected trom a DISCOVERER satellite.

|


It is anticipated thot assembly of this vehicle will be
completed on schedule.

Infrared Scanner Units
Infrared sconner waits for flights 3, 4, end 5 ere being menv-
fectured by Boird-Atomic, inc., ond for flights 6,7 ond 8 by
Acrojet-Generel Corporation.
© Delivery of the initial Baird-Atomic, Inc., infrared
detector payload has been made. This prototype
unit is undergoing tests ot the Lockheed facility, The
flight poylocd for the third MIDAS launch is now
scheduled for delivery in arty September. This
represents a two week schedule slippage.

© The delivery dates for the two Boird-Atomic, Inc.,
ground readout units have been established es 8 and
22 September. These schedule slippages, caused
by delays during systems tests, will have no effect on
flight schedules,

Facilities:

© Authorization has been granted to proceed with
the establishment of a satellite tracking station in
‘Africa. The primary function of this station will be to
record AGENA “8” second-burn performance dato.
A portable van installation will be utilized to support
the third MIDAS fight scheduled for February. The
AMR siting team has selected the location for this

station. The design criteria were completed by |

AFBMD and supplied to AMR during August,

© Initial studies are underway for modification of
the New Boston, New Hampshire, data acquisition
and processing building to accomodate MIDAS
equipment.

WDLPM-4.234



Facility Equipment* Flight Fenction

Sotellite A ‘Over-all control, convert tracking stotions dato to obtain a pre-

Test Center dicted orbit and generate subsequent ephemerides issue acquisi-
tien data te tracking stations for subsequent passes, predict
recovery oreq.

Vandenberg AFB BCDEFGHIK Launch, escent and orbital trocking, telemetry reception, trajectory
mecsurements including time to ignite second stage.

Point Mugu BCDEFGHUKL Ascent tracking ond telemetry data reception, tronsmits command
to ignite and shut down AGENA (via guidance computer).

Telemetry Ship OF Final stage ascent tracking and telemetry deto reception.
(Pvt, Joe E. Mann) ,
Kodiok, Aloske BDEFGHUK Orbital tracking and telemetry date reception, including first poss
Kaeno Point, BCDEFGHIK Orbital tracking and telemetry dato reception.
i Ochu, Hawaii
° (tracking stotion)

Hickam APB Over-oll direction of capsule recovery operations.
Oahu, Hawaii .

eS

*Equipment ’ .

|. ZUNIVAC 1103-A digital computers +H, Plot beerds for coder end TLM-36 tracking dato

VERLONT [Modilied Mod tl) rodor 1, Conversion equipment for teletype transmission of rodor,

-. TLM-18 setl-tracking telemetering entenne: TUM-18 end doppler tracking dota in binary formot

1 J. Acquisition progremmer for pre-ocquisition direction of .

ontennas
kK. G to satellite
1. Guidonce competer

Doppler renge detection equipment
. Telemetry tape recording equipment
. Telemetry decommutotors for real time data presentetion

gmnone>

GROUND SUPPORT FACILITIES

(tracking station} cequisition, recovery capsule ejection and impact prediction. |



MONTHLY PROGRESS—DISCOVERER Program
Progress

®@ During August o significant milestone was
achieved in the DISCOVERER program when the dato
topsules of DISCOVERER XII and XIV were ejected
from the orbiting satellite, re-entered the earth's
atmosphere ond were recovered successtully within
the programmed area north of the Hawaiion Islonds,
These two copsules represent the first objects to hove
been successfully recovered from on orbit in space.
As such, they take their ploce mong four other
“firsts achieved by the DISCOVERER Program {see
Table itt).

DISCOVERER Xi

©@ DISCOVERER XIII was lounched from Vanden-
berg Air Force Base ot 13:38, PDT, on 10 August and
was successfully injected into polar orbit. THOR
booster trajectory was slightly high and west but wos
well within tolerance. Second stage separation wos
successfully accomplished os wos transmission of
Commands 5 (time-to-fire correction) ond 6 (velocity.
to-be-gained correction). AGENA Performance was

very close to norminal. Re-orientotion of the satellite
into a nose aft attitude was @ccomplished after burn-
out. Table | lists nominal and actual orbitel Poram-
eters.

PARAMETER NOMINAL ACTUAL
Apogee, Statute Miles 408 = 429
Perigee, Statute Miles 400155
Eccentricity 0.0323 0.0326
Period, Minimum 935 94.1
Inclination Angle, Degree 81.69 82.67
Injection, Altitude, Statute Miles 140 156
Injection Angle, Minimum (') +0.08
Injection Velocity, ft/sec 25,852

TABLE I. DISCOVERER XII Orbital Parameters

© = The recovery sequence was Gutomatically initi-
Gted by the soteliite programmer 26 hours, 37 min-
utes after launch. This event occurred within range
of the Kodiak, Aloske, tracking station as DISCOV-
ERER XIN possed southward toward Hewsii on its

Fogure 1. Second stage AGENA tebscle Jus DIS-
COWERER N11 during systems checkout tabote)
ud wating with THOR fist stage tright). The
Delium and uitrogen sphevie visible in both Phatar
tte wied tus propellant tied pressurizane
satellite orbital attinde canted system n

AS

|



Figure 7. The Baird Atomic. lee, ia

asd
facility,
MIDAS

4°) 1961. The paylosd check
ir the equpace th ee

during checkou: at
This payload will

tbe ech
be carvied un

Hight which is farventl) scheduled

Suanyrale
the third
for Febru.

lout equipment is coutsived
eH ow the background.



© Deliveries of flight hardware for the third
AGENA “A” vehicle will be completed in July. Lote
evailability of components ond the recent strike will
require intensive efforts to. recover current schedules
for this vehicle.

© The first two AGENA “B” vehicles ore in the com-
Ponent ond subossembly stoges of manufacture, with
the first scheduled for completion in mid-September.
This vehicle is scheduled for lounch in April 1961
carrying an £-2 poyloed.

© Because of the attitude contro! problem experi-
enced on the second MIDAS flight, the first three
SAMOS seotellites will maintain a horizontal, nose
forward position throughout most of the first orbit,
Reorientation to the nose-down position will be initi-
oted by stored commands os the satellite comes
within range of the tracking station at Kodiak,
Alasko, on its first orbital pass. This change assures
completion of tank pressurization venting prior to
shutting off the flight control system pneumatics, The
forces created by the. continuation of venting after
switching from the flight control to the ottitude damp-
ing system are believed to be o major factor in the
boss of attitude control. Modifications to the AGENA
wiring and airborne components for the first flight
article are scheduled to be accomplished during the
Vandenberg Air Force Base modification and check-
out operation. Modifications for the second and third
vehicte will be occomplished at the systems test focil-
ity. The AGENA “B* vehicles will incorporate a full-
time attitude control system ond will not require
modification.

Visval Reconncissonce Systems

© Visual Reconnaissance Systems payloods ere being devel
oped in @ minimum number of contigurctions te attain revdeut
‘and recovery mission ebjectives. The design end purpose of coch
configuration is os follows:

Readout:

£-1—Component Test Payload:

£-2—Steereble Reconneissance Payload (with 20-leet ground
tetolution!

Recovery:

£-S—High Resolution, Steeroble, Receveroble Payload (with
S-feot ground resolution) .

Figure 8. Thirty-six inch focal engi camera and lens assem
by for E-2 payload. Payload delivery is scheduled for August.

Bé

Payloads

© = £-2 Payloads—Assembly of £-2 payloads con-
tinves on schedule ot Eostmon Kodak. The film drive
system and the film processor for the first E-2 poylood
hove completed functional and Operational tests suc-
cessfully, The completed 36-inch focal length camera
ond lens assembly are undergoing vibration ond
Operational tests at the contractor's facility.

© £5 Payloods—The first test of on E-5 recovery
test unit {RETU) is scheduled for July at Edwards Air
Force Base. The RETU simulotes the E-5 recovery cap-
sule in size, weight ond cerodynomic configuration.
This test series will determine capsule drag ond oscil-
lotion choracteristics during recovery by o C-130A
aircraft. Dato from these tests will be used to estab-
lish design criteria for the E-5 recovery equipment.
‘Additionol RETU tests, including the complete recov.
ery sequence, will be conducted later this year. A
mid-Februory 1961 date has been estoblished for
delivery of the first E-5 flight payload.

Ground Support Equipment

© Functional tests of the electronics portion of the
vacuum lest chamber (used for leak testing E-1 and
E-2 payloads) were completed by the contractor and
the chomber was delivered to Vandenberg Air Force
Bese. This completes the delivery of mojor items of
the E-1 payload ground support equipment for the
Vandenberg Air Force Bose missile assembly build-
ing.