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H. ATTTTUDE STABILIZATION AND STATION KEEPING.

With refinements in the employment and placement off new direc-
tional antenma types, the orientation of the vertical axig of the
satellites became a factor affecting performance. Satellites which
tumbled or orbited upside down or sideways did not orient theiz ELINT
antennas to produce optimum coverage if azimuth. To overcome this
problem, a Gravity Gradient Stabilizati, periment (GGSE) wag
implemented in the eighth launch (Mission « me satellite was

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_ NRO RENT FOR RELEASE ‘

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SE

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OR pRTED

SOIT Ayy

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= 1972

POPPY MGS - Buffered Digital Tape System

-32~

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ANNEX 4

GLOSSARY OF POPPY-RELATED TERMS

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——!) |

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1. NINTH LaucH - missiou BBE 9 marca 1965

were deployed ag separated
‘st 3-axis gravity gradient stabiliza~
rform ag planned and the satellite flew

sideways. Congequently, first attempt to use a microthruster for
stat lonkeeping could not be evaluated on this satellite.

Deteriorat: the storage batteries of
caused their tasking suspensions after about
eration. The impact wad a loss of som

With &ne
‘ing several months
n# when high sunlight conditions prevailed, the
ted for fj months,

Ow voltages created
months of useful life, leav:

J. TENTH rauNcH - MIssION[M 31 may 1567

The “thermal design of the Mission MMMM maltifaced satellites
favored the cold end of the thermal specification range and led ta
high battery yoltages. ‘he impact was negligible since the satellites
could be activated to reduce the voltages even when not used for ELINT
collection. Such activations were easily implemented by the 5é-minute
activation period and the capabilities fot delayed activation and
recycled activations at 16¢-minute intervals,

= a stretched sphere with conservative solar cell power
system Bann using four solar cell are on cam entepee iad
exper er system low voltages during periods of low I
and had to be conservatively tasked thereafter,



‘NRO APPROVED FOR RELEASE

soccer

First U.S. SIGINT Satellite,
GRAB/Dyno 1 mounted above TRANSIT 2A

-9-

ceaes - a


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6 June 2012

BADE SAE - SANE TOTTI,

‘TENTH LAUNCH

PROJECT NAME: -FOFFY (Byenan [i

nro wzssiox:

LAUNCH: Thor-Agena D from Vandenberg AFB, California on
31 May 1967

ORBIT: Nearly circular with 588 by 588 nautical mile
altitude, 78.0 degrees inclination, and period of
193.3 minutes.

GROUND STATIONS:
SATELLITES:
DIAMETER INCHES: 24
WEIGHT FOUNDS: 189

NUMBER RF BANDS:
RF COVERAGE MHZ

OF LIFE:
USEPUL LIFE:
INNOVATIONS: Aspect monitoring systems on all satellites.

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ERNDH-VEA-BYPMAY TRENT RELIOLE/COMINT CONTRO SS TEMS COT


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ANNEX 1
MISSION CHARACTERISTICS

Al-1

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BANDIT EA BARA TAREE OLE AEGON TROIS TENE JOBE

THIRD LAUNCH

PROJECT NAME: GRAB (Walnut security clearance)

NRO MISSION: Pre-NRO

LAUNCE: Thor-Able-Star from Cape Canaveral, Florida on
29 June 1961

ORBIT: Elliptical with 475 by 548 nautical mile altitude,
66.8 degrees inclination, and period of 103.8
minutes.

REMARKS; Pickaback with INJUN - failed to separate. ‘This was

the second separation failure of NRL Satellites.
Design of these separation systems had not been an
NRL responsibility but on all future launches NRL

took the responsibility for a their own

SATELLITES: Dyno 2, INJUN (SUI) and Transit IIIB (APL)
DIAMETER INCHES: 28 a

END OF LIFE: August 1962

USEFUL LIFE: 14 months

INNOVATIONS: RF coverage extended to two portions of the
spectrim.

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(uo @3SUI INH ASA) SETOTUA SITTTEIeS YIAeR TeOTdAL
UOTFeIS punozy UOTSSTW AddOd

-19«

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a -n__



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cowreewerewerymentiatitti mi cnteAlPAR intchetiittwiemwiiniinNiem—de biti

Used Bddy current damper to control librations.

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DL BUENA ECE COME SA SISTINE TOD

ELEVENTH LAUNCH

PROJECT NAME: POPPY (Byenan

nrc mission:

LAUNCH: horad-Agena D from Vandenberg AFB, California on
3@ September 1969 .
ORBIT: Nearly circular with 491 nautical miles perigee and

586 nautical mile apogee, 70.0 degrees inclination,
and period of 163.5 minutes.

REMARKS: ‘Thorad-stretched fuel tank on booster
GROUND STATIONS:

SATELLITES:

DIAMETER INCHES: 27 27 27 27
WEIGHT FOUNIS: 235 228 247 236

NUMBER RF BANDS.
REF COVERAGE MHZ

END OF LIFE:
USEFUL LIFE:
TNROVATIONS:

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; 6 June 2012
HANDS i -BUGMAN SUALENE-RGMRIOLEGOMDD-OONURGlr-GUSTENS —JORTTLA-
‘TTELFTS LAUNCH
PROJECT NAME: POPPY (Byenan

nro mssion: =

LAUNCH: Thorad-Agena D from Vandenberg AFB, California on
14 Decembeer 1971
ORBIT: Nearly circular with 538 nautical miles perigee and

548 nautical mile apogee, 78.6 degrees inclination,
and period of 164.9 minutes.

GROUND STATIONS:

a

DIAMETER INCHES: 27 27 27 27
WEIGHT POUNDS: 270 - == .278 282 282
NOMBER FF

RP COVERAGE’

END OF LIFE:
USEFUL LIFE:
TNOVATIONS:

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VII. OATA PROCESSING

A. GRAB DATA PROCESSING

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fitted with an extendal

2-axis gravity gradient stabilization experiment succeeded in aligning
the satellite's axig to within[[§ degrees of tha local vertical and
consumed no on-board power. ‘

Pete Gradient Stabilization was also implemented in Mission
including 2-axis gravity gradient and 3-axig gravity gradient
two additional booms to provide yaw stabilization. In Mission

two satellites were equipped with 2-axis gravity gradient sta~
bilization, and two were equipped with the 3-axis systein. One of the
3-axis stabilized satellites used additional booms) the other used a
flywheel to provide active stabilization of the yaw axis. All satel~
lites launched thereafter used the 3-axis, active system. employing 4
single boom and flywheel. ot

Anhydrous ammonia wes successfully used as the microthruster gas
in one satellite in 1967 and in all satellites launched thereafter.

Three axis stabilization was a necessary prerequisite to the
station keeping capability.

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V. GROUND READOUT EQUIPMaRT

Mission ground station functions related td ELINT data collection
included telemetry readout, satellite interrogation, and ELINT data
monitoring and recording, All mission ground stationd perforined the
.eleme xt sored and recorded # data apab

B. INTERROGATION

All satellites in 508 nautical mile orbits which came within 1758
nautical miles of. an interrogation site could be commanded or inter-
rogated upon acquisition and readout of the telemetry signal. ‘The
output of a command tone generator was fed into a transnittey with a
258-watt power output and propagated directionally on an array of four
1@-element Yagi antennas fitted on the same mast as the telemetry
antenna array, The satellite ELIND receiver(s) and data link trans~-
mitter(s) would be powered-up or activated when interrogated the
command signal froin the ground station. ‘The interrogation would be
verified by interpreting state of command data in the telemetry
stream.

With the move into permanent buildings, the manually steered
antennas were replaced by remotely steerable, pedestal-mounted arrays:
consisting of two rows of four cross-polarized Yagi antennas, These
antennas could be trained in both azimuth and elevation, permitting

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FORO SHHET2:

Pirst Generation

GRAB/Dyng 1
Receiving, Timing, and Recording Position ineide ESV Hut

-19+

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—reniolond? 2

Typical 27" Multifacs satellite
Missi

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HANDLE GA BUEMAN ALD ar IDOL SISTINE TOL —

1971 OCEAN SURVEILLANCE AUGMENTATION

SYSTEM ENGINEERING AND INTEGRATION

Mr. L. M. Hammarstrom of HRB and, subsequently, NRL provided

overall spacecraft/ground station engineering, integration, and
testing functions 1964 through 1976.

.

GENERAL

The above names and contributions are representative of gen-
erations of talented and dedicated individuals from NRL, NSA, NSG,
AFSS, ASA, CIA, HRB, ONI, Program C staff, Program-A, NRO, staff, and
NAVSPASUR who developed, operated, supported and exploited the POPPY
system.

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rere errors rer 20 Re ccerentrem erste ete —wirtttt

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Intercested pulses transponded ot [i
on 158 MHz omni-directional data down

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program; and disseminated quality control technical data to mission
ground stations. ‘the STIC member of the 10G was designated as the
product control representative.

6. Ag of 1962, the Amy Security Agency (ASA) provided a site,
support facilities and operating and maintenance personnel at the ASA
mission ground station,

7. ‘The sites where dedicated GRAB/Dynd collection and

c Pro-
cessing and spacecraft commanding systems wete installed in the
pre-NRO period are as follows:

ee ee eee

eee ee eee

ADAK, ALASKA... 6 2 eee ee ee et

BYBIA VALLEY VIRGINIA (Engineer ing
Ground Station)... 6 2 ee eee eee

WAHIAWA, HAWAIT 2. ee ee ee ee

’ B. NRO PROGRAM C

Upon consolidation of al] U.S. overhead reconhaissance Projects
into a National Reconnaissance Program (NRP) in 1962, DNRO established
NRO Program C as the organizational. component to continue operation
and management of the Dyno satellites. By December 1962, the Byeman

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—eelaacecion a a antatnctahaoentt ctenetaitnacstctentie

SEVENTH LAUNCH

PROJECT NAME: POPPY (Byenan

nro mission: (RD
LAUNCR: ‘Thor-Agena D from Vandenberg AFB, California on
15 dune 1963 .
ORBIT: Highly elliptical with 95 by 495 nautical mile

altitude rapidly decaying, 69.9 degrees inclination,
and period of 94.1 minutes.

REMARKS: No Agena second burn - failed to circularize.
GROUND STATIONS:

ae
DIAMETER INCHES: 24
WEIGHT FOUNDS:
NUMBER RF BANDS:
RE COVERAGE MZ:

ENO cP LIFE:
USEFUL LIFE:

INNOVATIONS:

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. a Bolupe 202i sus .

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ENE DERM DADO TE -CTT ie GUE TENE IO

NINTH LAUNCH

Soe

PROJECT NAME: POPPY cevenen

nro mission: (J
LAUNCH: Thor-Agena D from Vandenberg AFB, California on
9 March 1965
ORBIT: Nearly circular with 498 nautical mile perigee by

586 nautical mile apogee, 78.1 degrees inclination,
and period of 163.6 minutes.

GROUND STATIONS:

SATELLITES:
DIAMETER INCHES: 24 24 24 24
WEIGST FOUNDS: 163 186 138 138

NUMBER RF BANIS:
RE COVERAGE MHZ:

ED LIFE:
USEFUL LIFE:
TNROVATIONS:

‘Thr i avity gradient stabilization implemented
ee

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FOOTNOTES ON FUNDING

1 yRP funding authorizations do not include funding to Program A for
costs of launch vehicles end for launch vehicle/satellite

integration.

4 Cumulative program costs for 14 launches (11 successful)
as well as building, deploying, maintaining
ound stations for an 18 year period was approx
lollars, excluding Program A costs for launch vehicles.

| BYE-56105-78



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6 June 2012

respond with a tremendous effort and close that gap. In retrospect
the Vanguard program with its cular failure but subsequent suc-
cess and its tremendous technology advances may have been the best
‘thing that could have happened to the infant U.S. space program.

‘Also, of much wore specific value to the Navy was thé fact that
Vanguard had developed 2 technology base in satellite desigh at NRL
which formed the foundation for the subsequent POPPY program,

These first spece exploration successe§ stimulated the Advanced
Reseatch Projects Agency (ARPA) to solicit other DOD elements for pro-
posalg for spaca related projects. ‘The Chief of Naval Operations
(CHO) relayed the query to Navy scientific and technical. organizations
by asking, "All hands to consider how they could use space in their
design ideas for the Navy."

NRL responded to the QW query with the proposal to leunch a
satellite intq a 5€@ NM circular orbit. ‘he satellite would be
equipped with an § band crystal-video receiver to detect signals of
sufficient power density and would use an uncoded redar beacon to
transpond them (pulse-for-pulse) down to cooperative ground stations
for recording and subsequent analysis, ‘The proposal was reviewed and
approved through the Navy and DOD and was approved by the President in
August 1959 as Project TATTLETALE.

esident toa SESe

Order to tighten security, A special security system was then estab-

lished by the Office of Neval Intelligence (@NI), Access was Limited
to individuals with a strict need-to-know and required the approval of
GNI, ARPA, or the Office of the Special Assistant to the Secretary of
‘Defense (Special Operations), Those individuals granted access were
required to execute a project secrecy agreement. =_- :

NRL developed the conc and designed thé ELINY satellite and
ground readout equipment which was continued as the top secret Project
Walnut. Additional security wed provided by adding an NRL scientific
cover experiment designed ta telemetér measurements of solar activity
in X-ray, Lyman-Alpha, and ultraviolet rediations above the earth's
atmosphere. Thig cover experiment becama the first, of a series of
SOLRAD satellite experiments designed and exploited by the Naval
Research Laboratory. ‘The cover namé GRAB. (Galactic Radiation and
Background) wag used for the intelligence and scientific satellite.

With the first launch pending, new importance was added to the
project after the crash of a U-2 high-altitude reconnaissance aircraft
in the U.S.S.R. on 1 May 1966, Subsequent cancellation of routine U-2
overflights ended the capability for deep interior surveillance of the
U.S.S.R. Future overhead surveillance missions would ceduire presi-
dential approval.

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I. CONCEPTION

During the second world war, lookouts on German submarines used a
hand-held crystal video typd radar receiver named ATHOSS to detect
pulses emitted from search radar on allied warships and airplanes,
This simple passive electronic countermeasure receive enabled evasion
before range had closed sutticiently for ceturning raday echoes to
indicate presence of thé submarine to the searching warship or
airpl «After the war, ‘ceystal video receivér technology was
applied in the direction finding pystens for use on American warships
and airplanes because of its simplicity, ite small size and wide open
frequency detection characteristics. By the late fifties, a crys'
video receiver wag being fitted to type 8-4 submarine Ber iscopes the
first three ‘receiver prototypes were developed by the Naval Research
Laboratory (NRL) in late 1957.

On 4 October 1957, the Union of Soviet Socialist Republics
(U.8,8.R.) launched the first artificial satellite as pact of the
thirty-month International ical, Year. ‘Thirty days later, the
second Sputnik wag launched with a live dog as a passenger.

About one month later on 6 December 1957, with the whole nation
watching on National television; the United States (U.S.) attempted
its first satellite launch on a totally new sophisticated Vi rd
missilé. ‘the payload waa the grapefruit sized Ve rd satellite -
weighing three pounds, ‘The mis#ile lost thrust after 2 seconds and
crashed in a huge ball of flames, ‘the tiny satellite fell out of the
nosé -fairing and rolled away, Its antennas were bent and broken and -
charred black from the fire + yet it was still transmitt its sig-
nal. ‘his national embarrassment triggered a mmber of is, The
inmediate resuits were @ presidential decision to task the Army team,
under Dr. Wernher von Braun at the Redstone Arsenal, to launch 2
satellite on the existing ICBM called Jupiter C, Fortunately, these
efforts did met with success and on 3} Jaruary 1958, the U.S, placed
its first satellite, Explorer 1, in orbit, & satellite discovered
the Van Allen belt, ‘tha Navy Vanguard team succeeded on Saint Pat-
tick's bay, 17 March 1956, by placing Vanguard I in a highly ellip-
tical orbit. ‘this satellite, powered by solar cells, transmitted its
signa] for over six years stable orbit with constant. transnis-
sion from the satellite permitted the first long term observation of
orbital dynamics. ‘This resulted in the discovery of the “pear-shaped
earth" and initiated 4 series of sti¢ated modeling efforts of the
earth's gravity fies which ig so tant for predicting satellite —
positions ve tine and for ballistic ile accuracy. .

But the Vanguard initial failure also had other longer range
effects. Tt caused the nation to re-evaluate its position in the
newly arrived space age. We felt threatened in that we seemed to be
falling: behind in this new high technology area, & franti¢ call went
out to better educate more engineers scientists in our colleges
and universities. ‘The gauntlet had been laid down and America would

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II. ORGANIZATION .

Throughout its lifetime the POPPY project was managed, operated
and suppor ted by a number of DOD elements under overall Navy leader-
ship. @ were two distinct phases of organization, pre-NRO and the
reorganization following establishment of the NAO in 1962, Suring
both of these phases," multi-agency activities were coordinated by
means of 4 Technical Operations Group (TOG).

A. PRE-NRO

Directorship of Project GRAB/Dyno (see Annex 3) was assigned to
the Director of Naval Intelligence (INI). The 10G acted ag the steer~
ing committee or staff of the project director. ‘The 10G membera were
drawn from designated DOD organizations and thé National Security
Agency (NSA). ‘he participating organizations, their responsibil~
ities, and the staff responsibilities of their representatives to the
TOG were specified by the DNI. :

1. thé NRL developed the overall system concept; designed,
constructed, deployed, and logistically supported electronic receiv-
ing, recording, and timing equipment at mission ground stations;
designed, fabricated, tested, and calibrated the satellite systems

"from concept through launch injection into orbit, and provided engi~

neering and technical direction through the operational exploitation
phase; trained mission ground station personnel; controlled the satel~
lite prior ta launchy monitored the launchj and monitored on-orbit
performance of the satellite.. The NRL member of the 103 was desig-
nated ag the project technical representative/project managez until
January 1971, : : .

2, "the Naval security Group (NSG) directed and” coordinated all
mission ground station operations; acted ag the focal point for all
electrical communications associated with the operations of the pro~
ject; provided sites, support facilities and operating and maintenance
personnel at the NSG mission ground stations. ‘The NSG member of
the T0G wag designated ag the project. operational representative.

3. ‘the NSA authorized the allocation of service cryptologic
personnel to men and operate the mission ground stations; processed
all ELIN? data recordings and disseminated the ELINT product; inter-
preted national intelligence collection and processing requicements
and itade tasking recomendations; and furnished the tig tapes for
recording data at the mission ground stations. ‘the NS representative
to the TOG was designated as an advisor to the staff. -

4. ‘The INI had the authority to review and approve all aspects
of the project. ‘the Scientific and Technical Intelligence Center of
GNI (STIC) provided intelligence requirements to the director; pro-
vided signal analysis support to NSA; monitored the signal analysis

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A3-8 8

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ANNEX 3
KEY CONTRIBUTORS

A3-1

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aus 2012

ELINT COLLECTION (NRL)

Mr. Mayo established the overall performance requir
ELINT si tems in the succession of satellites based on
derivation of suitable collection requirements from the
current na’ 1 intelligence requirements. ‘he chief designer of the
ELINT payloads was Mr. V. S. Rose. ‘These designs were implemented,

tested, and installed in the Dyno and POPPY satellites by Messrs. V.
S. Rose, E, G. Becke, and L. £. Earl.

Mr. Mayo designed the original collection system for the ESV huts
and supervised implementation. Later réfinements and expansions of
the collection system inside permanent buildings were supervised by
Mc. Mayo with designs and implementation and testing by Messrs. F. v.
Hellrich and W. M. McDavit of NRL and by Messrs. L. M. Hammarstrom, M.
J. Van de Walle, and J. N. O'Connor of HRB-Singer, Inc.

SATELLITE STATIONKEEPING (NRL)

Mr. oR. T. Beal designed and implemented the 2-axis gravity
gradient stabilization used in the POPPY satellites. Mr. Beal also
Gesigned and implemented the passive ‘tip mast yaw stabilization
concept to provide 3-axis stabilization. The active, electronic
flywheel yaw stabilization method was adapted from Nimbus satellites
for POPPY by Mc. G. E. Flech. Mr. F. Raymond ceveloped the speci!
tions for injecting multiple satellites irto their desired orbit:

The microthruster subsystems were designed by Mr.
Ww emented by Mr. P. Carey. Satellite aspect monitoring
and control methods were developed by Messrs. Wilhelm, Beal, Raymond,
and Rovinski. Mc. Raymond determined the timing and degree of thrust-
ing necessary for stationkeeping. Actual thrusting manuevers were
conducted by Messrs. Wilhelm, Carey, and Beal. we

LAUNCH VEHICLE/SPACECRAFT INTEGRATION

Mr. Dix coordinated integration efforts for the launches from
Cape Canaveral. After 1962, the Director, Program A had the respon-
sibility for booster/spacecraft integration. During later POPPY
launch preparations, CAPE G. Geyer USAF supervised contractor fune-
tions and coordinated with NRL representatives from Mr. Wilhelm's

organization.
sons I 2

. Bisenhauer conceived and designed the signal eve] SS
measurement experiments used in POPPY. ‘These designs were
mented and refined by Messrs. B. W. Ryon and J. W. Phillips.

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2-0 I cc

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PCY Ge UTWALE

Mecanial falda
rev eet

HISTORY OF Un
WPPY SATELLITE SOS Etat

rad |



MISSION GROUND STATION FACILITIES (NRL)

Mr. C. W. Price adapted the ESV huts for Dyno and POPPY inter~
rogation and collection functions, including the ESV hut layouts and
installations of equipment. Later, Mr. Price coordinated the moves

into permanent buildings and equipment installations with cognizant
personnel He developed the preliminary building
design ac: y concept as well as provided the layout of the

operational equipment for the receiving recording and data processing
for the three MILCON projects.

MISSION GROUND STATION OPERATIONS MANAGEMENT (NSG)

CDR F. Hitz chaired the first TOG steering committee and super-
vised the development of the GRAB/POPPY operations management system.
Key focal point managers during the project's coming-of-age were
Commanders L. McGraw and R, W. Olson. Among the POPPY project
officers at mission ground stations making significant contributions
to management and data exploitation were Lieutenants R. L. Potts, R.
E. Lentz, B. F. Booth, and R. L. Kellogg. CPO R. B. Kargle was fore-
most among the senior enlisted men who managed personnel and day-to-
day operations and propagated their knowledge of ELINT in the field.
LCDR J. Morgan of NSG headquarters coordinated operations with POPPY
project, officers during the early seventies and organized the POCG at

n . .

NSA DATA PROCESSING

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L.  TWELPTH LAUNCH - MISSION) 14 veceaer 1972

same occurrences of cross-talk in receivers of Mission.

radation of storage batteries, starting with in

which very.slightly constrained tasking a We
lead to power ae, i slightly re-

s' king, Thus conserved, retiain useful to
date. :
BYB-56185-78
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SEA nN NTN I ONT ERE TITTY


to enhance the
detection and recognition of the new emitters as they were added to
the Soviet redar inventory during their rapid build-up during the.
1968's. These Soviet radar chanes started wi iginal designs in

and changes’ made to the satellite designs: in order

almost ail Of woich were ini

2. In 1967, GNI became redesignated as the Naval Intelligence
Command oe. COMNAVINICOM retai the responsibility of Director,
Program C. .

3. In response to the 1966 Presidents Scientific Advisory

patiel's urgent request ta expoit overhead reconnaissance to determing

_ if the Soviet Union was ibsllistic missile radar sys-
tem the program site in was equipped. with anal:

to-digital data conversion a a ‘processing computer. ‘This
a ig system ms installed in

4, AFSS participation endéd in Oc osure of
its last POPPY mission ground station at

5. ASA participation ended i 78 with the closure of
its POPPY mission ground station at :

6. On 14 January 1971, the Navy Space Project Office was estab-
lished as PM-16 of the Naval Material Command. ‘The Manager, Navy
Space Project (F¥-16) was designated as the Director, Program C.

PY project director functions were performed within the System Pro-
ject. Office {SPO} of FM-16. Liaison with NIC continued.

7. In June 1973, PM-16 was redesignated as PME-186 of the Naval.
Electronic Systems Command with its manager continuing as Director,
Program C.

8,

9. .m2 , the Director, Program C directed cegsation
of the POPPY Mission! ra . However, the Engineering ground
station at continues to perform power marage-
ment activities to sustain spacecraft operational capability.

ld. Om 38



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Control System was implemented throughout the project to govern secu-
rity procedures. Byeman Project replaced the Project Walnut
security clearance, ‘the satellites became designated as POPPY satel-
lites, and subsequent launches would receive NRO mission numbers in
the series. ‘The DNR reviewed the organization and responsibil-
ities within Program C as proposed by the DNI in the time fraite July
1962 through January 1963, ‘The following changes and ‘additions ta
organizational responsibilities were implemented: ‘

}. ‘the NRO provided funding to rt Program ¢ based on
annual program budget submissions by PRL beginning with fiscal year
1963. Consolidated Cryptologic Program (CCP) continued to rt
mission ground station personriel, magnetic tape, and data processing,

2. ‘The DNT became designated as Diréctor, Program C. ‘the ONT
provided a POPPY project director re ible for supervising and
administering all aspects of the project subject to the approval of
Director, Program C, . .

3, ‘the NRO Deputy Director for Operations prepared routine
tasking schedules for the operational control of POPPY satellites with
technical support from the NG, Routine tasking wes directed by the
NRO Satellite Operations Center (SOC) through NSG. NSA directed quick
reaction tasking cf POPPY satellites through NSG following tip-off of
Soviet space or missile activity:

4. Program A of the NRP provided the launch vehicle, launch
veliicle/satellite integration, and launch services.’ ‘The NRQ sepa-
rately fimded this support.

5, ‘he Naval Research Laboratory was designated the technical
director responsible for design, development, and operational, support.

C. LATER CHANGES

Program C and the POPPY project organization functioned in the
same general manner as established under the NRO for the next fourteen
years. Changes subsequent to 1963 were the result of realignments
within the Navy, changes in capabilities leading ta added .responsibil-
ities, and changes in participation. Significant changes and asso-
cidted factors were the follow.

1. Starting in April 1963, the requirement for detecting,
electrically reporting and logging new and unusual signals was d
to the reaponsibility of mission’ ground stations. ‘the resulting
on-line manual _analys duced the earliest possib qnition of

after it was couriered
8 site facilities were upgraded

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aN Se RODE corel inte ORE

PROJECT NAME:

NRL MISSION:

ORBIT:

GROUND STATIONS:

USEFUL LIFE:

INNOVATIONS :

FIRST LAUNCH

GRAB (Walnut security clearance)

Pre-NRO Launch: Thor-Able-Star from Cape Canaveral,
Florida on 22 June 1968

Elliptical with 338 by 565 nautical mile altitude,
66.7 degrees inclination, and period of 161.6
minutes.

This was the first operational overhead intelligence
satellite for the U.S.

Dyno 1 Transit 2A (APL)
20

98 days

First U.S. satellite with an ELINT mission and first
successfully launched U.S. intelligence satellite.

First U.S. pickaback launch.

Fixed tuned crystal video receiver with six monopole
antennas for anni-directional ELINT data reception.

ELINT receiver active for 46 minutes upon inter-
rogation from the ground.

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VIIZ. IMPACT OF PROBLEMS AND ANOMALIES

Most project problems and anomalies lead to technical innovations
and have been mentioned in preceding chapters, A brief summary of
other obstacles is provided in the following paragraphs in the launch

onology. -

A, FIRST LAUNCH. - GRAB/DYNO 1, 22 JUNE 196d

This mission was useful for ELINT collection for just ninety.
days. In addition to the short life, the need for President
authorization to interrogate the satellite was 4 constraint on the
amount of data that was collected. The actual impact of these two
factora was not overly important since statesidg analog analysia and
budding data processing capabilities were satutated by the amount of
data collected. No anomalies were observed in the intercepted data.
No problems wete encountered in the interrogation of the satellite or
in collection and forwarding of data tapes. Scientific cover experi-
ment SOLRAD 1 was operational for 1@ months and highly successful.

B. SECOND LAUNCH, 39 NOVEMBER 1960

The Thor rocket butned out 12 seconds early and was destroyed by
Range Safety, Fragments landed in Cuba. ‘he incident resulted in the
prohibition of launch trajectories ideal for the desired 7@-degree
inclination and forced a dogleg injection effort on subsequent
launches from Cape Canaveral, Florida. This failure resulted in a
nine-month lapse in GRAB collection,

Cc. THERD LAUNCH - DYNO 2, 29 JUNE 1961

This launch vehicle had three spacecraft stacked oné
the other, Failure of separation system between the topmost
caused Dyno 2 and State University of Iowa Dr, Van Allen's
satellites to remain attached in orbit. ‘Thus Dyno 2 was used on the
odd days and INJUN used on the even days during fo
Dyno 2 operational lifetime. The oo pt of

sate. a INJON precluded in ogation:
potentially lucrative passes over the 0.S.S.R.

D. FOURTH LAUNCH, 24 JANUARY 1962
The attempt wes made to orbit a third ELINT satellite with the
cover experiment SOLRAD 4A along with four other satellites. ‘The

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_ . erie tir Be

KEY MANAGEMENT POSITIONS /INCUMBENTS

Director, Naval Intelligence/Director, Project GRAB:

RADIM L. BH.
RADM V. L.

Frost UN... . + + +. » August 1959 to September 1968
Lowrance SN... . «20 '. September 1968 to July 1962

Director, Program C:

RADM V. L. Lowrance USN... . .°s. July 1962 to dune 1963
FADM R. L. Taylor ISN... .- - June 1963 to May 1966
CAPT M. H. Rindskopf USN «oe» May 1966 to July 1966
FADM E. B. Fluckey USN... duly 1966 to June 1968
CAPT F. Morphy USN... ... + dune 1968 to August 1968
RADM F. J. Harlfinger GSN... . . . August 1968 to July 1972
RAIM R. K, Geiger USN... ~~ . January 1971 to July 1975
CAPT R. T. UN... ee ee ee duly 1975 to duly 1977
RADM G. M. Yowell . 2... + + - « duly 1977 to Present

Director, Naval Security Group:

CAPT L. R.
FADM T. R.
<ArPr Lb. R.
FADM T. Re
RADM R. E.

Commander ,
RADIM R, EL

FADM C. G.
RADM G. P.

Shulz UN... ee ee June 1968 to July 1961
Kurtz USN. 6. ee ee duly 1961 to December 1961
Shulz UN... ee ee December 1961 to January 1962
Kurtz UN... ee ee January 1962 to August 1963
Cook UN 2. eee + August 1963 to.July 1968
Naval Security Group Command:

Cook USN... 2... +. duly 1968 to dune 1971
Phillips UN ..... . . dune 1971 to August 1974
March USN... .... .» » August 1974 to September 1978

Naval Research Laboratory GRAB/FOPPY Project Manager:

Mr. H. O. Lorenzen. . eee ees

« August 1959 to February 1973

Mc. RD. Mayo. 6. 6 ee ee + oe. February 1973 to Present

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VI, ANALOG ANALYSIS

Analog analysis of the GRAB and POPPY data was performed at
ic rt from NRL and STIC. A

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IX, PERFORMANCE VERSUS OBJECTIVES

Program objectives charged over th¢ years both in response to
new wy cntelligence re tequirementa and ag _a_conseq Of the project's

A. GRAB/DYNO 1

In response, to the requiremen collect ELINT from the
U.S.S.R., Dyno 1 was activated for 48-minute collection
periods over the U.S.S.R. ‘the chief resuit of this mission was the
successful demonstration of the collection technology in the satellite
and mission ground ‘stations. ELINE results included the following: .

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Use of stretched 2@-inch diameter sphere design on

First program launch without accompanying
unclassified SOLRAD scientific cover experiment.

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ANDER 175A BEEMAN ABALENE-RERHORD/COMENE-COUTROR- SS TIS Det


The first U.S. and reconnaissance satellite (photo or SIGINT) to
become operational was successfully launched on 2% June 196@ from Ca
Canaveral, Florida eboard a Thor-Able-Star. GRAB/bym 1, as 3
ELINT satellite was named, shared the launch vehicle with Transit a,
the Navy's second navigation satellite. . the purpose of the ELINT
package, designated Dyno 1, was ta collect ELINT data from the inte-
rior and infrequently covered maritime regions of the U.8.S.R, ELINT
data is transponded by the Dyno 1 for a forty-minute period after
interrogation. ‘he mission ground station equipment was operated only
when Dyno satellites were transmitting above their radia horizon;
recorded data from the down link(s) on magnetic tape; and forwarded

. data recordings with collection logs to NSA via the Anmted Forces
Courier Service (ARPCOS).

‘The ELINT capability of Dyno 1 was successfully tested on 4 Jul
1968 at Wahiawa, Hawaii, well out of Soviet range. Tenge politic
climate following the U-2 incident dictated that this satellite would
be tasked only by specific presidential authority. Thus only 22 data
collection passes across the SINO Soviet bloc were collected and pro-
cessed | dur ing the three month useful lifetime of the GRAB/Dyno 1
satellite. ‘

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eadoul
+ when

rroga’

ation
it was relocated to]

closure of
stablished et

Adak was the only one of the GRAS sta’ ontinue POPPY
operations until project termination, Adak ceased FOPPY
operations in August 1977.

During the initial operations collections were conducted in Earth

Satellite Vehicle (ESV) shelter huts. After the system stabilized in
the sixties, the transition was made to permanent buildings.

A. ESV HUTS

‘The ESV huts were procured from Craig Systems, Inc, of Lawrence,
Massachusetts, ‘These lightweight, aluminum shelters, designed for

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SEPP ar ne aan a naiahinteiateaenienetmeene

SIGNIFICANT EVENTS/TNNOVATIONS AND KEY CONTRIBUTORS

INTTIAL CONCEPT/SYSTEM PERFORMANCE REQUIREMENTS {NRL}

Mr. R. D. Mayo originated the concept of the Dyno ELINT satellite
in early 1958. Messrs. H. O. Lorenzen and J. H. Trexler expanded the

concept and coordinated with other or anizations to provided for
multi-agency participation, col-
lection, and forwarding of a or process: ‘product.
dissemination. RADM Reed of ONI advanced the NRL Proposal through the

Navy, ARPA, DOD elements, and the executive branch to secure presi-
dential approval.

SATELLITE DESIGN (NRL)

Mr. M. J. Votaw adapted the Vanguard design to accommodate Dyno
. and the Solar Radiation cover experiment. He also established the
interface between Dyno 1 and Transit 2A for the first dual-satellite
launch. Subsequently, Mr. E. L. Dix was the chief design engineer for
the satellites. Mr. P. G. Wilhelm became responsible for the satel-
lite technology from 1965 to present.

SATELLITE POWER SUBSYSTEM AND THERMAL DESIGN (NRL)

Mr. P. W. Raymond supervised the overall design of the power sub-
system with the solar cell array designed by Mr. J. Yuen and the power
subsystem conditioning package designed by Mr. J. G. Winkler. Mr. R.
S. Rovinski designed the thermal subsystem for all of the Dyno and
FOPPY satellites.

COMMAND AND TELEMETRY (NRL)

The command and telemetry subsystems for the first Dyno and the
early POPPY satellites were implemented by Messrs. Dix and Wilbelm.
Later refinements were made under the supervision of Mr. Wilhelm.
These included improved telemetry and data link transmitters by Mr. L.

. E, Bearton; command and telemetry subsystem expansions and refinements
by Mr. Winkler; on-board storage memory for engineering measurements
and timed command activation by Mr. R. E. Eisenhauer; and development
of the PCM telemetry subsystem by Mr. Eisenhauer and Mr. R. 0. Wilson.

The original interrogation and telemetry readout subsystems for
the ESV huts were designed and implemented by Mr. Dix. These

subsystems were later expanded and refined by Messrs. W. E, Withrow
and A. Q. Tool as the transition was made into permanent buildings.

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POPPY GROWTH

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FIELD DIGITIZATION .

Mr. F. V. Bellrich of NRL and Mr. L. M. Hammarstrom of HRB were
the architects of the system to digitize POPPY data in the field in
1967. Mr. M. J. Van de Walle of HRB developed the first linear phase
receiving system and the FS-1A solid-state receivers. Mr. M. Sheets
of NRL conceived of and specified the adaptive thresholding technique.
Mc. 7. W. Fisher and Mr. J. R. Lindley of NRL designed and implemented
fhe buffered memory digital recording system for the ADDS/digital tape

nter face.

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OTHER SOURCES
DIRNAVSECGRU (COMNAVSECGRU) control and advisory messages to mission
ground stations in BYECCM and SCCOMM communications channels
Mission Ground Station BYECOM and SOCOMM message traffic
NSA product reports
Mr. R. D. Mayo: video tape, notes, discussion
LU R. L. Kellogg USN: binders of source material, notes

NRL technical satff

LCDR R. L. Potts USN: original draft dated 15 June 1978 TS BYEMAN/TK/
COMINT Jointly

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RANDLE -BEEMAN, CENT haiti OER CONE - SES TEMS JOLT

PROJECT:
NRO MISSION:

LAUNCH:

ORBIT:
REMARKS:

SATELLITES:
DIAMETER INCHES:
WEIGHT POUNDS:
NUMBER RF BANDS:
RF COVERAGE MHZ:

INNOVATIONS :

FIFTH LAUNCH

GRAB (Walnut. security clearance)
Pre-NRO

Scout from Vandenberg AFB, California on
26 April 1962

Not achieved

Scout was launched with no attitude control gas in

the fourth stage.
Dyno

26

55

2

First project launch from Western Test Range.

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» FORAGE

1 -23-

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POPPY MGS Interrogation Position - 1972


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adn isla COINTO~SOANT le GS TENG JOLT

STXTH LAUNCH
PROJECT NAME: POPPY (Byenan
NRO MISSION: ||
LAUNCE: Thor-Agena D from Vandenberg AFB, California on
13 December 1962
ORBIT: Righly elliptical with 124 by 15@@ nautical mile
apogee, 78.3 degrees inclination, and period of
116.8 minutes. :
REMARKS: First burn in second stage continued until fuel was
depleted.

GROUND STATIONS:

SATELLITES:

_

28 28
WEIGHT FOUNDS: $5 55

NUMBER RF BANDS: ~
RF COVERAGE MHZ: .

END OF LIFE: -

USEFUL LIFE:

—

DIAMETER INCHES:

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FRONT MATTER PAGE
Cover Page. - ee te ee ee i

Foreword 2.00 ee ee ee ee ee ee ab

‘TEXT . .

I. CONCEPTION, poe et ee ee eee eee OD
II. ORGANIZATION 6 we ee ee ee 4
IIT, SATELLITES. Fe ee ee 6
Iv. MISSION GROUND STATIONS . 2-6. eee eee O17
‘ve GROUND READOUT EQUIPMENT « .- + +--+ eee 22
VI. ANALOG ANALYSIS. 2 2 eee ee ee ee ee ee 7
VII. DATA PROCESSING. ep eee te et ee eee 30
VIII. IMPACT OF PROBLEMS AND ANOMALIES ...+.+-- 39

1x. - PERFORMANCE VERSUS OBJECTIVES . - + «+ + we * + 44

1, MISSION CHARACTERISTICS 6. ee ee ee AD
2. COST DATA ge ee ee ee ABE
3. REY CONTRIBUTORS 6 ee ABT

4. GLOSSARY OF POPPY-RELATED TERMS... +++ - + + AG

5. BIBLIOGRAPEY 66 ep eet ABD

4

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N Fi
june

the microthruster was activated, HE caught up with, then went

ahead of before the microthruster could again ba used to
eliminate stall velocity difference and restore proper spacing.

There were a number of instances of cross-talk between receivers
on these satellites, resulting in inhibitions on certain tasking com
binationg. Many of the cross-talk situations eventually disappeared
as battery voltages fell.

cea
ie batteries until attainment of over

of useful life.

K. ELEVENTH LAUNCH - wcssron 30 SEPTEMBER 1969

On the fourth day after launch, the Agena D apparently exploded,
but no immediate adverse consequences to the satellites were observed.
The resulting orbit was nearly circular, and all satellites were pre-
dicted to be within a 248 nautical mile envelopa by late November.
All subsystems operated as desired. No constraints were imposed on

« Operational tasking comnenced on schedule in late

terrogation by

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Thor-Able-Star ane vehicle exploded during launch due to 4 crack in

at) the second stage eng The t of the loss of the satellite was
h a postponement of aspect intelligence collection activity.

E.  FIPIH LAUNCH, 26 APRIL 1962

! Another launch failure occurred in the program's first tempt
i pci Western Test Ramge et Vandenberg ee California. | ‘The ELINT

: package was the same type of configuration on priog attempt
i - and SOLRAD 4B provided a cover experiment. ‘the Scout rocket roee for
! . een ear two minutes and landed in the ocean within sight of the
i al

P. SIXTH LAUNCH - MISSION [MM 13 vecamser 1962

injected into a highly

ell orbit of 124 miles because the Agena D

wed to burn after its programed turn-off time. ‘This elliptical

Srbit made it difficult to detect and track the telemetry signal with
the fixed elevation antennas used at the collection sites, .

Near perigee, the field of view of was consider-
ably reduced to a radius as léw as 909 nautica] miles, about hele the
radius of thé field of view for the intended orbit. At 4 the
radius of the field of view was approximately 2709 nautical mi niles.

G. SEVEN sauce - missroy [15 sine 1963

The attempt to place the into a circular
orbit was not entirely succes: Agena D fated

te on ike second clreularizing born. The ft bit o:
: — = — _ _ —_

H. EIGHTH LAUNCH ~ uission 11 gasuary 1964

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EIGHTH LAUNCH

PROJECT NAME: POPPY (Byenan

NRO MISSION: | |

LAUNCE: TAT-Agena D from Vandenberg AFB, California on
11 January 1964
ORBIT: Nearly circular with 498 by 566 nautical mile

apogee, 69.9 degrees inclination, and period of
183.41 minutes.

REMARKS: (TAT) thrust augmented Thor. ‘Three solid rockets
strapped to booster.

GROUND STATIONS:

SATELLITES:

DIAMETER INCHES: 28

WEIGHT FOUNDS: 65 89 cy
NUMBER FF BANDS:

RF COVERAGE MZ:

END OF LIFE:

USEFUL LIFE:

Axis of MBB aligned to within [fl degrees of ver-
tical using 2-axis gravity gradient stabilization
with re _at end of 26~-foot boom with eres
tel-

genera’ r up or boom

down by use of omi-directional antennas.

INNOVATIONS:

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stretched sphere with a 9-inch eqatorial band. ‘the multiface
satellite measured 27-inch diameter across flatg at ity 12+s

equator. spacecraft equatorial bands varied in size ta acc late
the increase in size and number of electronic and mechanical compo-
nents necessary to satisfy the increasing mission requirements. The

basic ce structure wag utilized on all POPPY satellites after
Missia The weights of the multiface. satellites ranged from 162
to 282 pounds.

D. POWER

The first Dyno satellite was powered from a 12-volt storage bat~
tery consisting of nine D size cells in series, The bat was
charged by silicon solar cells and was designed to provide useful life
of one year in orbit, Six 9-inch diameter round patches of 156 cells
were symmetrically located on the surface of the re 86 that
approximately one watt of power would be available for any orientation
vata of charging power the chanical Feacage battery, From Dyno 2
watts of charg to c storage + From J
onward, +]2-volt okt =12-volt storage batteries were included.

In the 24-inch diameter satellites, more solar cells of smaller
size were placed on ll-inch diameter panels, ‘The six symmetrically
placed panels provided -about four watts of charging power to an 18~
cell, nickel-cadmium battery pack. (NOTE: 9+ Giameter solar
panels were used with the 2@-inch diameter satellite and ll-inch dia-
meters with the 24-inch satellite.) ° 3

E. TELEMETRY
The ‘satellites continuously telemetered engineering data on the

housekeeping condition of the satellite and state of command of
@ ELINT ection receivers and on

.. Satellite engineering data suc

S Pact age, peratures, etc. were sampled ye cote
mutator. Discrete ofc status indicators were binarily encoded
and menitored by commutator .

“the satellites were equipped with _—
telemetry subsystem in order to rove
: spe te ty of telemetry readout using a] display at

the mission ground stations.

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BAND -VE DAN EEE OLE COENE-CONEROE- GS EMCO



PROJECT NAME:
NRO MISSION:
LAUNCH:

ORBIT:

SATELLITES:

DIAMETER INCHES:
WEIGHT POUNDS:
NUMBER RF BANDS:

RF OOVERAGE MHZ:
INNOVATIONS :

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6 June 2012

SECOND LAUNCH

GRAB (Walnut security clearance)
Pre-NRO

Thor~Able-Star from Cape Canaveral, Florida on
38 November 1968

Not achieved

Booster vehicle malfunctioned and was destroyed.
Impacted in Cuba causing an international incident.
Resulted in restrictions on all future launches from
Cape Canaveral relative to acceptable launch
azimuths.

Dyno Transit 3A (APL)

29
49
1

None

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The first GRAB/Dyno satellites transmitted telemetry signals at
108 MBz, In later years, frequencies in the neighborhood of 137 MHg
were used to avoid interfering signals. . .

In the spheres and stretched spheres, the power output of both
the telemetry transmitter and the ELINT data transmitter(s) was fed
into a single ami-directional, 4-element turnstile array, ‘The same
antenna served for reception of thé command signals. ‘The mtifaces
used two such turnstile arrays, one for ¢ reception and telem-
etry transmission, the second for ELINT data transmissions.

was 2 superhete fyne O OL O

and second oscillators to provide stability. Audio

the proper tone activated the corr ing relay switches to turn oh
the data link transmitter and one of the two timers and to turn off
telemetry at the end of useful life, :

As command options increased to include more data receivers, data
links, experiments, station keeping devices, etc. the basic command
system was expanded from a simple tone system to a tone digital system
utilizing ten frequency tones allowing over a hundred comands.

G. — -ELINT COLLECTION

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FOREWORD

: This report describes the history of the POPPY project from its
concept in 1958 through its termination on 30 September 1977, this
history wag compiled at the request of the Director; National Recon-
naissance Office to the Director, Program C, Included in shig report
are the significant events during the nineteen years of, the POPPY pro
ject, including. the development and refinement of POPPY satellites,
migsion ground’ stations, ground readout equipment, snalog analysis,
and data processing, The impact of failures, probleme anomalies
are evaluated. Successes of the POPPY project. are measured against
program objectives, ‘Technical data, cost history, key contributions,
a glossary of terms related to the POPPY project, and a bibliography
ate contained in annexes to the report.

Each of the chapters in the report ig intended ta be somewhat
self-contained. Annex 1 containg a summary of mission characteristics
‘and merges same information from the third through the seventh chap-
ters in order to provide a chronological summary of the technological
innovations in. the order of the launches. ~

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ANNEX 2

COST DATA

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worldwide service conditions, could be transported by helicopter,
large aircraft, truck, tail, ot ship.. ‘They were deseribed as all~
weather shelters constructed of lightweight rigid floor, roof, side-
wall and end els secured by two Ligting-bard assemblies. The
panels were fire resistant and water proof, ‘The ESV huts came
equipped with two work benches, a spare parts cabinet, exhaust fans, a
filtered air inlet, incandescent lighting, @ power entrance and dis~
tribution cabinet, and an electri¢ heater.

At NRL the ESV huts were fitted out for operations prior to
deployment. NRL installed sheet-metal supporting racks to hold the
electronic equipment, the necessary electronic equipment, an antenna.
mast, antennas, an anterina steering mechanism and brake assembly, and
an air conditioner. The ESV huts were shipped as stand-alone assem-
.blieg requiring only minimal site support. At. the mission ground
stations, the ESV huts were placed on concrete pedestals, on pavement,
or on elevated platforms equipped with carport-type canopy roof, pro+
vided with electrical power and they were ready to conduct operations,
The ESV huts were only manned t6 prepare for and conduct scheduled
collection operations. By 1962, in preparation for the first dual~
satellite launch, each collection site was provided with two of the
fully equipped ESV huts.

B. PERMANENT BUILDINGS

As the expanded exploitation and ‘data collection roles placed
increasing burdens on the site pefsonnel, a@ move into permanent
buildings was started in the early sixties when buildings housing
GRD-6 direction finding systems became available at
Adak. ‘These wooden buildings were ite to replace
juts and provided the necessary space to install the growing
number of bays of electronic equipment. =

At other sites different buildings or parts of build
le available £ be poppy installation. By 1967, the

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LANL

HISTORY OF THE POPPY SATELLITE SYSTEM

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INI Project Agreement (Security), 13 page working paper, annotated
date of 1959

M. Votow (NRL) draft paper of January 1968: ‘The Solar Radiation
Satellite

a sx) Project Grab Processing Suggestions and Review of
intelligence Summary, dated 6 December 1968

Project GRAB Technical Operations Group letter G-52/00822-61/jmc of
18 January 1961: Status report on Project GRAB

NSA (COSA-5) Status Report of Analysis on Project GRAB I, dated
1 May 1961

DNI letter 922YB/mlk BYE-19613-63 of 21 January 1963: System
POPPY; reassigrment of responsibilities for

NSA summary of results from RF bands of vision fl undated

Department of the Navy document BYE-5198@/69 of 2 December 1966: Navy
Satellite Program C : .

NRL letter BYE+26910-67: Technical Description

NRL Program “C" Technical Description of Mission [J Bye-51912-69 of
1@ December 1969

COMNAVINTCOM memorandum Op-892/kfg BYE~66385/78 of 17 August 1978:
Navy Ocean Surveillance Requirement

Manager, Program C letter NIC-20/djb BYE~66428/70 of 13 October 1970:
Interim Failure Report on the Missioi Command System

USIB SC SORS memorandum BYE~1429-76/ 16./37/5 of 4 November
1976: Evaluation of POPPY - Mission i

USIB SC SORS memorandum BYE-1571-7; 10./155 of 2 December 1971:
Mission Guidance for POPPY Missio:

Director, Program C memorandum PM-16:RKG BYE~52238/71 of 6 May 1971:
POPPY Growth; capabilities vs funding

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Collection operators noted in their logg occurrences of NSA

specified signals of high interest as well ag new, unique or uniden-
tified signals. After 4 pass, analog anal played back tapes

back the
at their analysis and quality-contro tions and performed aural
and visual scans of each of the recorded data links. Parameters of
these signals of interest and unidentified signals were measured and
tabulated. After verification of the parameters of unidentified
signals, leading analysts prepared a daily signal of interest tipoff
report for transmission to NSA and to other POPPY sites,

In the early seventies, pulse width selectors were added to the

analog analysis positions to isolate and display the data collected .

from 2 single RF band in the satellite(s).

As the reliability in detecting and reporting signals of interest
at the mission ground stations became established, the requirement for
forwarding all analog tapes to NSA diminished to a requirement to for-
ward only those tapes containing unidentified signals or tapes specif-

ically requested by NSA. Recordings not forwarded were retained for.a_

specified period, then degaussed and recycled.

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TERM EXPLANATION

Athos - German-developed crystal video receiveer of WWII. Prob-
ably named after Mount Athos in northeastern Greece, home
of ‘eel ibate monks inhabiting 28 monastaries. One
thousandth anniversary of founding of first monstary,
Great Lavra, in 1963. Book on Athos monastaries pub-
Lished in Germany in 1943 (Moenchsland Athos by F.
Doelger). .

GRAB - Galactic Radiation and Background. Covername for Project
Dyno ELINT satellites.
- Galactic Radiation Energy Balance.
— NRO SOC title for Mission [ser ies Reports Control
Manual.
Reptile ~ Unclassified name used at NSA for POPPY project. .

SISS ZULU - Unclassified name used within the Naval Security Group to
refer to the POPPY project.

SOLRAD -. - Solar Radiation measurement packages carried along with
ELINT payloads. This legitimate scientific payload
formed excellent "cover story" for the Dyno ELINT
payloads through the pre NRO period.

Transit 2A - Second Navy navigation satellite, shared launch vehicle
with Dyno 1 on 22 June 1968. First successful dual-
satellite launch.

Transit 4A - Navy navigation satellite was the primary payload on the
launch vehicle with Dyno 2 on 29 June 1961.

Walnut

- Name of security project for safeguarding details of the
Dyno ELINT satellites. CANIS security oath.

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uninterrupted telemetry and data collection as the satellites passed
at high elevation angles. ‘These antennas were fed by 5d-watt output
cammand transmitters.

‘the interrogation position expanded into five bays of equipment
manhed by one operator. By 1967, the position included programed
command tone generators which read pre-punched: cardg prepared to
implement the specific collection task groups authorized by the NRO
Satellite Ogerationg Center (SOC). ‘The position also included an
R-39BA/URR receiver connected td 4 25-foot whip antenna for the recep-
tion of the local standard time broadcast used tg set the digital time
genetator. Solid state receivers replaced tha R-39GA/URR receivers
used to copy telemetry.

All satellite interrogation except for Etint data collection
operations, (such as thrusting and power/attitude management, etc.)
was Pers ground station in Bybla Valley,
Virg .

Cc. ELIN? COLLECTION

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ANNEX 5

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IIT, SATELLITES

All of the GRAB/Dyno ELINT satellites contained scientific cover
experiments of the SOLRAD type. Engineériny evolution and innovative
refinement of the spacecraft and ground station subsystems were con-
tinued by NRL in the POPPY program following the transition from GRAB/
Dyno ta POPPY, ‘The satellites were designed for long-life high-duty
cycle operation, All satellites were designed for full utilization
any time a satellite was in view of a ground station, Eight satel-
lites provided useful intelligence for periods in excess of

This combination prov: ne low-cost satellite
system which continuously had Operating satellites
on-orbit from 1963 until 1977 when the program was terminated.

A. CLUSTER SIZE

The GRAB/Dyno satellites were launched pickaback with other
scientifi¢ and navigation satellites. ‘Two of the five attempts to
ai’ mo satellites were successful. The first POPPY launch Mission

orbited ir of ELINT satellites, ‘the next two la
ForPy| ch of final four 3_ carr ae
satellites

B. ORBITAL CHARACTERISTICS

C. PHYSICAL CHARACTERISTICS

‘The GRAB/Dym satellites were of spherical configuration with a .
diameter of 24 inched. ‘the first hyn spacecraft weighed 42 pounds)
later Dyno spacecraft. weighed up to 55 pounds.

In the first POPPY launch, both of the satellites were composed
of two 28-inch diameter hem: @§ joined by a 4-inch wide equatorial
band. ‘The stretched sphere design was used for all satellites in the
next three launches, either with 2@-inch or 24-inch diameter
configurations. ‘These satellites weighed between 55 and 134 pounds.

. The multiface design was first used ort Mission in 1967,
three of the four satellites being multiface. The fourth was 4

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FOURTH LAUNCH

PROJECT NAME: GRAB (Walnut security clearance)

NRO MISSION: Pre-NRO

LAUNCE: Thor-Able-Star from Cape Canaveral, Florida on
24 January 1962

ORBIT: Not achieved

REMARKS: No guidance on Able-Star stage

SATELLITES: Dyno + 4

DIAMETER INCHES: 26
WEIGHT POUNDS: 55

NUMBER RF BANDS: 2

sr covence ven:

INNOVATIONS : Attempt to place five satellites into orbit using a
single launch vehicle.

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Sry erreeere—rererretrpweinaimeetiettetereriniatin—ratatn

FUNDING AUTHORIZED IN SMILLIONS

FISCAL ARPA/ 1 2

aR. MISSIONS NAVY RE oor TOTAL
1958 NONE 6.2

1959 NONE 8.225

1968 Dyno 1 8.79

1961 DYNO 2 AND ABORT = =—s-3..825

1962 WO PAILURES 5

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FOP-SECREF

Typical 24" Diametey Spherical Satellite
with 9" high Equatorial Band

-l1+

BYE-SA105,

Be RE AARNE Kiannaté tatoctes