Project HEXAGON Overview

NRO APPROVED FOR RELEASE 17 September 2011

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T H E C A P IT IT O Conditions for this photograph are: Mission 1212-3, op 723, frame 002 forward, 002 aft, -24° scan, 15 October 1976, stereo, 20X magnification of the Capital, Washington, D. C. The ability of the HEXAGON camera to photograph targets in stereo greatly increase its capability as

an intelligence gathering tool. All subjects reveal more information in three dimensions because they assume all the spatial dimension we are used to seeing. This allows determination of structure height, seeing the real shape of unusual objects and separation of items from confusing background.

The item at (A) is the press box for the last presidential inauguration. It was still under construction. The relief of the trees at (B) shows how cover for troops and vehicles can be interpreted and targets

located. During the time between exposures, vehicles (C) moved to new locations. The scale of the photograph and time interval are known so their speed can be calculated. Stereo imagery generally increases the information content of a target area and provides for a more complete and accurate intelligence reporting.




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r-1

PAN ORA

C SYSTEM SYST EM LEXIBILI LEXI BILITY TY

FRAMES

110 NM

CAPABILITY SCAN SECTORS

30, 60, 90, 120

DEGREES AT FULL SCAN CENTER OF SCAN

0, *15, ±30, ±45 DEGREES

CO CONTIGUOUS NT IGUO US AREA ACQUISITIONS

BIF003W/2-093942-77

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CONTI

OUS

DE AREA COVERAGE r START OF FRAME

START OF OPERATION

r — C A M E R A I D E N T I F I C A T IO IO N ( "A "A " O N L Y )

F IL IL M T R A V E DIRECTION

FRAME 1 FORMAT

31.4" = 30° SCAN (MIN)

RAME 2 FORMAT

2.5"

6.6"

VANDENBERG AFB IMAGE

5°SCAN 5°SCAN AN GLE MARKS

APPROXIMA TELY PARALLEL TO SV GROUND TRACK

F IL IL M S E G M E N T ( FU L L S C A L E

S V T IM IM E W O R D ONCE PER FRAM E)

TIMING DOTS EVER Y 2 MILLI SECONDS



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D E A ST C O V E R A G

A typical area search acquisition by HEXAGON is the coverage of the Eastern

Mediterranean. This is a single two-minute stereo operation. At 90 nm altitude and a cross track scan of ±45 degrees, the primary areas of interest in Western Syria, Lebanon, Israel, Western Jordan, part of the Sinai Peninsula, and part of Cyprus are acquired as a contiguous area. At ±60 degrees scan, the additional width permits a greater tolerance in the longitudinal position of the flight path in

addition to a wider area searched. In an extreme crisis, through the control of the orbit, a daily r eport of the acquisition of these areas is achievable.


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D E A S T C O V ER A G

±45° SCA N A T 90 NM

34 DAMASCUS

MEDITERRANEAN SEA

GOLAN AREA

32

AMMAN

ERUSALEM

^PCNtT SAID ALEXANDRIA

30° N

CAIRO

-4

30°

32

34

36


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B R O A D A R E A A C Q U IS I S IT IT I amisswatigsaazirmsterfaxasonsa.

The HEXAGON system can provide broad area acquisition with a contiguous area

acquisition of considerable magnitude along the line of flight using any of the selectable scan sector and scan center combinations. combinations. The maximum 120 degree swath

width is illustrated for a

area,

32

20

minute contiguous operation acquiring a 4800 nm long

nm wide, extending from Western Russia, through the Eastern Mediterranean,

down into Southern Africa. The total area approximates 1.54 M sq nm with an average

altitude of 88 nm.

NRO APPROVED FOR RELEASE 17 September 2011 -1

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BROA D A REA A CQ SITI SI TION ON

± 60° SCAN SECTOR

20 MINUTE CONTIGUOUS ACQUISITION ALONG LINE OF FLIGHT SHOWN

THE AREA COVER ON THIS PASS IS

APPROX 1.54 M SQ NM AT 88 NM




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S E AR C H G

BAL COVERAG

This is a r epresentative coverage of the Europe, Asia, and surrounding countries The enclosed block or cell areas taken but not cloud-free are also shown. High priority targets were t aken several times to ensure a cloud-free take and to note ground activity changes throughout the four-month life of Mission 1209.

These geographic areas of interest total 10.9 million square nautical miles and consist of: USSR 6.87, Easter n Europe 0.4, China 2.82, other Communist countries 0.56, and Middle East 0.25. The free-world area, including the United States, comprises a total of 41.3 million square nautical miles.

-4


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S EA EA R C H

LOBAL COVERAG

EURASIA COMPOSITE INTELLIGENCE SUMMARY

MSN 1209 30 OCT 74 - 7 MAR 75 LEGEND

NM CLEAR STEREO COVERAGE CLEAR MONO COVERAGE

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61


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C O V E R A G E H IS IS T O R

The initial contract for HEXAGON was to fly each vehicle for thirty days every

days

for a 50% search covera ge. The highly successful on-orbit performance, higher altitude, and design improvements of HEXAGON has allowed longer mission durations. This has resulted in extending search and surveillance operations up to

17

days.

The gap in continuity continuity (RV #4 recovery to next vehicle vehicle launch) of HEXA GO N coverage has varied widely. These gaps for the 13 flights to date have ranged from a low of 39 days to a high of more than 200 days. Under the accomplished schedule of the 13 launches, operational coverage with the acquisition and subsequent return of imagery data was available approximately half the time.


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C O V E R A G E H IS IS T O R LAUNCH MOON DAY 1201

GAP-DAYS

20

1203

20

8

39

—k--

1206

1207

1208

1 48

62 1973

1210 4,

1976 1213'

1977

02


-0

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N C R E A S IN I N G D U R A T IO IO N B E T W E E N R E C O V E R I E S

Since the first launch on 15 June 1971 the increasing mission life (from 32 to 176 days) has

resulted in an increasing number of operating days between recoveries. Starting with a low of 5 days, it has increased to intervals of 36, 34, 60, and 46 days on the thirteenth flight. On each of 11 flights, the shortest operating days per RV prece ded the recovery of RV -1. On each of eight flights the longest time period preceded RV-4 recovery. Future increases in mission life to utilize utilize the potential of the SV will produce on the a verage as many as 6 0 days of operations preceding the recovery of each RV.

nder crisis condition it it ispossible ispossible to make a non-full RV recovery after the the critical critical tar-

get is photographed; however, this option has not been selected to date. Solo operations have been used to exploit the SV capab ilities ilities without risk to RV recovery.

Solo tests have been instrumental in successfully increasing mission durations.


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NCREASING NCREASI NG DU RATION RATI ON B ETW EEN RECOVERIES RECOVERI ES DAYS

MISSION 1201

1202 1203 1204 1205 1206

SOLO

1207 1208 1209 1210 1211

1212 1213

RV-1 A TIME RV-1 36 D A Y S BIF003W/2-093942-77

RV-2 A TIME RV-2 34 DAYS

A TIME RV-3 0 DAYS MAXIMUM TO DATE

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-4 A TIME RV-4 46 DAYS


SECRET/H SO-255 COLOR FILM

Conditions for this photo are: Mission 1208-4, OP 733, Frame 006, Aft, Scan Angle -2°, 15 July 1974, 40X magnification of San Francisco, California. Color photography contributes an additional dimension to search and surveillance photography. It removes the image from the abstraction of black-and-white and places it in a context we understand more readily.

We see the world as a collection of shapes with size, texture, and color. A photograph lacking color is lacking one element in relation to reality.

This scene is photographed in natural color and many items are readily identifiable because of color cues. The school buses at (A) could be interpreted as such in black-and-white by their proximity to the school complex. However, the distinctive yellow hue that we associate with school buses signals their use immediately.

The blue color traditionally found in swimming pools is easily located in several residential areas (B). Black and white coverage would require a detailed search because their geometric shapes would be lost among the buildings. The competition competition pool at (C) shows varying depth by the transition from lighter to darker blue as the

water deepens. This same signature is seen at (D) indicating an expensive, in-ground pool. Numerous other items will be apparent to the viewer because of its association with object color in everyday experience.

Military, industrial, and transportation items also have distinctive color coding signatures and are separated from the enormous amount of photo detail in the same manner as the items cited above.



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S O 1 30 3 0 I F R A R E D C O L O R F IL IL M Conditions for this photo are: Mission 1213-3, OP 713, Frame 006, aft, scan angle 0°, Oct 14, 1976,

5X magnification near Santa Fe, New Mexico. Infrared color films were originally designed as a camouflage detection film. They have the capability of separating man-made, hidden objects from natural vegetation because of special characteristics of infrared radiation. Resolution is quite low compared to the black-and-white films used as the primary payload. Vegetation containing living chlorophyl reflects a large percentage of the infra-red component of natural

sunlight. Plants under stress (having insufficient water, diseased, etc.) will have a breakdown in their chlorophyl structure and consequently reflect less infrared. This type of color film shows infrared reflectance as a magenta colored image. Healthy vegetation will appear as bright magenta and will change in

either color or brightness as the plants degrade. As a result of this characteristic, SO-130 is an ideal film for monitoring monitoring crop vigor and potential yield giving very basic intelligence data on the food supply and import/export requirements of a country. In the accompanying photo varying degrees of vegetation vigor and distribution are indicated. The plant-

ings at (A) are well advanced and show local irregularities in water supply and/or soil capability. Pasture land is seen as healthy at ( B) and fallow fields are obvious at (C) . The natural ground cover for the area is indicated as arid area, low chlorophyl cover by the response indicated by (D).

There are also notable color differences in the ponds that cross the format diagonally. diagonally. As suspended sediments increase in volume, the color shifts toward the light blue and into the green portion of the

spectrum. This is an indicator of the e rosion and retention of valuable soils. Though marginally useful as a comouflage detection film at this scale, SO-130 is outstanding as a crop monitoring tool.



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F IL IL M T Y P E S F L ISZENUNIIMOF

CONVENTIONAL BLACK AND WHITE FILMS ARE:

1414 — The standard fine grain high resolution B & W film flown on HEXAGON Missions through Mission 1213. This film has an extended red sensitivity, is approximately 2 mils thick (0.5 mil emulsion coated on a 1.5 mil base), and has an Aerial Film Speed (AFS) of 15.0.

SO-208 — This film is identical to 1414 except that it is coate d on an ultra-thin 1.2 mil base. This w ill allow approximately 20,000 additional feet of film to be utilized in the HEXAG ON system and is the standard material for missions 1214 and up.

HIGHER RESOLUTION BLACK AND WHITE FILMS ARE:

SO-124 — A panchromatic B & W film flown experimentally on Mission 1210. This film has higher low-contrast resolution than the co nventional B & W films. It is coated on a 1.5 mil base and has an AFS o f 6.0 requiring longer exposure times than the conventional B & W films.

SO-460 — This film is essentially identical to SO-124 except that it is coated on the ultra-thin 1.2 mil base. The AFS is 6.0. SO-464 — This film is essentially essentially SO-460 with the yellow AH dye removed. This results in an increase of emulsion speed to an A FS of 10.0. This emulsion is also coated on the ultra-thin 1.2 mil base.

Aerial 15 — This is one of the new "Mono D ispersed Cubic" emulsions sometimes also referred to as "J" coatings. These emulsions exhibit extremely fine grain, high resolution, and very slow emulsion speeds. This film has an AFS of 6.6 and is coated on the ultra-thin 1.2 mil base.

COLOR FILMS ARE:

SO-255 — This is a conventionally sensitized, fine grain, high-definition color reversal film. The emulsion is coated on a 1.5 mil base with the film having an AFS of 9.5. SO-130 — This is a "False Color" infrared sensitive color reversal film on a 1.5 mil base with an AFS of 7.5. This film is used extensively for economic intelligence evaluation.


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FI M TYPES FL F IL IL M T Y P E S

SO-255

MISSION

SO-130

SO-208

SO-124

SO-460 I SO -464

AER AL 15

Film Footage - Feet 1201

1202 1203

172,640 156,115 185,325

1204 1205 1206 1207

1208 1209 1210 1211

1212 1213

TOTALS

216,010 191,017 207,832 210,069 217,338 210,156 153,942 231,450 198,536

2,558,884

2,000 21,000 4,984 2,588

3,000

9,150

3,150

3,750 4,500

4,500_ 3,500

4,500 2,000


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M A P P IN G S Y S T E M


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A P P IN I N G C A M E R A O P E R A T IO IO N

The mapping came ra system (MCS ) is utilized to provide cartographic control for compilation of

1:50, 000 scale maps. Photogrametric data is achieved b y simultaneously acquiring overlapping

terrain and star field photographs through three precisely calibrated lens systems. Control points are established by measurements of prominent imagery on overlapping pairs of terrain photography. Measurements of star image locations on stellar frames provide an accurate orientation of the terrain camera axis in space at the time of each photograph. Stereo photography,

necessary for vertical measurements of terrain imagery, is acquired in two stereo modes providing 70% or 55% overlap. A third mode is used to provide mono photography with 10% overlap. The high resolution and wide coverage

(70 X 140

nm) of the terrain camera provide a useful tool

in searching for primary targets of interest and earth survey objectives. On completion of the MCS mission, the terrain and stellar films films are returned in a single Mark V reco very vehicle. The doppler beacon system and NA VPAC system provides ephemeral information information which accurately

establishes establishes camera/vehicle position position in space. These data are needed to support mensuration of MCS imagery.


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A P P IN I N G C A M E R A O P E R A T IO IO N S

TERRAIN MAPPING CAMERA B I LA LA P P H O T O G R A P H Y

55% OVERLAP

TERRAIN MAPPING CAMERA TRILAP PHO PH OTO TO G RAPHY

10BTECTIVES

MAPPING AND GEODETIC SURVEY PAYLOAD DATA MAPPING CAMERA 2,000 FEET - 70 MM FILM (STELLAR) F O R M A T - 1 34 34 X 6 7 N M A T 8 8 N M C O V E R A G E - 5 .4 .4 M S Q N M / M I S S IO IO N O NE RECO VERY VEHICL FO R T ERRAIN AND ST ELLAR CAMERA FILMS ORBITAL DATA

70% O VERLAP

A T 8 8 N M . A L T IT IT U D E

I N C L IN IN A T I O N - 9 6 . 4 D E G R E E S S U N - S Y N C H R O N O U S AVERAGE PER IGEE - 88 NM A V E R A G E A P O G E E - 1 55 55 N M MAPP ING MISSION DURATION - UP TO 120 DAYS


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A P P IN IN G C A M E R A S Y S T E The Mapping Camera System (MCS) structure supports and positions the individual subsystems

with respect to each other and within the space constraints of the SV shroud. The loads are transmitted to six structural attach points on the vehicle bulkhead. Pitch and yaw alignment of the structure to the SV attitude reference module is achieved by shimming the attach points.

Temperature control is achieved by passive means (paint, tape, multilayer blankets and thin

metal sheets, i. e. , cocoons) for all but the precise temperature requirements of the lens system, which employs heaters for their accurate control.

Electrical interfaces between the SV and the MCS are at the bulkhead. All command, telemetry,

timing and power are provided by the SV.


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A P P IN IN G C A M E R A S S T E M

RECOVERY VEHICLE

MULTILAYER BLANKETS

T E L L AR AR C A M E R L IG IG H T B A F F L E

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APP

G C A M E R A D E SC S C R IP IP T I MARK V SATELLITE RECOVERY VEHICLE

FRAME ADVANCE

2.76-IN (70MM) FILM WIDTH

TELLAR AND TERRAIN TAKEUP ASSEMBLY

MA IN INSTRUMENT ASSEMBLY

FIDUCIAL LOCATION

STELLAR SUP P LY ASSEMBLY

10

-C

DATA BLOCK

10.75

LENGTH TITLE

4.330-IN

(110 MM) IMAGE LENGTH

TITLE AREA

o L2

START OF OPERATION MARK

TITLE MARKS

.y TITLE MARKS

FRAME

9.00IN. F O 0R M M ) USEFUL O R M A T

(4 PLACES)

PR RESSU ESSURE RE MAKEUP FSYSTEM

10

- 9.44S-IN. FILM WIDTH (REF)

- START OF OPERATION MARK

TERRAIN SUPPLY ASSEMBLY

STELLAR FILM CHUTE

STELLAR BAFFLE

4.33-IN. (110 MM) DIAMETER MINIMUM USEFUL FORMAT (REF)

RESEAU SERIAL NO, ORIGIN OF RESEAU ROW AND COLUMN NUMBERS (TYP)

STELLAR LENSES

DIRECTION OF FLIGHT AND FILM ADVANCE

TERRAIN LENS

DIRECTION

DATA BLOCK LOCATION (APPLIESTO FRAME SHOW N) RESEAU SERIAL NUMBERS

THERMAL SHUTTER ASSEMBLY

S T E LL LL A R F O R M A T

MAIN INSTRUMENT SYSTEM ELECTRONICS ASSEMBLY

E L E C T R I C A LD I S T R I B U T I O N ND POWER

ORIGIN OF RESEAU ROW AND COLUMN NUMBERS

ERRAIN FORMAT


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A P P IN I N G C A E R A LE LE N S E L E N S F O C A L L EN EN G T

RELATIVE APERTURE SENSITIVITY BORESIGHT STABILITY FIELD OF VIEW

10.0 INCHE

1/2.0 ST A R S O R B R I G H T E R th M A G N I T U D E ST 2 ARC-SEC IN OPERAT ION 16 BY 25 DEGREES

STELLAR SHUTTER SAFETY SHUTTER

I N H I B IT IT S E N S O

STELLAR LENS AND BAFFLE

RESEAU PLATE

F I L T E R (W (W R A T T E N 2 1 ) ASPHERIC SURFACE

FOCAL LENGTH REL. APERTURE DISTORTION

15.13-IN.

DIAMETER

STABILITY RESOLUTION F I E LD LD O F V I E W

12.0 IN.

1/6, 1/14

MICRONS M AX RADIA 2 0 M IC IC R O N S M A X T A N G E N T I A 2 MICRONS IN OPERATION 9 5 L /M /M M A W A R ( V E M O N 3 4 1 4 F I LM LM ) 38 BY 72 DEGREES

EARTH


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A P P IN IN G P R C E S S MAPPING

ORBIT DETERMINATION

PROCESS_

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I ?°11) 1, STEREO PHOTOGRAPHIC PLOTTING

ACQUISITION

EXPLOITATION DATA

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GRID AND CONTROL

RELIEF

AP DETAIL

NAMES

PUBLICATION

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APPI G CA ERA DATA NAVSATS TIME WOR READOUT

ORIENTATION DETERMINATION

NAVPAC FILM RECOVERY

COMPILATION

-0-

F IL IL M A N D L E N S DISTORTION CORRECTION

DOPPLER

PALLET

BEACON

DOWNLINK

CONTROL POINT MENSURATION MAP AREA PRIORITY

TRANET

ASGLS STC-RTS

EPHEMERIS PREDICTION

CAMERA PARAMETERS

WEATHER PREDICTION

COMMAND LOAD GENERATION

TM DATA ANALYSIS

OPERATING MODE

NAVPAC AND DOPPLER BEACON DATA ANALYSIS

EPHEMERIS


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6 W I LL L L IA IA M S A F B (20 X) ® EK 3400 FILM ( M I S S IO IO N S 1 2 0 5 - 1 2 0 8 )


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P R O D U C T IMPROVEMENT

•

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o EK 3414 FILM ( M IS IS S IO IO N S 1 2 0 9 A N D U P


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A R E A A C C E S SE SE D P E R

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A C T U A L T E R R A IN IN C O V E R A G

MISSION (NUMBER)

M I S S IO IO N L E N G T H (DAYS)

TOTAL AREA ACCESSED THOUSAND SQ NM

1205

40

1206

EQUIVALENT AREA ACCESSED SQ NM

CONUS ( 2 .2 .2 6 M

S. AMERICA ( 5 .2 .2 0 M

AFRICA ( 8 .9 .9 5 M

5894

2.6 X

1.1 X

0.6 X

6282

2.8 X

1.2 X

0.7 X

1207

58

6671

3.0 X

1.3 X

0.7 X

1208

60

6487

2.9 X

1.3 X

0.7 X

1209

59

3.0 X

1.3 X

0.8 X

6668

3.0 X

1.3X

0.7X

6919

3.1 X

1.3 X

0.8 X

1212

7363

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1.4X

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8099

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E T R IC IC P A N C A M E R S Y S T E M - A T T IT IT U D E D E T E R N A T

The metric pan camera attitude determination provides accurate coordinates of selected geographic points

to be used as control points for compiling maps. It derives image space angles from measured space coordinates and requires auxiliary data to establish absolute coordinates coordinates and base distances; e. g. , accurate ephemeris data and time of exposure, the angular orientation of the stellar relative to the pan terrain camera (interlock), the stellar angular orientation and camera angular motion history are the required

data. Stellar orientation data is acquired by a solid state electronic camera system accurate enough to determine pan camera line-of-sight pointing to within 5 arc seconds (1 a-). Two stellar cameras will be mounted on the TCA frame, one on each side of the SV, with line-of-sight elevation of 10 degrees up from horizontal

and 55 degrees aft in azimuth. Data of star image detections will be processed and stored in existing onboard recorder. This data will be read out to supporting tracking stations and will be processed off-line. Film markings will be provided correlating stellar camera star image detections and pan photography time. SV rigid body motion history during photography is obtained from the current ARM rate gyros through the

existing telemetry system. Vibration and thermal distortion motions are accounted for in on-ground data processing. Implementation is scheduled for previously described.

SV-17

and up superseding superseding the M apping Camera System System (M CS)

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E T R IC IC P A N C A M E R A S Y S T E M 5.8°FIELD OF VIEW

10°ELEV

_--------

55°

-------

5.8°FIELD OF VIEW 7

10°10°ELEV

A T T I T U DE D E D E T E R M I N A T IO IO N

PAN CAM A

PAN CAM B OPTICAL AXIS

OPTICAL AXIS

NADIR

LARGE LOOPER

SV SKIN

SHUTTER DRIVE

CATADIOPTRIC LENS

OPTICAL HOUSING

FOCAL PLANE ELECTRONICS CONTROL - READOUT

MOUNTED ON PAN

CAMERA'S FRAME

OPTICAL BAR

A-SIDE S V I E W P O R T HATCH LARGE LOOPER ELECTRONICS

IGHT SHIELD AND HEATERS SOLID STATE FOCAL PLANE

OOLER AND HEAT SINK

SV TIMING

GYRO DATA

DATA PROCESSING ELECTRONICS

TELEMETRY SYSTEM

EXISTING

TELEMETRY TRANSMITTER

EXISTING

EXISTING ....-. O N - B O A R D

A-SIDE S D A T A P R O C E S S I N G ELECTRONICS ..

FWD r22

STELLAR SOL ID STATE (S

ASSEMBLY

PITCH LINK UNCAGING MECHANISM

CAMERA ASSEMBL

TO OFF - LINE PROCESSING

SATELLITE

TRACKING STATION

STELLAR CAMERA DATA FLOW

RECORDER


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E T R IC IC P A N C A M E R A SYSTEM- LOCATI N DETERM NATI

The primary tracking system for the reconstruction of an accurate ephemeris has been the Doppler Beacon System (DBS) using a worldwide network of geoceivers. This subsystem is a dual oscillator of ultra high stability which provides a method for the accurate tracking of the Satellite Vehicle by the supporting station network. The electronics and the antenna are currently mounted on the mapping camera system. The plan is to install the antenna on the forward bulkhead starting w ith SV-17, which will be configured without a mapping camera system.

The DBS will be redundant to the Navigational Package (NAVPAC), which will be the primary means by which a precision ephemeris can be reconstructed for mapping. NAVPAC consists of two sensing

systems plus associated control and data processing hardware. The antenna/receiver system can

acquire up to three Navy Navigation Satellites (NAVSATS) simultaneously and track the doppler and refraction frequencies. The miniature electrostatic accelerometer (MESA) provides data on all nongravitational accelerations sensed. The delta processing unit collects, sorts, and time annotates all

the data, recording NAVPAC times at which NAVSAT time marks are received, thus calibrating the NAVPAC clock. Timing accuracy is expected to be 1.2 microseconds. NAVPAC is mounted on the -Y pallet with the antenna erected vertically above.


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E T R IC IC P A N C A M E R A S Y S T E M NAVSATS

LOCATION DETERM NATION DBS ACCURACY

DOPPLER BEACON

±200 F T I N - T R A C K

± 1 75 75 F T C R O S S - T R A C K ±100 FT RADIAL O R B I T A L V E L O C I T Y ± 0 . 1 2 F T /S /S E C

PALLET

NAVPAC ACCURACY 30 FT ALL 3 AXIS

TRANETS

ASGLS

SGLS








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S A T E L L IT IT E B A S I C A S S E B L Y


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S H R O U D C O N F IG IG U R A T IO IO N The shroud provides a protective enclosure for the payload on the launch pad and during ascent. It is a corrugated monocoque monocoque aluminum cylinder 52 ft long and 10 ft in diameter. Through air conditioning umbilicals and ducting the tempera-

ture and humidity are maintained at the desired values while on the launch

pad. Twenty-four removable doors provide access for servicing reentry vehicle igniters,

sub-satellite trickle charge and arming, alignment checks of attitude reference to two-camera assembly reference axes, shroud thruster spring cocking, and shroud final pyro arming.

The shroud separates from the Satellite Vehicle after the pyrotechnic agent, Mild Detonating Fuse (MDF), breaks the magnesium longitudinal and beryllium circum-

ferential breakstrips. Springs initiate the shell separation and then the acceleration from the booster Stage II cause the halves to fall away from the SV. No single failure in the pyrotechnic or electrical system will prevent shroud separation.


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SHR UD CON

GURATI ALUMINUM SKINS, SKINS, RINGS AND CORRUGATIONS AFT - M A G N E S I U M S K IN IN S AND RINGS FWD STAINLESS STEEL DOM

SHROUD IN JIG .848

SEPARATION JOINT

LONGITUDINAL SEPARATION LINES

TYPICAL STRUCTURAL DETAIL

ff BERYLLIUM BREAKSTRIP

AG BREAKSTRIP

-Z

LONGITUDINAL SEPARATION JOINT HINGE DETA IL AND CIRCUMFERENTIAL S E P A R A T I O N JO JO I N T BIF003V02-093942-77

fy

+z

HINGE LINES (2 PLACES)

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PRING THR USTER DETAI 05





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S A T E L L T E B A S IC A S S E M B L Y S T R U C T U R B O O S T E R A D A P T E R S E C T IO IO N OAM RCM SECTION E Q U I P M E N T S E C T IO IO N

SECTION

MID SECTION

APSA

F O R W A R D S E C T IO IO N

BIFO03VV/2-093942-77

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10


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S A T E L L IT I T E B A S IC I C A S S E M B L Y -A -A F T S E C T I O N The Aft Section consists of an equipment module, a booster adapter section, and an Orbit Adjust Module/ Reaction Control Module (OAM/RCM). It is 10 ft in diameter and 5 ft long. This section is a semimonocoque structure with a corrugated aluminum external skin. It weighs approximately 3500 pounds, including all equipment, less expendables. The Aft Section provides environmental protection and thermal control during

ground, ascent, and orbital operations. The structure is capable of withstanding the dynamic and static conditions imposed during all phases of ground handling, launch, ascent, and orbit. The Aft Section interfaces with the booster, Mid Section, ground AGE, main electrical umbilical, pressurization and propellant loading

lines, and the battery cooling lines The booster adapter section mates the Satellite Vehicle to the Titan IIID booster. The adapter is equipped

with 70 square inches of vent area. The separation joint with a redundant redundant pyrotechnic system is a part of this

section. The OAM/RCM section houses and supports the OAS/RCS hydrazine systems which provide orbit and attitude

control, the independent lifeboat freon gas system which provides emergency attitude control, and the solar

array modules which generate power. This section interfaces with ground pressurization and propellant loading lines. The solar array modules which mount on the aft bulkhead adjacent to the OA engine nozzle are not

shown in the photograph. The equipment section consists of

12

equally spaced, equally sized bays, each capable of supporting up to

500 pounds of equipment on individual trays. Two bays are presently unused and are available for growth items. Each equipment bay provides sufficient access to allow complete module installation and removal at the factory and pad as shown in the lower completely open bay. The other bays as shown have non-flight panels

with ground access doors used in factory assembly and test. This section interfaces with the main electrical

umbilical umbilical and the M id Section. Section.


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SA TELLITE TELLI TE BA SIC SI C ASSEM BLYE Q U I P M E N T S E C T IO IO N

T SECTION SECTION

AM/RCM SECTION

BOOSTER ADAPTER

AGE HANDLING RING .1

ID SECTION ORBIT ADJUST ENGINE NOZZLE

. . . . . . . . .

...• ..... •

............. •

Pr_

44;

4...

s! I

11


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A T T IT IT U D E C O N T R O L XIMESSIMMISIMURNIIIP

ffileSSIMESP

The Attitude Control System (ACS) provides earth-oriented attitude reference and rate sensing. It develops RCS thruster firing signals to bring the vehicle to a commanded attitude and to maintain attitude and rate within the accuracies shown below. The ACS also provides measurements measurements of vehicle attitude and rate during search/surveillance operation to the

accuracy shown. The ACS is a three-axis rate gyro-integrator system with updating in pitch and roll by horizon sensor and in yaw by gyro-

compassing. Error signals generated by the gyros and horizon sensor are combined in the flight control electronics, and modulated by pseudo-rate circuits in each axis to provide thruster firing commands with the impulse bit control necessary

to meet the tight rate control and short settling-time settling-time requirements. All elements are redundant for malfunction correction. Cross-strapping between redundant and primary ACS components (horizon sensors, gyros, flight control electronics assembly) is possible to permit selection of non-failed components components to drive the RCS thruster. Control Requirements

Pitch

Roll

Ya

easurement Requirements

Pitch

Roll

Ya

0. 001

0.001

For search/surveillance operations

Attitude Attitude accuracy ( deg)

0.7

0.7

0.64

Rate accuracy (deg/sec)

0.4

During non-horizontal operations

Attitude Attitude accuracy ( deg) Rate accuracy (deg/sec)

0.15

Setting time from search/surveillance search/surveillance disturbances: Stereo 0.2 seconds, Mono 6 seconds

1ef


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A T T IT U D E C O N T R L 1 THRUSTERS

NOTES:

t. I R A R O L L . P I T C H A N D Y A W C H A N N E L S

ATTITUDE CONTROL MODULE

MAY BE CROSS-STRAPPED INDIVIDUALLY

2. THRUSTERS MAY BE CROSS-STRAPPED AT PAIR LEVEL

THRUSTERS cz HORIZON SENSOR (PACS

THRUSTERS

3 HORIZON SENSO R (RACS)

4 I R A (P (P A C S 5 IR IR A ( R A C S ) EDUNDANT

PRIMARY OT SHOWN

( L O C A T E D OUTBOARD)

H/S ELECTRON ICS (PACS) H/S ELECTRON CS (RACS) F/C ELECTRONICS (PACS)

9 F/C ELECTRONICS (RACS)

BIF003W/2-093942-77

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FLT CONTR OL ELEC. , FLT CONTR OL ELEC.

HORIZON SENSOR

NERTIAL EFERENCE

NERTIAL HORIZON EFERENCE SENSOR

PRIMARY ATTITUDE REDUNDANT ATTITUTE CONTROL SYS (PACS) CONTROL SYS (RACS)


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R B IT I T A D JU JU S T A N D R E A C T I N C O N T R An Orbit Adjust System (OAS) and Reaction Control System (RCS) provide the forces necessary to control the vehicle orbit

and the vehicle attitude in orbit, respectively. The OAS provides injection error correction (if required), drag and perigee rotation makeup, and deorbit of the Satellite Vehicle at the end of the mission. The RCS provides pitch, yaw, and roll con-

trol via 8 thrusters. OAS and RCS both use catalytic decomposition decomposition of monopropellant hydrazine to generate thrust. For reliability, the systems

are pressure-fed, with the pressurizing gas enclosed in the propellant t ank with the hydrazine. This results in declining or blowdown pressure characteristics; the thrust level of the OAS engine declines from

to 100 pounds and that of the RCS

engines from 6 to 2 pounds. A quad-redundant valve operated by the command system controls flow to the OAS engine. The ACS generates signals that control the firing of the RCS engines. SV-15

the 62-inch diameter OAS tank can be loaded with up to 4000 pounds of propellant with two spheres containing high

pressure nitrogen (isolated by pyro valves and admitted into the OA tank at times selected during the mission) to maintain the

pressure within the desired operating range. This propellant can be utilized in OA burns to provide velocity increments of 2 ft/sec to 400 ft/ sec. A passive (surface tension) propellant management management device maintains propellant at the tank outlet at all times, permitting engine firings in any attitude.

On Vehicles SV-13 and SV-14 the two nitrogen tanks are manifolded directly with the OA ta nk and provide enough ullag space to permit 3700 pounds of propellant to be loaded within the operating pressure range. The four 22-in. diameter RCS tanks provided capacity for 450 to

40

pounds of propellant. Propellant orientation is main-

tained by diaphragms. The thruster impulse bit (0. 15 lb-sec or less, depending on blowdown status) is compatible with the

tight rate-control requirements. A complete redundant set of thrusters is provided for malfunction protection; either set can be supplied by the four tanks and each pair of thrusters can be driven by the primary or redundant ACS valve drivers. A transfer line is provided between the OAS and RCS tanks to permit propellant exchange to optimize the use of on-board propellant for each mission.


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ORBIT ADJU ST t REACTION CONTROLJ

fir 1ge, ""••• ._ V I EW E W L O O K IN IN G F O R W A R D

N I T R O G E N F I LL LL V A L V E C A P I L L AR AR Y G A L L E R Y

6 2 " D IA IA O R B I T A D J U S T

FILL V A L V E RC G A S F I L L V A L V E S ( 2 ) R C S P R O P E L L A N T F I L L V A LV LV E ISOLATION VALV ES (6 R C S G A S /P / P R O P T A N K (4

RCS THR USTERS (16

OAS ULLAGE T ANKS (2)

VIEW LOOKING AFT

QUAD

PROPELLANT

TANK

VALVE

CATALYST

NITROGEN FILL

VALVES (2)

NITROGEN

(6

HYDRAZINE

OAS € RC S FILL £ DRAIN ISOLATION VALVES (6

OAS ULLAGE TANKS ® 6 2 " D IA IA . O R B I T A D J U S T T A N OA/RCM J-BOX 10, ORBIT ADJUST ENGINE

Li BIF003VV/2-093942-77

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PRIMARY

EDUNDANT THRUSTERS

11


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E L E C T R IC I C A L D IS IS T R B U T I N A N D P O

ER

Power to operate the Satellite Satellite V ehicle is provided by solar arrays deployed from the A ft Section following following separation from the booster. Rechargeable NiCd batteries (type-40 ) provide energy storage to meet dark-side-earth and peak power req uirements. Unregulated power is distributed distributed throughout throughout the vehicle to using equipment within a 24 to 33 v dc range.

The pow er generation and storage system com prises four parallel segments, segments, with an array section, charge con troller, and battery in each to reduce the effect of a failure; a single malfunction will not terminate the mission. Fusing of equ ipment, limiting minimum w ire size, and isolating voltage-critical voltage-critical circuits add to the reliability. reliability. The power system is capable of providing providing approximately 1 ,000 watt-hours/day of usable power over a beta angle range of -8 to +60 deg by adjusting the array angle about the v ehicle roll axis. This will support at least 52 minutes per day of search/surveillance and mapping camera system operation.

Power for the lifeboat system is provided by one type-40 battery from the m ain power system. Eq uipment necessary for recovery vehicle and Satellite V ehicle deorbit can be switched to this battery for emergency operations. Depletion of the batteries below 55 percent or an excessive load on the m ain power system will automatically automatically isolate the lifeboat lifeboat system and its battery. This assures assures adeq uate power for the emergency operations. The lifeboat system can be reconnected to the main system by command if the anomaly can be corrected. Pyro pow er is provided by either of two type-40 batteries from the main pow er system and distributed by redundant circuits.


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ELECTRI ELECT RICAL CAL

STRIBU STRIBU TION TI ON POW ER SOLAR ARRAY PANEL

P O W E R D IS I S T R I B U T IO IO N J-BOX

MAPPING

EARCH/

PAYLOAD

AYLOAD

CAMERA SURVEILLANCE

t 22 PANEL SOLAR AR RAY (177 FT2) FT2) 2) POSITIONAL DRIVE ASSYS C H A R G E C U R R E N T C O N T R O L L ER ER S (INBOARD) 4 ) A FT FT P O E R D I S T R IB IB U T I O N J - B O X TYPE 40 BATT ERIES (4 F O R W A R D P Y R O J -B -B O X

AFT SECTION EQUIPMENT

WD DIST -BOX

LIFEBOAT II SEPARATION SWITCH ( H IG IG H C U R R E N T )

PYRO

COMMAND -+ YPE 40 ATTERY

TYPE 40 BATTERY

t IN IN T E R F A C E J - B O X E S 5 ) F W D P W R D I S T R IB IB U T I O N

J-BOX ) M A P P IN IN G C A M E R A M O D U L E 0- BOX

BIF003W/2-093942-77

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HARGE ONTROLLER

YPE 40 ATTERY

YPE 40

ATTERY

PYRO US#2

HARGE HARGE HARGE ONTROLLER CONTROLLER CONTROLLER

SOLAR ARRAY

OLAR ARRAY

117


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TELE ETRY AN D TR ACK NG t.1

The SGLS-compatible telemetry subsystem provides PCM real-time data (ascent at 48 kbps, engineering analysis at 128 kbps, and orbit at 64 kbps), and PCM tape recorded data (48 kbps played back at 256 kbps). The PCM telemeter provides status data for normal mission operation, test operations and evaluation, command

acceptance confirmation, and postflight evaluation. Each tape recorder storage allows the monitoring of the SV temperature profile by periodic sampling. Over 1500 data sources are monitored — some at up to 500 samples per second. The SGLS-compatible tracking subsystem provides range measurement information, including slant range (50 ft maximum la bias error and 60 ft rms maximum noise

error), range rate (0.2 ft/sec maximum la error), and angle-of-arrival (1.0 milliradian maximum la bias error and 1.0 milliradian rms maximum noise error).

fl


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T E L E M E T R Y E T R A C K IN G

MASTER UNIT

PCM REMOTE (5 PLACES)

TAPE RECORDER ATA

CI INSTRU INSTRU MEN TATION J-BOXES (3) 2 PCM R EMOTE (5) 3 PCM MASTER NO .1 PCM MASTER NO.2 3 TAPE RECORDER NO. 1

6 TAPE RECORDER NO.2

SIDEA' SIDE'S' SIDE' S'

PCM MASTER

il

CM MASTER

TIMING IGNALS

IMING

--------(6-

OUTBOARD

SIGNALS

ECORDER

st

ECORDER

QUIPMENT

'-

VCTS

VCTS NO. 1

1 VCTS NO

, CTS #2

ULTICOUPLER

ULTICOUPLER

9 BACK-UP TIMER

NTENNA

IL

10 CONTROL

BIF003W/2-093042-77

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19 111111111111111111111111101101



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E Q U IP M E N T L O C A T E D O OUTBOARD SIDE OF RACK (EXCEPT ITEM 6)

COMM AND SYSTE

DATA INTERFACE UNIT

0 3 7 5 M H z R E C E I V E R ( L I FE FE B O A T I 1 ) C D M I N I M A L C O M M A N D S Y S T E M (M (M C S ) COMM AND J-BOX TYPE 2 P R IM IM A R Y C O M M A N D B A C K U P RECEIVER VCTS RECEIVER NO.1

EC REMOTE DECODER

CMDS

6 (L (L O C A T E D I N B O A R D )

DATA INTERFACE UNIT ECS REMOTE DECODER

MCS BACKUP DECODER

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CMDS

BACKUP DECODER

OPER TIME

T IM IM I N G S I G N A L D A T A

VCTS RECEIVER NO. 2

IF003W/2-093942-77

CMDS

CMDS

1 ) E XT E N D E D C O M M A N D S Y S T E M (E C S )

IMING SIGNAL hips CMDS

NTERFACE IT

EXTENDED COMMAND SYSTEM

VCTS 110.2 RECEIVER

VCTS NO.1 RECEIVER

PRIMARY CMD BACKUP RECEIVER

ANTENNAS

MINIMAL COMMAND SYSTEM

375 MHz

RECEIVER


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L I FE FE B O A T I The lifeboat system provides emergency capability to initiate separation of two Reentry Vehicles (RV) and to

deorbit the Satellite Vehicle in the event of a complete failure of the main power system. the attitude control system, or the extended command system.

ti Emergency operational control is provided by the 375 MHz receiver and minimal command system, with

capability for real-time, stored-program, and secure commands.

Attitude control for RV releases and SV deorbit is provided by earth-field sensing magnetometers, rate gyros, and a cold gas (freon 14) control force system. Lifeboat is capable of RV releases and SV deorbit operations on both south-to-north and north-to-south passes.

Power to keep the system ready for use, and for the emergency operations is provided by a type-40 battery and 1/4 of the solar arrays from the main power system. The O AS engine and the redundant S GLS, PCM, tape recorder, and other equipment necessary for RV release, SV deorbit, and recovery of vehicle diagnostic data are switched from the main power system to the lifeboat bus for the emergency operations. In a nominal tumbling mode, enough power is generated to ke ep this emergency mode operating until the vehicle reenters.


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LIFEBOAT RATE GYRO (3)

ELECTRONICS TYPE 40 BATTERY

a_—

46. O U T B O A R D V IE IE W

FREON GAS

NBOARD VIEW

TANKS FILL VALVE

1 1 1 M I N IM IM A L C O M M A N D S U B S Y S T E M

REGULATOR

MAGNETOMETER (3 AXIS)

3 LIFEBOAT 11 J-BOX

THRUS TERS

75 MHz RECEIVER

375 MHz

RECEIVER

ANTENNA

MCS - ELECTRONICS 1

X-Y-Z AXIS MAGNETOMETER

-Y-Z AXIS

ATE GYROS

EGULATOR

FREON GAS TANKS THRUSTERS (6)

N-S-N

POLARITY SWITCH

F IL IL L V A L V BIF003W/2-093942-77

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1111111=


TOP SECRE T/

HARDW ARE FL •111111=112112111110111112119

The HEXAGON integrated test program begins at the piece-part level and continues through component,

module and vehicle levels of assembly.

esting at progressive levels of assembly permits workman-

ship faults to be identified and eliminated early in the test program.

verify piece-part specification. The SBA components are subjected to ambient, random vibration.

temperature-vacuum and burn-in burn-in acceptance tests for early detection and correction of design, parts and manufacturing defects. The components are then assembled into the aft section modules or installed

in the forward and mid-sections. mid-sections. The aft section electronic modules modules are subjected to ambient, acoustic and thermal vacuum tests. The propulsion module and solar array modules are subjected to ambient and acoustic tests. The sections are then mated to form the Satellite Vehicle which is then ready for the system level tests prior to VAFB shipment.

The nomenclature shown on the accompanying illustration indicates the contractor where manufacturing

or testing occurs:

SB AC — Satelli Satellite te B asic Assembly Assembly Contractor (Lockheed) WC — M idwest idwest Contract Contractor or (M cDonnell cDonnell Douglas) Douglas)

NEC — Northeast Contractor (Itek) OPC — Our Philadelphia Contractor (General Electric) SSC — Sensor Subsystem Contractor (Perkin-Elmer)


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H A R D W A R E FL FL O W SHROUD ACOUSTIC TEST

AND CLEANING

SHROUD MFG (SBAC)

ASSY/TEST (NEC

^, ,- M TEST

ASSY/TEST RV'S (OPC)

ALIGNMENT & TEST WD SECT BUILD-UP

F W D S E C T M F G ' ` B !,

STACK

impr 7-7 777

RV ASSY/TEST (MWC,

MID SECT MFG (SBAC

INSTALLED PRIOR TO VAFB SHIPMENT

MID

MODULE BUILD-UP

ASSY & TEST (SS&

MODULE TEST

AFT SECT ASSY (SBAC)

MID SECT RECEIVING AND INSPECTION

1171

OAM/RCM BUILD-UP

I N T E G R A T I O N & TESTING SOLAR ARRAY BUILD-UP &

TEST

EQUIP RACK BUILD-UP



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H A R D W A R E FL FL O W

M O D U L E TEST AM

COLLIMATION TEST

SHIPPING SHIPPING PREPS

TRANSPORTER

Project HEXAGON Overview

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