Project HEXAGON Overview

8/4/2019 Project HEXAGON Overview

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HEXAGON CY31 DECEMBER 197772 SHEETS

P R O J EC T H EX A G O N

OVERVIEW

C L A S S I F I E D B YVEMAN 1XEM PT F R O M GEN ER AL D EC LASSI FI C AT IONS C HE D UL E O F E 0 11662 , E X E MP TI O N C A TE G O RY 58 . 12)

AU T OM AT I C ALLY D EC LASSI FI ED ON : I M POSSI BLE T O D ET ER M I N E

NA TI O NA L S E C URI TY I NFO RMA TI O NUNAUTHORIZED DISCLOSURE SUBJECT TO CRIMINAL SANCTIONS I

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A S SO C IA T E C O N T R A C T O R Sn11 1nO

Project HEXAGON is a team effort consisting of nine major contractors throughout the United States. These contractors

provide a coordinated effort by using Interface Control Documents as binding technical agreement on responsibilities and

performance of their respective equipments. The project HEXAGON team consists of:

Search/Surveillance (Stereo Panoramic)

Two Camera Assembly — Perkin-Elmer, DanburyFilm supply and take-up units — Perkin-Elmer, DanburyShroud, Mid and Forward Section structure — Lockheed, SunnyvaleReentry vehicles (Mark 8) — McDonnell Douglas, St. LouisFilm — Eastman Kodak, Rochester

M apping and Geodesy SystemStellar and terrain cameras — Itek, BurlingtonReentry vehicle (Mark V) — General Electric, PhiladelphiaStructure — Lockheed, SunnyvaleFilm — Eastman Kodak, Rochester

Satellite Control Section

Telemetry, power, and pyros — Lockheed, SunnyvaleCommand system — General Electric, UticaAttitude control and orbit adjust — Lockheed, SunnyvaleStructure and booster adapter — Lockheed, Sunnyvale

B ooster Vehicle — Titan IHD

Stage 0 solid propellant — United Technologies Chemical System Division, SunnyvaleStage I and II liquid propellant — Martin Marietta Corporation, Denver

The photographs were taken via the search and surveillance camera and magnified 40 times.

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A E R O S P A C E V E H IC L E

The HEXAGON Satellite Vehicle is launched by the Titan HID Booster Vehicle. When

mated together, the entire assembly is termed the Aerospace Vehicle.

The Aerospace Vehicle is launched from Space Launch Complex -4 East, Vandenberg

Air Force Base. The Solid Rocket Motor, Stage I and Stage II are stacked at the launch

site and functionally tested. The complete SV including the shroud is mated to the

booster vehicle fourteen (14) days prior to launch. The Aerospace Vehicle is then func-

tionally checked and all propellants and gases are loaded.

The booster vehicle can place 24,800 pounds into an 82 x 144 nm (perigee x apogee) orbit

with an inclination (-97 degrees) that provides the nearly sun synchronous condition

needed for long life missions.

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T IT A N IIID B O O S T E R V E H ICLE

The Titan HID booster vehicle is a three-stage booster consisting of the standard liquid core for Stages I and II

plus two solid rocket motors (SRMs) as Stage 0.

Each SRM is 10 feet in diameter and 85 feet long. It consists of five identical interchangeable segments, a six-

degree canted nozzle, a gas generator type igniter, staging rockets, and an externally mounted thrust vector

control (TVC) injectant tank. The TVC provides steering during Stage 0 burn by injecting nitrogen tetroxide

(N2

04) through 24 proportional valves around the SRM nozzle. Jettison is provided by pyrotechnic separation

of the interconnecting structure between each SRM and the Titan core vehicle, followed by ignition of four solid

staging rockets at each end of each SRM.

Stage I liquid core is 10 feet in diameter and 71.5 feet long. It is aluminum skin-stringer construction with

propellant tanks arranged in tandem. The two turbo pump feed Aerojet LR87-AJ-11 engines burn a 50-50 blend

of hydrazine/UDMH (Aerozine) as the fuel and nitrogen textroxide as the oxidizer. Each engine subassembly

contains a regeneratively cooled gimballed thrust chamber combined with an ablative skirt extension giving a

15:1 expansion ratio.

The Stage II propulsion system is similar to that of Stage I. It is also 10 ft in diameter but only 31 feet long.

The single engine thrust chamber is also regeneratively cooled and has an ablative skirt extension that providesan overall expansion ratio of 49:1.

The flight control system stabilizes the vehicle from launch to SV separation in response to (1) attitude data,

(2) rate data, (3) command data — issued by flight control computer and/or the radio guidance system via ground

tracking station.

Electrical power for the flight control system, instrumentation, flight safety, and electrical sequencing system

is provided via silver-zinc primary batteries.

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O P E R A T IO N A L EV E N T S

The major operational events are launch, orbit maintenance/payload operations, and RV recovery/SV

deboost. Sequence of launch events:

0.0 secRM Ignition

0.2ift-off

40.0ransonic passage

54.0aximum dynamic pressure

113 .9ore I start burn

125.3RM separation

262.0ore I shutdown and Core H start burn

262.7ore I separation

276.0hroud separation

460.6ore II shutdown

472.6ore II separation (injection)

The solar arrays are deployed after SV stabilization on Rev 1 with payload operations starting on Rev 5.

Orbit adjusts to correct period, altitude and perigee location occur every two to four days. All control of

the SV and telemetry data is processed through the Air Force Satellite Control Facilities and associated

remote tracking stations.

The SV is pitched down to a specified angle for each RV ejection. The SV is deboosted for ocean impact

after the last RV is ejected.

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U S A F T R A C KIN G N E T W O R K

The Sunnyvale Satellite Test Center (STC), part of the SAMSO Satellite Control Facilities, is organized to provide

operational control of on-orbit satellites and does this function for project HEXAGON. The center directs the trackingand commanding of these satellites through a net of remote tracking stations (RTS). The STC also coordinates the aerial

and surface recovery operations for reentry vehicles (RV). Launch activities are a coordinated effort between the

V andenberg AFB Test Wing and the STC.

Servicing the HEXAGON vehicle requires skin and beacon tracking, recording and displaying telemetry data, and com-

manding that often needs more than one RTS each revolution. Because the STC supports several programs, the Mission

Control Center (MCC) within the STC is used to direct the effort of each tracking station in support of each program. The

SV real time telemetry data incoming to the RTS are processed and displayed in real time via 1200 bit lines or relay satel-

lites to the STC. The SV real time and recorded data are recorded at the RTS for later playback to the STC. Complete

RTS recorded tapes are flown to the STC as permanent records. Display and analysis of these data provides SV health

and status information to the Technical Advisor (TA) staff on a continuous basis throughout the mission. The TA staff,

located at the STC, includes operational specialist teams for each major contractor.

The remote tracking stations acronyms and locations are as follows:

Vandenberg Tracking Station (VTS) or COOK at Vandenberg Air Force Base, California

Guam Tracking Station (GTS) or GUAM on Guam Island

Hawaii Tracking Station (H TS) or HUL A at Kaeha Point on the island of O ahu

Indian Ocean Station (I0S) or INDI in Seychelles Island group on Mahe' Island

New Hampshire Station (NHS) or BOSS near New Boston, New Hampshire

Thule Tracking Station (TTS) or POGO at Thule Air Force Base, Greenland

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S E A R C H / S U R V E I L L A N C E C A M E R A S

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S E A R C H /S U R V E IL LA N C E C A M E R A S

The search/surveillance cameras provide high-resolution stereoscopic coverage of selected areas

on the earth's surface by using two independently controllable panoramic cameras. The system pro-

vides a target resolution of 2.7 ft or better at nadir when operating at primary mission orbital alti-

tudes with an apparent target contrast of 2:1, sun angles greater than 30 degrees and using *S0-208

film.

The search/surveillance system has been designed with the following characteristics:

Optics0-in. focal length, f/3 Folded Wright (ModifiedSchmidt) System

Film.6-in. wide film — Type 141 4 or S0-208 (B & W),S0255 (C olor), and 50130 ( Infrared)

Film Load23,000 ft Type 1414 or 144,000 ft S0-208 percamera (1950 lb total)

Film Resolution (2:1 Contrast)enter of format 155 1/mm, elsewhere informat a 94 1/mm

Field Angle2. 85 Degrees

Scan Modes0, 60, 90, and 120 degrees

Center of Scan, ±15, ±30, and ±-45 degrees

M aximum Scan Angle60 degrees

Stereo Convergence Angle0 degrees

Frame format (120 degree scan)-in. by 125-in.

Film Velocity00 in. /sec (maximum) at focal plane

Image M otion Compensation Range.018 rad/sec to 0.054 rad/sec for Vx/H±0.0033 rad/sec for Vy/H

Weight (less film)375 pounds

*S0-208 is a thinner base equivalent to Type 1414 film used extensively for the first 13 missions.

L.//

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T W O C A M E R A A S S E M B LY

The Mid Section has been rotated to show the side that looks toward the earth with the two

Camera Assembly (TCA) exposed. In flight, a black fiberglass baffle and a multilayer

insulation covers the gas spheres and optical bars except for view ports. Doors cover

the electronics and then multilayer insulation blankets are installed. Not shown are the

film take-up reentry vehicles in the Forward Section.

The two optical bars rotate in opposite directions indicated by the arrows adjacent to thelenses. The light is conducted along a folded path to the film platen where the film motion

is matched to the image motion by the commands generated in the electronics.

Normally both optical bars are commanded on simultaneously to reduce vehicle roll torques.

However, each camera can be commanded individually, and either may be operated alone,

if desired.

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S Y S T E M F IL M P A T H

The coarse film transport includes all components that operate at nominally constant speed during

photography and recycle, as well as the looper carriage which operates at the recycle frequency. The

supply and take-up control system maintains a steady flow of film into and out of the loopers at pre-

cisely the average rate at which film moves through the platen. The loopers serve as an interface be-

tween the coarse and fine film transport system. Total film in the looper is constant but relative

lengths in supply and take-up sides vary with looper carriage position.

The control of film tracking is by active and passive articulators. The film path of the forward camera

functionally includes component assemblies in the following order:

a. Supply "B " g. Platen m. Take-up 4

b. Seal Door/Exit Vestibule h. Metering Capstan n. Articulator

c. Articulator Steerer i. Output Drive Capstan o. Takeup 3

d. Looper j. Crossover p. Articulator

Crossover k. Looper q. Takeup 2

Input Drive Capstan 1 . Articulator Steerer Articulator

Takeup 1

The film supply spools rotate in opposite directions, and the respective take-up spools rotate opposite to

the supply spools in order to reduce vehicle torques. The start-up disturbances are minimized by

accelerating the film path to the required coarse velocity before photographic operations are begun.

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O P T IC A L B A R A S S E M B L Y

The two cameras mounted in a frame make up a two-camera assembly with each

camera having a folded Wright optical system mounted in a rotating optical bar.

Structurally the bar consists of two rigid end bulkheads separated by a cylindrical

tube with housings and hollow shafts at each end on which bearings are mounted.

The platen end bulkhead is the member to which the optical components are refer-

enced. The optics consist of the corrector plate as the aperture, a folding flat

mirror, a concave primary mirror and a field group of refracting elements and a

filter. The optics wavefront errors spec values are shown as a fraction of the

wavelength. All values are root mean square (RMS).

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F I R S T E LE M E N TS E C O N D E L E M E N TT H I R D E L E M E N T

F O U R T H E L E M E N TF iLTER

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O P T IC A L P A T H

The optics for each camera are mounted in an optical bar (OB). The system is a

f/3 folded Wright. The aperture is formed by an aspheric corrector plate that cor-

rects for spherical aberration. Light entering the aperture is folded 90° by the folding

flat and reflected onto the primary mirror at the far end of the OB. The primary mir-

ror focuses the light back through the field group mounted in a center hole in the folding

flat. The field group includes four refracting elements and a filter. The refracting

elements provide correction for the field curvature and residual chromatic aberration

characteristics of optical systems using a concave primary mirror.

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O P T I C A L B A RCAMERA "A"

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P L A T E N A N D F IL M D R IV E

The platen is mounted at the focal plane end of the optical bar (OB). The platen assembly

is mounted on the OB's inner housing to support the film in the camera focal plane, and

to rotate on its own bearings independently of the OB. While the OB is rotating continu-

ously on its end bearings, the platen assembly is free to oscillate through its 130-degree

operational arc. The fine film drive assembly encloses the outer end of the platen assem-

bly and is stationary. A twister assembly, included in the fine film drive assembly, accom-

modates the twisting of the film path at the interface between the stationary film drive

assembly and the oscillating platen assembly. The twister assembly consists of a twin

air-bar assembly and a housing that incorporates a manifold through which nitrogen gas

is supplied to the bars. The use of air bars in the twister, rather than rollers, permits

the film to translate along the length of the bars without damage as the film path twists.

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P L A T EN A N D FIL M D R IV E





Dry nitrogen gas is supplied to the film path air bars at specified flow rates and pressures. Air bars are located

in the twister, TCA cross-over, and the supply cross-overs. These bars are D-shaped in cross-section and

hollow with small holes in their curved portion through which nitrogen is forced by the pneumatic system. This

provides a practically frictionless bearing for the film, permitting both lateral film movement and film transport

across the bar. The nitrogen supply is two spherical tanks with a combined storage capacity of 68 pounds of which

62 pounds are usable.

Pressure enclosures seal the entire film path including the film supply and the take-ups, maintaining the required

relative humidity for film moisture content stabilization. The film path gaseous environment includes the 50 pounds

of water in the film as outgassing water vapor plus the 62 pounds of nitrogen coming through the orifices of the gas

bars. During non-operating periods the film supply unit is isolated from the rest of the film path by a commandable

seal door to minimize leakage and moisture loss.

In test and during ascent the sealed film path accommodates atmospheric pressure changes through relief and pres-

surizing valves. When film is being transported, a lower pressure relief setting in the film path compared to that

in the supply allows a system pressure bleed-off through vents on the forward steerer enclosure.

The pneumatics supply module is a self-contained unit consisting of high pressure storage spheres, regulators, and

valves. The system is designed with individual paths from a supply sphere to a camera with cross-overs at the high

pressure and low pressure portions of the system. The high pressure cross-over valve between the nitrogen tanks

is normally closed. It is used to transfer gas from one tank to the other. To isolate a flow path, on external com-

mand or in response to a feedback signal of over-pressure downstream of the regulator, a solenoid latching valve

in the high pressure portion is closed. Normally, a uniform simultaneous flow through both sides is maintained

by the open low pressure cross-over valve, which is commanded closed only because of any failure requiring isolation.

The shut-off valves in the low pressure paths are commandable, controlling on/off requirements of gas flow.

P N E U M A T IC S S YS T E M

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CROSS OVER VALVENORMALLY CLOSED)

LOW PRESSURECROSS OVER VALVE'NORMALLY OPEN,

II . ISOLATION VALVE

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L A R G E L O O P E R

The accompanying illustration shows a Two Camera Assembly (TCA) incorporating the

large looper which will become operational with SV-17. The increased film capacity

(45 feet versus the 13 feet on the original design) enables the platen to be fed film at the

desired rate during the time the coarse transport system is accelerating and to be stopped

while the coarse film transport system is decelerating. Film management is greatlysimplified since all the film is used in sequence. The present delay in the start ofphotography until the coarse film transport has accelerated to the average rate and the

rewind of unexposed film passed through the platen is eliminated. This removes rewind

as a possible source of contamination or as a wastage of film when rewind could not be

accomplished between nested operations. Because this major change is being accom-

plished in-line, full provisions are retained to operate the coarse transport system in the

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M A R K 8 R E E N T R Y V E H IC L E

Wnen the take-ups in the RV are filled, the next in-line RV is enabled and the full RV is ejected from the

optimized pitched down SV at a 3 ft/second rate. The spin-up to 10 radians per second is accomplished via

hot gas generator to stabilize the RV during the retro rocket motor burn. The retro rocket provides a

1623 pound thrust to slow the RV for reentry. The despin system then slows the spin rate to 1.4 radians per

second, which provides the needed stability during the coast period and still permits the aerodynamic torques

to align the RV angle-of-attack with the flight path early in the reentry period. The drogue parachute is de-

ployed upon closure of an acceleration switch at approximately 60,000 ft altitude. The drogue parachute is

released and main parachute deployed upon closure of a barometric pressure switch at about 50,000 feet.

At 15,000 feet, the rate of descent is from 1200 to 1650 feet per minute, which is suitable for aerial recovery

by USAF JC130 aircraft.

Each RV has a base diameter of 57-1/2 inches and is 85 inches from the heatshield nose to the retro motor

nozzle. Maximum total weight of the RV and film is 1695 pounds. This consists of 956 pounds of RV and

equipment, 239 pounds for film take-ups, and 500 pounds of film.

The heatshield when removed shows the gold tape covered canister which is part of a passive on-orbit thermal

control system which, together with electrical heaters, maintains the desired canister temperature. The

propulsion truss assembly and SV attachment fittings are shown.0


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MIN SEC

IPIN-UP 0-02

2ETROGRADE 2:05

3PIN-DOWN 2:40

4RUSS SEPARATION 2:45

5TMOSPHERIC ENTRY 2:55

6ROGUE &MAIN CHUTE DEPLOYMENT 9:37

7EAT SHIELD SEPARATION 9:59

8ERIAL RECOVERY 27.55

SPIN-UP EVEN T R V W I TH O U T H E A T S H I EL D

R E C O V E R Y S E Q U E N C E

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T-1

D A T A R E C O V E R Y O P E R A T IO N S

The target cone is 10 feet in diameter and 15 feet high. It contains the nylon load lines which are

engaged by hooks on the retrieval line loops deployed by the retrieval aircraft.

The minimum dispersal impact area applies to all normal film load with the maximum dispersal area

applicable to a maximum unbalanced film load. In an emergency, recoveries may be required outside

this designated area toward Midway Island or the California Coast.

If aerial retrieval is not accomplished, water recovery becomes a backup phase. When sea water

contacts a sensor, a relay closes the film canister vent valve and transfers vehicle power to the water

recovery beacon. A salt water corrosion plug will sink the recovery capsule in 48 to 60 hours after

water impact. This allows a reasonable time for location and pickup by Air Force and Navy forces.

If the RV significantly overshoots the specified impact point, it will be destroyed. This is accomplished

by ejecting the heatshield and deploying the drogue chute if aero drag has not produced 0.003 g by a given

time after RV separation. This results in the RV burning up when the atmosphere is encountered. This

provision has not been utilized on the HEXAGON program to date.


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DISPERSAL IMPACT AREA

M A R K 8 R E C O V E R YCAPSULE

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M A R K 8 EQ U IP M E N TiThe film is shown passing through the RV. Transfer of film to this RV consists of transferring take-up

power, wrapping film on this take-up, cutting and sealing the film path on the exit side, followed by cuttingand sealing the inlet film path on the forward RV.

The RV base ablative cover consists of panels of ultra low density material. The base panel structures are

of fiberglass honeycomb sandwich construction. A laminate of graphite blankets over glass fiber blankets

covers the main parachute compartment. The circuit interrupter switch and wire bundles are mechanically

separated near the ablative surface by a guillotine prior to physical separation of the RV from the SV.

The bottom view shows the film on take-up A and B. The take-up drive motor and control electronics are

contained mainly within the take-up hub. The canister is shown removed for access to the take-up and the RV

equipment. This access greatly enhances film tracking alignments and testing during SV factory testing.

The RV assembly shows the structural frames within the RV which provide mechanical support for the take-up

assembly and RV equipment. Of the encapsulated volume inside the RV, 18 ft 3 is for the take-up assembly

and 13 ft3

is used by the RV equipment. The film stack diameter can be up to 35 inches. RV power distribu-

tion and event sequence control is provided by relays. Time delay relays are used to control sequence timing.

Instrumentation is provided for monitoring the deorbit-reentry events and temperature. This data is proc-

essed through the PCM commutator to the tracking and telemetry transmitter.


17003W/2-093942-77




ACCESS DOORF I L M PA TH O U TL E T

TOP SECRET/HIF003W/2-093942-77

F IL M O N R V T A K E U P S

I N L E T

A R T I C U L A T O RS U P P O R T

I I .--SB A

SPOOL-AR OTATION S P O O L - BR OTATION

O U T L E T

F I LM C H U T E

A R T I C U L A T O R

C U T T E R / S E A L E RA S S E M B L Y

_LA_

F I LM T H R O U G H R V

PROPULSION TRUSSS P I N - O F F C O N N E C T O R

CIRCUITI N T E R R U P T E R

S W I T C H

VH F A N T E N N A

P A R A C H U T ESOFT COVER

DROGUEMORTAR COVER

RV ASSEMBLY

ACCESS DOORF I L M PA TH I NL E T

RV BASE ABLATIVE COVER

TOP SECRET/H

M A R K 8 R V E QU IP M E N T





S E A R C H C A P A B I L IT Y

T O P S E C R E T /H 431F003W/2-093942-77

T O P S E C R E T /HNRO APPROVED FORRELEASE 17 September 2011



S E A R C H /S U R V E IL LA N C E O P E R A T IO N S211 1 1 1 1

Scanning is accomplished by continuous rotation of the optical bars at a rate to produce a nominal

three percent frame-to-frame overlap allowance at nadir. The minimum scan sector is 30 degrees,

the maximum 120 degrees. To achieve stereoscopic coverage the port camera (camera-A) looks

forward 10 degrees and the starboard camera (camera-B) looks aft 10 degrees. At 88 nm altitude the

interval of the forward to the aft frame is 31 nm. Since camera-B lags camera-A with respect to

ground cover at nadir, the shutter of camera-B is inhibited for the first three frames and camera-A

for the last three frames of each operation. Either camera can be operated separately in a mono mode.

The ground format varies with altitude, scan sector, and scan center. With the optical bars counter-

rotating the ground formats for the two camera are not the same. The area of coverage per mission

also varies with the average scan sector of acquisitions. At ±45 degrees average scan with the maxi-

mum supply of 1414 black and white film. gross stereo coverage of 20 million square nautical miles

(M sq. nm) can be achieved at an average acquisition altitude of 88 nm with the current film transport

system. At an average scan of ±30 degrees, this coverage would be reduced to 16 M sq. nm.


IF003W/2-093942-77




2 P A N C A M E R A S

T O P S E C R E T / Hr m w w -

S E A R C H /S U R V E IL L A N C E O P E R A T IO N S

AFT /F R A M E

LINE OF FLIGHT

BIF003W/2-093945-77

/***-O B J E C T I V E S

CONTINUOUS SEARCH

PAYLOAD DATAS T E R E O P A N O R A M I C C A M E R A

60-INCH FOCAL LENGTH246,000 FT - 6 .6 INCH UTB F ILM

FORMAT - VARIABLEC OV E RA GE - 20 M S Q NM / M I SS I ON S T E RE O

- R ESO LU T IO N - 2 . 1 TO 7 . 5 FEET G R D( N A D I R T O 60 D E G R E E S )

F O U R R E C O V E R Y V E H I C L E SFOR PANORAMIC CAMERAS

O R B I T A L D A T AINCLINATION - 96 .4 DEGREES SUN- SYNCHRONOUS

AVERAGE PERIGEE - 88 NMA V E RA GE A POGE E - 155 NMMISSION L IFE - UP TO 180 DAYS

'5T O P S E C R E T /H







T O P S E C R E T / HNRO APPROVED FORRELEASE 17 September 2011



T H E C A P IT O L

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.

T O P S E C R E T / H8 BIF003W/2-093942-77










TOP SECRET/H

PAN ORA M IC SYSTEM FLEXIB IL ITYr-1

F R A M E S

110 NM CAPABILITY

S C A N S E C T O R S

30, 60, 90, 120

D E G R E E S A T F U L LS C A N

CENTER OF SCAN

0, *15, ±30, ±45D E G R E E S

L

J

CONTIGUOUS AREAACQUISIT IONS

BIF003W/2-093942-77 TOP SECR ET/H





5°SCAN AN GLE MARKS

C O N T IG U O U S W ID E A R E A C O V E R A G E

r START OF FRAMEiS T A R T O F O P E R A T I O N

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

F I L M T R A V E LDIRECT ION

31.4" = 30° SCAN (MIN)

FRAME 1 FORMAT

VANDENBERG AFB IMAGE

2.5"

IRAME 2 FORMAT

1 3

6 .6"

AP P RO X I M A T E L Y P ARAL L E L T O •S V G R O U N D T R A C K

•• •• •• •• F IL M S E G M E N T ••• ( F U L L S C A L E ) • TIMING DOTS

E V E R Y 2 M I L L I-S E C O N D S

S V T IM E W O R D( O N C E P E R F R A M E )

TOP SECRET/Llik BIF003W/2-093942-77




T O P S E C R E T / H

M ID E A ST C O V E R A G E




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 report of the acquisition of these areas is achievable.

54 T O P S E C R E T /H BIF003W/2-093942-77




B R O A D A R E A A C Q U IS IT IO NNRO APPROVED FOR




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 se-

lectable scan sector and scan center combinations. The maximum 120 degree swath

width is illustrated for a 20 minute contiguous operation acquiring a 4800 nm long

area, 32 2 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.

56 T O P S E C R E T /H BIF003W/2-093942-77

U

-1 2

T O P SECREVH




T O P S E C R E T /HIF003W/2-093942-77

BROA D A REA A CQU ISIT ION

± 60° SCAN SECTOR

20 MINUTE CONTIGUOUS ACQUISITIONALONG LINE OF FLIGHT SHOWN

THE AREA COVER ON THIS PASS ISAPPROX 1.54 M SQ NM AT 88 NM

57








S E A R C H G L O B A L C O V E R A G E




4 -4

This is a representative 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 taken 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 con-

sist of: USSR 6.87, Eastern 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.

60 T O P S E C R E T /H BIF003W/2-093942-77

TOP SECRET/H

. H NRO APPROVED FORRELEASE 17 September 2011



S EA R C H G L O B A L C O V E R A G EI

E U R A S I A

C O M P O S I T E I N T E L L I G E N C E S U M M A R Y

M S N 1 2 0 9

30 OCT 74 - 7 MAR 75

LEGEND

N M C L E A R S T E R E O C O V E R A G E

C L E A R M O N O C O V E R A G E

4,

TOP SECRET/H 61


C O V E R A G E H IS T O R Yr-c




The initial contract for HEXAGON was to fly each vehicle for thirty days every 60 days

for a 50% search coverage. The highly successful on-orbit performance, higher alti-

tude, and design improvements of HEXAGON has allowed longer mission durations. This

has resulted in extending search and surveillance operations up to 17 6 days.

The gap in continuity (RV #4 recovery to next 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, opera-

tional coverage with the acquisition and subsequent return of imagery data was available

approximately half the time.

L

L

62 T O P S E C R E T /H BIF003W/2-093942-77

TO P S E CRE T/ H




C O V E R A G E H I S T O R Y

LAUNCH MOON DAY1 2 0 1 or1202

G A P - D A Y S120320 420 5

8 11—k--;1I I39

1 2 0 8

1 481 2 0 7 1 2 0 6

62

1973

1 2 1 02 1 12 1 2

W 4,02

1 9 7 6

1 2 1 3 '

1 9 7 7

TO P S E CRE T/ HIF003W/2-093942-77


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

-0




Since the first launch on 15 June 1971 the increasing mission life (from 32 to 176 days) hasresulted 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 preceded 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 the potential of the SV will produce on the average as many as 60 days

of operations preceding the recovery of each RV.

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

get is photographed; however, this option has not been selected to date.

Solo operations have been used to exploit the SV capabilities without risk to RV recovery.

Solo tests have been instrumental in successfully increasing mission durations.

U


IF003W/2-093942-77

TOP SECRET/H




INCREASING DU RATION B ETW EEN RECOVERIES1 0 -

MISSIOND A Y S

2 00000 02 04 06 08 0

1 2 0 1

1 2 0 2

1 2 0 3

1 2 0 4

1 2 0 5

1 2 0 6

1 2 0 7

1 2 0 8

1 2 0 9

1 2 1 0

1 2 1 1

1 2 1 2

1 2 1 3

S O L O

lihkNaa

R V - 1RV-2 gV - 3vvV-4 3

A TIME RV-136 D A Y S

A TIME RV-234 DAYS

A TIME RV-30 DAYSM A XIM U M T O D A T E

A TIME RV-446 DAYS

BIF003W/2-093942-77 TOP 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 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.

T O P S E C R E T / H6 BIF003W/2-093942-77





S O -1 30 IN F R A R E D C O L O R F 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 reflec-

tance as a magenta colored image. Healthy vegetation will appear as bright magenta and will change ineither color or brightness as the plants degrade.

As a result of this characteristic, SO-130 is an ideal film for 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. 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 erosion 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.

T O P S E C R E T /H8 BIF003W/2-093942-77





F IL M T Y P E S F LO W NISZENUNIIMOF




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 coated on an ultra-thin 1.2 mil base. This will allowapproximately 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-contrastresolution than the conventional B & W films. It is coated on a 1.5 mil base and has an AFS of 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 SO-460 with the yellow AH dye removed. This results in an increase ofemulsion 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 Dispersed Cubic" emulsions sometimes also referred to as "J" coat-ings. These emulsions exhibit extremely fine grain, high resolution, and very slow emulsion speeds. Thisfilm 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.

E l

T O P S E C R E T /H0 BIF003W/2-093942-77

TO P S E CRE T/ H




F IL M T Y P E S F L O W N

F IL M T Y P E S

MISSION A E R I A L 1 54 1 4SO-255 I S O - 1 3 0 I S O - 2 0 8 I S O - 1 2 4 I S O - 4 6 0 I S O - 4 6 4Fi lm Footage - Feet

1 2 0 1

1 2 0 2

1 2 0 3

1 7 2 , 6 4 0

1 5 6 , 1 1 5

1 8 5 , 3 2 5

1 2 0 4 208,454 10,0001 2 0 5 216,010 2,000

1 2 0 6 1 9 1 , 0 1 7 21,000 5 0 0

1 2 0 7 207,832 4,984 5 0 0

1 2 0 8 210,069 2,588 3,000

1 2 0 9 217,338 8,150 3,400

1 2 1 0 210,156 9,150 3,150 3,750

1 2 1 1 1 5 3 , 9 4 2 4,500 4,500 4,500

1 2 1 2 231,450 4,500_ 4,500

1 2 1 3 1 9 8 , 5 3 6 3,500 5,500 20,000 7,000 8,000 2,000

T O T A L S 2,558,884 70,372 25,050 24,500 3,750 7,000 8,000 2,000

BIF003W 2-093942-77 71O P S E C R E T /H i





M A P P I N G S Y S T E M

T O P S E C R E T /H1F003W/2-093942-77 73


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

NRO APPROVED FOR




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

1:50, 000 scale maps. Photogrametric data is achieved by 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 orien-

tation 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 pro-

viding 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 are returned in a single Mark V recovery vehicle.

The doppler beacon system and NAVPAC system provides ephemeral information which accurately

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

imagery.

74

O P S E C R E T /H

IF003W/2-093942-7


M A P P IN G C A M E R A O P E R A T IO N SNRO APPROVED FOR




T E RRA I N M A P P I NG C A M E RAB I LA P P H O T O G R A P H Y

5 5 % O V E RLA P

1 0 B T E C T I V E S

M A P P I NG A ND G E O D E T I C S URV E Y

P A Y LO A D D A T A

M A P P I NG C A M E RA

3,300 FEET - 9 .5 INCH EK 3414 F ILM (TERR AIN)

2,000 FEET - 70 MM FILM (STELLAR)F O R M A T - 1 34 X 6 7 N M A T 8 8 N MC O V E R A G E - 5 .4 M S Q N M / M I S S IO N

ONE RECOVERY VEHICLE

FOR TERRAIN AND STELLAR CAMERA FILMS

O R B I T A L D A T A

IN C L IN AT IO N - 9 6 . 4 D EG R EES SU N - SYN C H R O N O U SAVERAGE PER IGEE - 88 NMA V E RA G E A P O G E E - 1 55 NMMAP P IN G M ISS IO N D U R AT IO N - U P T O 120 D AYS

75

70% OVERLAP

AT 88 N M . AL T IT U D E

BIF003W/2-093942-77 T O P S E C R E T /H

T E RRA I N M A P P I NG C A M E RA

TRILAP PHOTOGRAPHY


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

NRO APPROVED FOR




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 sys-

tem, 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.

T O P S E C R E T /H6 BIF003W/2-093942-77

TOP S E C R E T / H

M A P P IN G C A M E R A S Y S TE MNRO APPROVED FOR





8

R E C O V E R YV E H I CLE

M U LT I LA Y E RB L A N K E T SI

w. I 1 1T E L L AR C A M E R AL IG H T B A F F L E

RTF00:3W 2-0 3 42-77 77


M APP IN G CAM ERA DESCRIPT IO N

NRO APPROVED FOR




F R A M EA D V A N C E

2.76-IN

( 7 0MM)F I LM WI D T H

TITLE MARKS

- S T A R T O FO P E R A T I O N MA R K

4.33-IN.

(110 MM) DIAMETERM I N I M U M U S E F U LF O RM A T (RE F )

R E S E A U S E R I A L N O ,

O R I G I N O F R E S E A UR O W A N D C O L U M NNUMBERS (TYP)

10 M

10

DA TAB LO C K

10.75±

FRAMEL E N G T H T I T L E

4.330-IN

(110 MM)I MA G E

LE N G T H

STELLARSUPPLYASSEMBLY

STELLAR F ILMCHUTE

T E R R A I N S U P P L Y

ASSEMBLY

STELLARBAFFLE

STELLAR LENSES

M A R K V S A T E L L I T ER E C O V E R Y V E H I C L ET E L L A R A N D T E R R A I N

T A K E U P A S S E M B L Y

M A I NI N S T R U M E N TA S S E M B L Y

T E R R A I N L E N S

D I R E C T I O N

T H E R M A L S H U T T E R A S S E M B L Y

E L E C T R I C A L D I S T R I B U T I O NM A I N I N S T R U M E N T S Y S T E MN D P O W E RE L E C T R O N I C S A S S E M B L Y

PRESSURE M AKEUPFSYSTEM

-C o

- 9.44S-IN. FILM WIDTH (REF)

9.00IN.0 M M )

USEFULF O R M

O R MA T

FIDUCIALL O C A T I O N(4 PLACES)

T I TL E A RE A

o L2S TA RT O FO P E R A T I O N MA R K

TITLE MARKS

.y

D I R E C T I O N O F F L I G H TA N D F I L M A D V A N C E0

D A T A B L O C K L O C A T I O N( A P P LI E S T O F R A ME S H O W N )

RE S E A U S E RI A L NU M B E RS

O R I G I N O F R E S E A U R O WA N D C O L U M N N U M B E R S

S T E LL A R F O R M A TE R R A I N FO RMAT


IF003W/2-093942-77


M APPING CAM ERA LENSES

NRO APPROVED FOR




T O P SECRET/H1F003W/2-093942-, 79

L E N S F O C A L L EN G T HRELATIVE APERTURESEN SI T I V I T Y

B O RE S I G H T S TA B I L I TYF I E L D O F V I E W

1 0 . 0 I N C H E S1/2.06 th M A G N I T U D E ST A R S O R B R I G H T E R

2 A R C - S E C I N O P E R A T I O N1 6 B Y 2 5 DE G RE E S

STELLAR SHUTTER

SAFETY SHUTTER

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

E A RT H

S T E L L A R L E N S A N D B A F F L E

RE S E A U PL A T E

FILTER (WR ATTEN 2 1 )

ASP H ER IC SU R FACE

F O C A L L E N G T HREL. APERTURED I S T O R T I O N

STABILITYR E S O L U T I O NF I E LD O F V I E W

12.0 IN.1 /6 , 1 /14100 M I C R O N S M A X R A D I AL2 0 M IC R O N S M A X T A N G E N T I AL2 M I C R O N S I N O P E R A T I O N9 5 L /M M A W A R ( V E M O N 3 4 1 4 F I LM )38 BY 72 DEGREES

15.13-IN.

DIAM ETER

MAPPING


M A P P IN G P R O C ES S

NRO APPROVED FOR




ACQUISITION

DATA EXTRIrly:

n

COLOR SEPARATION

DRAFTING

C O M P I L A T IO N O F M A P D A T A

EXPLOITATION

ESENTATION

•

C O MP U T I N G

I ?°11)

1,

S T E R E O P H O T O G R A P H I C P LO T T I N G

I

G R I D A N D

CONTROL

D A T A P R O C E S S I N GR O D U C T I O

RELIEF

M AP

DET AIL

N A M E S

PROCESS_

P O I N T MA R K I N G

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T O P S E C R E T /HM E T R IC P A N C A M E R AS Y S T E M - A T T IT U D E D E T E R M IN A T IO N

NRO APPROVED FOR




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 co-

ordinates and requires auxiliary data to establish absolute 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 deter-

mine 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 on-

board 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 SV-17 and up superseding the M apping Camera System (M CS)

previously described.

T O P S E C R E T /H2 BIF003W/2-093942-77


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

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S T E L L A R S O L I D S T A T E ( S 3 ) C A M E R A A S S E M B LY

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S T E L L A R C A M E R A D A T A F L O W

T O P S E C R E T /HM E T R IC P A N C A M E R AS Y S T E M --L O C A T IO N D E T E R M IN A T IO N

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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 oscillatorof 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 with 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 non-

gravitational 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.

94 T O P S E C R E T /H BIF003W/2-093942-77


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

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N AV SATS

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SHROUD CON FIGUR ATION

The shroud provides a protective enclosure for the payload on the launch pad and

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during ascent. It is a corrugated monocoque aluminum cylinder 52 ft long and10 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.

1 04

T O P S E C R E T /H BIF003W/2-093942-75


S H R O U D C O N F I G U R A T I O N

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S A T E L L I T E B A S I C A S S E M B L Y S T R U C T U R E




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B O O S T E R A D A P T E R S E C T IO N

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S A T E LL IT E B A S IC A S S E M B LY -A F T S E CT 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 con-

ditions 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 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 load-

ing 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 of12

equally spaced, equally sized bays, each capable of supporting up to500 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 and the M id Section.

T O P S E C R E T /H10 BIF003W/2-093942-77

E Q U I P M E N T S E C T IO NA M / R C M S E C T I O N

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

X I M E S S I M M I S I M U R N I I I P 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 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 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 to

drive the RCS thruster.

Control Requirementseasurement Requirements

For search/surveillance operations

Pitch Roll Yaw Pitch Roll Yaw

Attitude accuracy ( deg) 0.7 0.7 0.64 0.4 0.4 0.5

Rate accuracy (deg/sec) 0.01 4 0.021 0.01 4 0.001 0. 001 0.001

During non-horizontal operations

Attitude accuracy ( deg) 3 1 1Rate accuracy (deg/sec) 0.15 0.15 0.15

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

1 12

T O P S E C R E T /H BIF003W/2-093942-77

1ef




O R B IT A D JU S T A N D R E A C T IO N C O N T R O L

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 of monopropellant hydrazine to generate thrust. For reliability, the systems

are pressure-fed, with the pressurizing gas enclosed in the propellant tank with the hydrazine. This results in declining or

blowdown pressure characteristics; the thrust level of the OAS engine declines from 250 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.

On 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 thepressure 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 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 tank and provide enough ullage

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 540 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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114O P S E C R E T /H

IF003W/2-093942-77

O P S E C R E T /H

ORBIT ADJU ST t REACTION CONTROLJI




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O A S U L L A G E T A N K S ( 2 )® 6 2 " D IA . OR B IT A D J U S T T A N K

OA / R C M J -B OX

10, ORBIT ADJUST ENGINE


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V I EW L O O K IN G F O R W A R D

OAS FILL V A L V E

RCS G AS F I L L VAL VE S (2 )

R C S P R O P E L L A N T F I L L V A LV E

I S O LA T I O N V A L V E S ( 6)

rt R C S G A S /P R O P T A N K (4 )

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NI T RO G E N F I LL VALVES (2)

NI T RO G E N F I LL V A LV E

C A P I LLARY G A LLE RY62" D IA O R BIT AD J U ST TANK

Q U A D PROPELLANT V A L V E

CATALYST B E D

O A S U L L A G E T A N K S ( 2 )

PRIMARYEDUNDANTR C S THRUSTERS

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Li

11 5BIF003VV/2-093942-77


E L E C T R IC A L D IS T R IB U T IO N A N D P O W E R 1 1

Power to operate the Satellite V ehicle is provided by solar arrays deployed from the A ft Section 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 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, 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 circuits add to the reliability.

The power system is capable of providing approximately 1 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 isolate the lifeboat

system and its battery. This assures adeq uate power for the emergency operations. The lifeboat system can be re-

connected 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.

U

T O P S E C R E T /H1 6 BIF003W/2-093942-77

SOLAR ARRAY


ELECTRICAL D ISTRIBU TION POW ER




P O W E R D I S T R I B U T IO NJ -BOX

P A N E L

M A P P I N GE A R C H /CAMERA SURVEILLANCE

P A Y L O A DA Y L OA D

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t IN TER FAC E J - BOXESH AR G EHA RGEHA RGEHA RGE

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BIF003W/2-093942-77 T O P S E C R E T /H 117


T E L EM E T R Y A N D T R A C KIN G

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The SGLS-compatible telemetry subsystem provides PCM real-time data (ascent at48 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 labias error and 60 ft rms maximum noise

error), range rate (0.2 ft/sec maximum la error), and angle-of-arrival (1.0 milli-

radian maximum la bias error and 1.0 milliradian rms maximum noise error).

11 8 T O P S E C R E T /H BIF003W/2-093942-77

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T E L E M E T R Y E T R A C K I N G




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1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 0 1 1 0 1

CI INSTRU MEN TATION J -BOXES (3 )

2 P C M R E M O T E ( 5 )

3 P C M M A S T E R N O . 1

4 P C M M A S T E R N O . 2

3 TAPE RECORDER NO. 1

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T A P E R E C O R D E R

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BIF003W/2-093042-77 1 19

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C O M M A N D f T I M I N G i




T O P S E C R E T /HIF003W/2-093942-77 1 2 1

(EXCEPT ITEM 6)

D A T A I N T ER FA C E U N I T

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, 1 ) E X T E N D E D C O M M A N D S Y S T E M ( E C S )0 3 7 5 M Hz RE CE I V E R ( L I FE B O AT I 1 )

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COMM AND J -BOX TYPE 2

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VCTS RECEIVER NO. 2

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L I FE B O A T II

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.

n




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 OAS engine and the redundant SGLS, 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 keep this emergency mode operating until the vehicle reenters.

ti

T O P S E C R E T /H22 BIF003W/2-093942-77


L I F E B O A T II




RATE GYRO (3)

ELECTRONICS

CD TYPE 40 BATTERY

a_—

46.

O U T B O A R D V IE WFREON GAS

T A N K SN B O A R D V I E W

FILL

V A L V E

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

MAGNETOMETER (3 AXIS)

3 LIFEBOAT 11 J-BOX

4 75 MHz RECEIVER

R E G U L A T O R

THRUSTERS

3 7 5 M H zRECEIVER

ANTENNA

MCS - ELECTRONICS 1

X - Y- Z AX IS-Y-Z AXISM A G NE T O M E T E RA T E G Y RO S

N-S-N

POLARITY SWITCH

BIF003W/2-093942-77

IEGULATOR

41FREON GAS TANKS ( 2 )

THRUSTERS (6)

F IL L V AL V E

T O P S E C R E T /H 1 1 1 1 1 1 1 =

T O P S E C R E T /HH A R D W A R E F LO W

•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.




The SBA piece-parts are subjected to electrical and environmental stress and visual inspection tests to

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

temperature-vacuum and 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. The aft section electronic 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 — Satellite B asic Assembly Contractor (Lockheed)

M WC — M idwest Contractor (M cDonnell Douglas)NEC — Northeast Contractor (Itek)

OPC — Our Philadelphia Contractor (General Electric)

SSC — Sensor Subsystem Contractor (Perkin-Elmer)

124O P S E C R E T /H

IF003W/2-093942-77

B

TO P S E CRE T/H

H A R D W A R E FL O WS HRO UD A C O US TI C TE S TA N D C L E A N I N G I

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TO P S E CRE T/HIF003W 2-093942-77 12

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TOP SECRET/H

H A R D W A R E FL O W




M O D U L E T E S TaAMU

COLLIMATION TEST TRANSPORTER

SHIPPING PREPS

TOP SECRET/HIF003W/2-093942-77