(Vehicle 48 Series With High-Altitude Capability) JUNE 1981 DM/46.pdf · VII Vehicle Azimuth vs....

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DATA BOOK

THE KH-8CAMERA SYSTEM:

DUAL MODE(Vehicle 48 SeriesWith High-Altitude

Capability)

JUNE 1981

TCS-27601 /8172 PagesCopy 1 0 0

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PREFACE

ThisTnis data book has been prepared by the National Reconnaissance Officein cooperation with the National Photographic Interpretation Center, the

Imagery Exploitation Subcommittee of COMIREX,' and the Defense !lapping Agency.• It is intended to serve as a reference book for' imagery analysts and othersassociated with the exploitation community who wish to become familiar withthe Ka-s system and its imagery and who also wish to develop skills in pre- .paring requests for special. acquisitions, taking advantage of such factorsas exposure, look angle, frame length, sun angle, area coverage, etc., tomaximize the utility of the photography.

This book supercedes the data book entitled T'ae KH-8 Camera System (Vehicle 48 Series) (TCS-5677/77 dated February 1977) by pr•!senting newmaterial that describes high-altitude acquisition capabilities (up to 470nm) and Some of the changes in the vehicle that were required to achievetnese capabilities. Basic characteristics of the vehicles flown on

Missions 4348 through 4331 (number of recovers' vehicles, stereo mirrorpositions, roll capabilities, number of film strands and capabilityof using different film types film titling, etc.) remain unchanged.

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TABLE OF CONTENTS

Preface

List of Figures iii

List of Tables iv

PART I: System Description . • OOOO • • 1

Introduction 1Camera System Characteristics 2

Light Path 2Image Motion Compensation (IMC) 2Exposure 4Film Swath Widths 5

Film Characteristics 8Film Load 8Multiple Film Types 8

Film Marking Data 8Modes of Operation 13

Monoscopic Photography 13Stereoscopic Photography 13Lateral Coverage Photography . 13Request for a Specific Mode . .... . • • • • . • . . • 13Operations Schedule 21

Mission Film Index 23Mission Correlation Data 25

PART II: Targeting 33

Mission. Target File 33Target Entries 33Requirement Entries 33Application of the Requirement Constraints 37

Special Operations 59

. Area Requirements 59

Operations Process 62

GLOSSARY ... • • 67

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LIST OFOF FIGURES

Figure PageNo.

31 Effect on Pointing of Subsystem Offset

r 2 Variation in Swath Width. with Altitude and Obliquity Angle . . . . 63 'Nine-inch Film Format 94 Five-inch Film Format 105 Monoscopic Photography 146 Full Stereo Pair 157 Stereo Triplet 168 Half-Stereo Pair 179 Lateral Pair 18

10 Lateral Triplet 1911 ExaMple of Conflicting Mode 2012 Target-to-Vehicle Azimuths 3513 Vehicle Pointing 3914 Vehicle Viewing Limits 4015 Target-to-Vehicle Elevation Bands 4116 Elevation Viewing Limits 4217 Azimuth Viewing Limits 4318 Azimuth and Elevation Viewing Limits 4519 Vehicle/Target Geometry-Sample Pass 1 4620 Vehicle/Target Geometry-Sample Pass 2 4721 Vehicle/Target Geometry-Sample Pass 3 4822 Vehicle/Target Geometry-Sample Pass 4 4923 Vehicle/Target Geometry-Sample Pass 5 5024 Vehicle Azimuth vs. Target Latitude-96.4° Inclination 5225 Vehicle Azimuth vs. Target Latitude-110.5° Inclination 5226 Line of Closest Approach from Vehicle Azimuth 5327 Sun Declination 5428 Northern Hemisphere Sun Angles-Noon 5529 Northern Hemisphere Sun Angles-Noon +2 Hours 56,30 Area Coverage Capability 6031 Target Selection:Functional Flow 6332 Target Coverage 66.33 Multiple Target Framing 66

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LIST OFOF TABLES

Page

TableTableNumber

I Dual-Mode Improvements 1II Optical Properties Summary 5

III KH-8 Dual-Mode Mission Parameter and S ystem Characteristics • • 7IV Available Mode Options 20

Mission Film Index Format 23VI Vehicle Azimuth vs. Target Latitude: Inclination 96.4° . . . . 51

VII Vehicle Azimuth vs. Target Latitude: Inclination 110.5°. . . . 51

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DECLASSIFIED ON:ON: 10 JANUARY 2013PART 1: SYSTEM DESCRIPTION

INTRODUCTION

Tne Kli-8 dual-mode camera system, like its Block 48 camera system prede-

cessors, is a satellite-borne photographic reconnaissance system designed togatner high-resolution photography. The KH-8 originally was designed forpoint target surveillance. The addition of an extended altitude capability.

(EAC) in the dual-mode configuration allows operation at higher altitudes,which results in wider swath coverage at greater ground resolved distances

with search mode requirements.

• Various system improvements and modifications have been incorporated,.effective with Flight Model 52, to achieve this increase in flexibilityand utility for the Kii-8 camera system (see Table I).

TABLE I

DUAL-MODE IMPROVEMENTS

SYSTEM PERFORMANCE

Extended altitude capability (68 to 470 nm)Mlultiple-range film drive speed control (two high, two low)

9a to 120 day lifetimeFocus sensing possible over entire slant rangeExpose ancillary data at all film drive. speedsAdditional smear slits for high modeitigoer thrust SRV -rocket motorsVariable recovery Sequence timers on both recovery vehicles

ACQUISITION CAPABILITY

Increased area coverage at high altitude (17 million square nm potential)Crisis reaction capability.Use of very high resolution filmsIncreased frame potential (to 25,000)Sophisticated target conflicting and selection softwareFlexible modes of operation (i.e., can serve various mission scenarios)

As a consequence of these net' capabilities, a KH-H mission Can now beflown in three different wa ys: (1) an entire mission at low altittides It obtainI. highest quality imagery of techincal intelligence targets: (2)an entiremission at high altitudes - as high as 470 nm - to satisfy a signiiicant

portion of standing search requirements; or (3) a combination of missions,

with hall the filM expended at high or low altitude and returned, and the

remainder expended at the other altitude.

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CAMERA SYSTEM CHARACTERISTICS

The dual-platen camera is a strip camera with several unique featuresthat permit the imaging of targets over a wide range of altitudes, slant

ranges, and exposure conditions. Since the camera system utilizes 9.5-inchwide and 5-inch wide films independently or simultaneously, two differentfilm types may be available at any one time, offering wider latitude inimaging a target.* This freedom of choice is further enhanced by theavailability of independent variable exposure mechanisms provided for each

platen.

LIGHT PATH

Light is gathered from the scene beneath the vehicle and reflected by

a tiltable mirror (the stereo mirror) to a focusing mirror at one end ofthe camera. This mirror concentrates the bundle of light and directs itthrough a correcting lens toward the imaging platens. The resulting focusedray of light is then imaged directly on the 9-inch film platen and, by meansof a narrow reflecting prism, also on the 5-inch film platen. It is thisimaging of a single ray of light on two separate platens that enables thesystem to take simultaneous or independent photography of a single target.

The reflecting prism for the 5-inch platen is below the optical axis

of the 9-inch platen, causing the 5-inch line of sight (LOS) to be directedaft of the 9-inch LOS. The effect of this offset is illustrated in Figure1, which also shows the magnitude of this offset in nautical miles as afunction of slant range.

The stereo mirror can direct the line of sight at right angles to thevehicle motion (at the nadir if no vehicle roll is present) and 8.65 degreesforward and aft. The imaging capabilities realized by this flexibilityare described in the section entitled "Modes of Operation."

IMAGE MOTION COMPENSATION (IMC)

Vehicle velocity, earth rotation, and variations in terrain elevationcombine to produce considerable differential motion between an orbitingvehicle and a scene to be photographed (i.e., images projected on theplatens are moving at different speeds depending on their position alongthe slit). The dualmode camera system employs two means to eliminate thisrelative image motion during photography. First, the stereo mirror isrotated about the center of its supporting yoke to a calculated crab angle,

*For convenience's sake, tlhewider film subsystem is called the 9-inch sub-system through the rest of the manual.

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which reduces cross-track axial image velocity, within the discrete limits F

of the crab settings, to near zero. Selection of the crab angle for eachframe is based on both image velocity vector alignment and pointing con-siderations. Second, the film is driven at a calculated speed that matchesthe in-track axial image velocity for the crabbed system.

Since differences in crab angle between the 9-inch subsystem and the5-inch subsystem are negligible, pointing and IMC paraMeters for a giventarget are calculated for whichever of the two subsystems is the primarycamera for that acquisition and used for both.

The displacement of the lines of sight between the 9-inch and 5-inch,subsystems as shown in Figure 1, require different film-drive speeds ifproper image motion compensation (IMC) is to be achieved for both. Sincethere is only one film drive speed (FDS) memory in the command prOdessor,only one film drive speed may be commanded at any given time. This pre-sents a conflict in cases when the two subsystems are operating simultaneouslywith different FDS , steps required for each The operational softwarechooses which subsystem to optimize in such cases (usually the 9-inch sub-system is preferred), and the other subsystem is then operated at a less-than-optimum FDS, resulting in some minor image degradation (smear). r

Film drive speed varies inversely with vehicle-to-target distance(slant range). Calculations of limiting cases (maximum and minimum speedsin inches/second) show that it is possible to obtain photographs withcorrect film-drive velocities at target ranges from 68 NM to about 470 NM.

EXPOSURE

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In a frame camera, the amount of energy falling on the film is controlledby a combination of the shutter speed (exposure time) and the lens aperture.With a fixed aperture strip camera such as the 101-8, this energy is con-trolled entirely by the slit width.

Exposure for the KH-8 dual-mode system is controlled by positioningmoveable blades in front of each platen which are capable of providing 16slit openings for each subsystem, ranging from 0.0040" to 0.3000". Theratio between successive slit settings is approximately 1.334, and themaximum time needed to change from one slit to an adjacent one is 1.0 second.

The slits are also used to place additional information on the filmsto aid in post-flight analyses. Light-emitting diodes (LEDs), controlledby the camera electronics assembly modules, produce data tracks (vehicleclock information) in both subsystems. Interframe marks are producedalong the edge of the film by apertures illuminated by incandescent lampsthat are also controlled by the camera electronics assembly. The slitblades, in addition to controlling exposure levels, generate fiducial lines

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to delineate the main scene and provide the smear slits that create

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FILM SWATH WIDTHS

Figure 2 graphs the approximate swath widths for each subsystem overa range of altitudes, obliquity angles, and stereo angles. Optical pro-perties of the KR-8 dual-mode camera system are summarized in Table II.General system characteristics are summarized in Table III.

TABLE II

OPTICAL PROPERTIES SUMMARY

Effective focal length

Aperture diameter (primary mirror)

f number (9-inch system)

Type

Configuration

Semi-field angle: 9-inch5-inch

175 inches

43.5 inches

4.02 nominal

Aspheric reflector with five-element Ross corrector

Optical path folded by stereomirror; optical axis passesthrough stereo mirror

1.45 degrees0.74 degree

Stereo angle of line-of-sight,with respect to nadir (deg) -8.65, 0, +8.65

Crab-angle range (deg) -3.85 to +3.85

Peak static resolution, Vehicle51 (geometric mean)

liginesimm*

Based on 2:1 contrast at film plane,.threshold modulation

= 0.0170 + 2.07 X 10 -7 v 2 for SO-409 at nominal exposure.

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TABLE IIIr-

Kh-8 DUAL-MODE UISSION PARAMETER AND SYSTEM CHARACTERISTICS

r-

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ITEM

Target ranges

Theoretical orbit inclination

Mission duration

Direction of travel duringphotography

Film footages (feet)

9-inch

5-inch

Potential number of frames

CHARACTERISTIC

68 to 470 nm

82 to 120 degree:: (perigeeanywhere in orbit)

20 to 120 days

North or south (south descending)

11,500 (13,500 max. with1.2-mil base)

2,800 (3,600 max. with1.2-mil base)

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No. of exposure slits (widths ininches)

Best resolution (GRD)

Nominal resolution

Seta angle range

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4,600 (6,100 max.)

16 (0.004 to 0.300)

•±40 degrees

403 to 780 manometers

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FILM LOAD

-44,P4DEWHET--FILM CHARACTERISTICS

The KR-8 dual-mode 9 x 5 system is capable of using both black-and-white and color films with thicknesses varying from 0.0015-inch (1.5 mils)to 0.0039-inch (3.9 mils) on either film supply. Under certain conditionsit may be possible to accommodate thinner films, but thicker films, becauseof limitations imposed by mechanical clearances in some locations,are to beavoided. Film footages are shown in Table III.

MULTIPLE FILM TYPES

Color film provides a definite spectral information increase overblack-and-white (B&W) film even though the image quality (tribar resolution)may not be as good. Similarly, color infrared film has the unique capa-bility to record an image which is interpretable in terms of the healthof agricultural crops and the presence of camouflage materials. The dualplatens on this system make it possible to obtain both high resolution B&Wimagery and color or color infrared imagery simultaneously over a singletarget or, as a means of ensuring maximum resolution, simultaneous coverageusing two different, high-resolution, black-and-white films.

FILM MARKING DATA

Illustrations of the 9 and 5-inch films are shown in Figures 3 and 4.Descriptions of the major elements follow.

Fiducial Lines

The fiducial lines on both films are narrow bands of high exposure ateach edge of the main scene and mark the limits of the imagery.

Data Tracks

There are two pairs of data tracks on each exposure mechanism, onedesigned for low mode and one for high mode. For either mode the two datatracks encoded on the film provide timing information in the form of lightpulse exposures represeviting the vehicle timing signals. The two tracks,A and a, are identical and represent timing signal A inverted and logicallysummed with timing signal B. The data tracks are imaged at 500 pulses persecond with an octal time word encoded every 0.2 seconds. The LED lampsthat imprint the data tracks are offset along the axis of the film on eitherside of each slit centerline as a means of measuring film speed. The rela-tive data lamp positions are the same for both the . 9 and 5 slit mechanisms.

and The following table shows the data lame positions nd the effective aperturesize at the platen: •

Hata lamp) Position withrespect to slit t

I Distance from slit talong film axis (inches)

Effective aperture sizeat the platen (inches)

Outside 0.05 after 0.001 x 0.005Low mode AB Inside 0.05 ahead 0.001 x 0.005

Outside 0.15 ahead 0.0005 x 0.005High mode 2

Inside 0.15 after 0.0005 x 0.005

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Film Can Labeling

The control number on the shipping labels will be similar to thosepreviously used. Typical examples follow:

M481001

-

"M"for main record (9 inch)

"481" for. Mission 4348-1

"001" for can number

C481001

- "C" for 5-inch record

Color coding on the label will be the same as previously used:

Original negative (ON) - GreenDuplicate negative (DN) - YellowDuplicate positive (DP) - BlueDP File Copy - RedColor original positive (OP) - OrangeColor DP - Green

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MODES OFOF OPERATION

The KH-8 system is capable of performing three basic modes of photo-graphy; monoscopic, stereoscopic, and lateral coverage. These three modes,with the variations described below, are available for almost every photo-graphic opportunity. The mode required for a particular acquisition may bespecified by the user. Each of the modes and how to state the requirement forthem is discussed below.

MONOSCOPIC PHOTOGRAPHY

As stated earlier, there are three stereo mirror pointing positions;forward 8.65°, vertical, and aft 8.65°. Monoscopic photography is obtainedby imaging a target from only one of these mirror positions on a given pass(Fig. 5). The resulting frame can vary in length from only a few inchesup to several feet.

STEREOSCOPIC PHOTOGRAPHY

Single-pass stereo photography can be obtained in three ways. The fullstereo pair consists of one photo taken with the stereo mirror in the for-ward position and one with the mirror aft (Fig. 6). The convergence angleis approximately 17.3 degrees. A stereo triplet consists of a series ofthree frames, one from each of the mirror positions (Fig. 7). The stereohalf pair is made up of a vertical acquisition and either a forward or aftframe (Fig. 8). The stereo angle in these latter two modes is 8.65 degrees.

LATERAL COVERAGE PHOTOGRAPHY

Lateral coverage photography is a combination of the mono and stereomodes and is used to provide greater area coverage around a point on theground. Two options are available. A lateral pair consists of two framestaken in the forward and aft mirror positions with a vehicle roll betweenacquisitions. The resultant pair overlap approximately 15 percent cross-track, and the target is centered in the overlap (within system limits). Alateral triplet consists of three frames laid cross-track, one from eachmirror position with a vehicle roll between each acquisition. Examples oflateral pairs and triplets are shown in Figures 9 and 10.

REQUEST FOR A SPECIFIC MODE

The user may request a mandatory mode or a set of acceptable modesand their preferred order. Table IV shows the mode options that will beavailable for operations.

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TABLE IVIV

AVAILABLE MODE OPTIONS

Any monoForward mono mandatoryVertical mono mandatoryAft mono mandatoryStereo triplet mandatoryStereo pair mandatoryStereo pair (preferred over) any monoHalf stereo mandatoryHalf stereo (preferred over) any monoStereo pair (preferred over) half stereoStereo pair (over) half stereo (over) any monoStereo triplet (over) stereo pair (over) half stereoStereo triplet (over) stereo pair (over) half stereo

(over) any monoLateral triplet mandatoryLateral pair mandatory

A typical example of how the modein Figure 11. The example is intendedcamera system affect requested modes.meter is the time required to flip theanother.

preference logic operates is shownto show how fixed parameters of theIn this example the limiting pars—stereo mirror from one position to

Available servo time is Ti T2 (Time from turning camera oft afteracquiring Target A to turning camera on to acquire Target B).

Roll time from A to B (for this example) is less than T i 12.Mirror flip time full stereo (for this example) is greater than T1T2.Mirror flip time half stereo or mono (for this example) is less than Ti T2.

FIGURE 11. EXAMPLE OF CONFLICTING MODE

Handle viaTALENT•KEYHOLEChannelsTCS-27601181

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40P-13€43441E-T--


As shown, the time to alter the vehicle pointing in roll is within theservo time available between the off-time of the frame of Target A to the

on-time of the frame of Target B. The time to flip the stereo mirror be-

tween extreme positions (aft to forward) is greater than the available time.The time to flip between adjacent positions (aft to vertical), however, isless than the available tine, T1 T2. This conflict in timing means that arequest that includes both an aft frame of Target A and a forward frame ofTarget B cannot be achieved. Hence, if both targets are specified "stereomandatory," only one would be photographed in a single pass. If eitherwas "stereo mandatory" and the other was "stereo preferred but mono acce pt-able," then the photography would consist of a stereo pair of the first anda mono strip of the other.

OPERATIONS SCHEDULE

Pre-Flight

The XH-8 dual-mode reconnaissance system is maintained in a launch-on-demand status and does not have preestablished launch dates as did mostprevious Kii-8 vehicles. Prefliglit activities of importance to users remainessentially the same, however.

Normally, the launch processing timelines are as follows:

1.-80: DeadlineDeadline for users to submit any requirements to ICRS thatnecessitate the use of "exotic"films or multiple coverage

requirements for different films.

L-60:1CRS submits final film load requirements for film spool design.

ICRS submits final mission profile (altitude selection). Users shouldsubmit any requirements for coverage that may affect orbit selectionwell before this date.

Handle viaTALENT-KEYHOLEChannelsTCS- 27601181

21

-110P-SteltET-


TCS-27601181

22-T.Peeeitef-

RO APPROVED FOR RELEASEECLASSIFIED BY: C/IARTECLASSIFIED ON: 10 JANUARY 2013 -10PINECRET-

On-Orbit

The 101-8safellie is loaded with a set of commands just prior to eachrevolution of photography. This is to take maximum advantage of the latest

available predicted weather. New target requirements, or changes to exist-ing ones, can be accepted at the KH-8 operations center as late as 90minutes prior to the start of imaging operations on a given revolution.

11 APPROVED FOR RELEASELASSIFIED BY: C/IARTLASSIFIED ON: 10 JANUARY 2013 ileenfr-

MISSION FILM INDEX (MFI)

The MFI, a sample copy of which is shown as Table V, is a computerlisting of mission coverage by rev, and identifies specifically how theframes from each system correlate. A sample format of the MFI is explainedbelow:

TABLE V.

MISSION FILM INDEX FORMAT Mining')

M Cam. C Cunt Printing Dats• IA Frames C Frames COO M Peon* C Footage ChimpsN.. OP ON No. DP ON DOMMYY Arm RS,/ From-To From-To E0•1F-CC Photo Ship Photo SNP •

M41111101 LO•LD C481001 LI•LD 040276 A 0001 00014001 50014001 XXX.XX XXX.XX XXXXX XXX.XXM4141001 010275 A 0001 900141002 NF 23.01M4811101 0481001 010278 A 0001 60014001 NFCC 10.00M4it 10112 0481001 010276 A 0001 90034004 50024403 11.65 3449 4.72 14.72

Table Headingor Entry Explanation

M Cont U Main control number

M481001 "M" for main record (9-inch),"481" for Mission 4348-1,"001" for can number. If thecontrol number is followed bya "C" or "I", the associatedframes ("M Frames" column) arecolor or IR film.

Printing Printing level for the 9-ifichDP/DN DP and DN. A medium copy will

alWays be shipped. If anyadditional print levels areproduced, they will be reflect-ed in this column.

L - LightD Dark

•

C Cont

C481001

PrintingDP/DN


Tr.S-27601/81

Companion control nuMber.

"C" for companion record(5-inch), "481" for Mission4348-1, "001" for can number.If the control number is followedby a "C" or "I", the associatedframes ("C Frames" column) arecolor or IR film.Printing level for the 5-inchDP and DN.

23

91110fertET"

IIINRO APPROVED FOR RELEASE __......4DECLASSIFIED BY: C/IARTDECLASSIFIED ON: 10 JANUARY 2013 fieeltEC"

Explanation

GMT date of photography

Geographic area

Revolution number

Frame numbers for the 9-inchfilm. Frame numbers are se-quential within a rev andcycle back to 9001 at thebeginning of each rev.

Same for the 5-inch film.

ED - Edited; NF - Noforn;CC - Cloud Cover.

Film footage for the 9-inchfilm for each set of framesand the cumulative film foot-age by rev.

Same for the 5-inch film.

Two versions of the MFI areproduced - preliminary, and -final. This column flags any •changes between these two edi-tions.

Table Headingor Entry

Date

Area

Rev

M framesFrom - To

C FramesFrom - To

CodeED-NF-CC

M FootagePhoto Ship

C FootagePhoto Ship

Changes

Handle viaTALENT-KEYHOLEChannelsMS-27601181

24

r 25Handle via

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TCS-27601181

IC SSIFIED BY: C/IARTPPROVED FOR RELEASEC SSIFIED ON 10 JANUARY 2013 --TOP-8661461—

FI MISSION CORRELATION DATA (MCD)

The MCD is a computer listing of the parameters associated with eachphotograph. A sample MCD entry is shown on the pages that follow, accomrpanyed by a description of each entry. Note that KEY numbers (first column)in the 40's are heading or title lines, and KEY numbers in the 60's are datalines. Note also that not all title lines are described here; the readeris directed to the MCD glossary for a complete description.

OVED FOR RELEASE

i

SSIFIED BY: C/IARTSSIFIED ON: 10 JANUARY 2013

Typic

41 REV ACC T T1T2 MR P R OLL rm0-CRAB-COMP S F SR CONE At61 530 9007 0 5.2 V 0 24,85 1,672 1,704 3 0 26,521,43 REV ACC IAT*Ii*LoNG tATIEZIRLONG LAT*W*LONG43 53 9007 54,93m 39,85E 55.4AN 40.46E 55,75N 40,68144 ',WANT RT0SEs-TAW P ITCH Anti.. THEW' RENO ERROR•'e4 .00011 .013F ..000045 NPA VFL-X65 1.1 .3.58450666 PROGRAmmEn 10 072016601 *47 TN FRAME 10 M LAT LONG n T-ALT VFC RES FM AM :A7 007016601 3 59,70m 40,57.E 1008. 1.20,1 41.6 g o 40A7 02z016604 0 si s g nm 39.67E 1000. 1.2445 53.2 PO 3567 077016601 r 59,70 4, 40,12E 1000. • 1.2223 34.1 A5 4067 121016601 0 95.40v 40,57E 1000. 1.1992 50. - 5 85 4567 6167014602 n 55,70m 39,67E 1000. 1.23149 43.6 A0 4047 112016401 0 S5,50m 40.12E 1000. 1.2164 34.9 R5 4567 037014601 55,104 40,12E 1000. 1.22R1 34.1 AO 4542 SYSTIME 0LK TIME LAT-P.AnTR-LONG HEIGHT PIER VEL62 31774,24 p957,7231 57 5,17P 5344,24E 492,044 P41131,1962 31774,84 0057 2723457 3.14 N 4343.00E 452.044 24341.1462 51779,46 0057272%7 57 1,101 3341.77E 452.053 24331,1062 31776,06 005727242 5659,074 3340.54E 452.05E 24331,0562 31774.46 0.05727245 5657,03N 3339.31F 492.06A '4331.0142 '31777.26 1097272F0:5454.9404 3 33A.08E 492.064 24330.9662 '1777,616 no1 4 717 74 5692,9 4 4 1 136. P 5F 44,.067 -?41430,9262 31778,44 0057?7294 5650,924 3335.63E 492.071 24330A742 31771,04 A05727261 5644,84N 3334.40E 44p .074 24430,834,2 31779.44 0057272,23 5647 . 5 3N 3333.59E 452.077 24330,80

Handle uiaTALENT-KEYHOLEChannelsMS-27601181

, .•

NRO APPROVED FOR RELEASEDECLASSIFIMINAWARTDECLASSIFIED ON: 10 JANUARY 2013

MCD Entry

3 VF SS F-USE* INTRK - RC - y TRK ALPHA-90-BETA 213-FRAME-I111.2220 „oncl .53 '914174, 248050. .627 .541 5223MAY809096

LAT*X*LONG *V**Y* *V**U* *V**W* *Y**X* *Y**2* F-AREA FLMRS5.65N 39.64EAY PITCH19 .0465VEL-Y-.126590

21.10 14.72 15.31 14.72 15.31 611.3 00000nRil nEP FRROR-YAW PITCH ROLL.0000 -.0125 .0000

VE1-1 SLR.014354 513.500

4 TK -n- XTK CLN TNT MAR CMD-SLIT-COMP HR GM LR P2 P3 P4 P5 P6 P7 P81 A .0 1 .5 5R. FFF600 .00620 .00540 14. 11. 8. 99 99 99 99 99 99 991 2 .2 26.1 16. Onno17 .00620 .00540 14. 11. 8. 99 99 99 . 9999 99 997.8 11.8 99, FFFFFF .00620 .00540 14. 11. 8. 99 99 99 99 99 99 993,4 -2.1 25. CEA000 .00620 .00490 14. 11. 8. 99 99 99 99 99 99 992,4 22.4 41. 0006FF .00620 00540 14. 11. 8. 99 99 99 99 99 99 99

-1.8 8.2 P8. 08ARCC .00620 ,00540 14. 11. 8. 99 99 99 99 99 99 9917,3 15.4 37, 333111 .00620 .004140 14. 11. 8. 99 99 99 94 99 99 agv/H VFH AZM FLTPTH LAT -PR RAY -LONG AZM-PR RAY-SLR EL-SUNA7R

.nOR q 1/6.209 .7358 5550.54N 4015.55E 291.709 5 13.55 59 .5 169.4

.8089 194.194 .2356 5 54A.60N 4014.02E 291.686 513,56 54.5 169.4

.n089 196.179 ,9354 5546.64N 4 012.99E 291.664 513.56 54.5 169.3

.0089 196.164 .2352 9594467N 4010.96E 291.692 513.56 54.6 169.3

.0069 196.149 .9350 5549.70N 4n 9.44E 291.621 513. 57 59.6 169.2

.n189 196.133 .7349 9540,748! 41 7.91E 291.599 513. 57 59.6 169.2

.n089 194.118 ,9‘47 55 3A.77N 4n 6.39E 291.578 513.5A 54 ..6 169.201089 196,104 ,2345 5536.80v 4n 4.88E 291.556 513.58 54.7 169.1.n0R9 196.189 .9343 5534,P4N 4n 3,36E 291.535 513.54 54.7 169.1.n0R9 1 96.079 .9342 5533.52N 4n 2,35E 291.520 513.59 54.7 169,0

I I D ON: 10 JANUARY 2013V-.

Explanation ofof Entrionlina 41/81

KEY HEAUEK DESCRIPTION

61 41 CAmERA LVENT DATA LI14EREv hr!► NU.%.nER(40 HEAwER) ASCENDING UK 0ESCEUDING FLAG 10EWTLFIE,. elf A ')R 1).(A0 HLAwcR) STPANu OF FIL!.: USED (9 Ok !))ACC FRAME ACCESSLGI pate. 0ER. STARTS AT 1 ,4T :•ACh

dta ►. OPLRATivkAL FiJk‘,IEJT FILM TYPE USL ► Fuk Th1 I7,LATIFT1-';

►t ►i1C6.E COoSTA•ls DIbVLAYT1T2 uURST TINErdt I.:It/Rol • • 0S1 %J "1

uVCRLAP FkAA L P$JICATOR IF Aia ?ART LS :0,LRE1 fly

OTHER FRAME.— 0 = OVERLAPPED. 1 = fioT 4vEALAPDEDROLL ROLL ANGLE. .4)(64TIZEDCm0..CRAu CCMMANOLD CRAB ANGLE—CJMP COMPUTEL. CRAB ANGLE5 SLIT i.AMBER. COASANDEDF FLAG uF SLIT OAS TYPESb PLANNED SLIT BIAS OF FRANCCONE AN6 CONE ANGLE. GRANTIZEDVF FILM SPEED, ..ituAwTIZEDSS EFFECTIVE SHUTTER SPEEDF—USED LENGTH uF FRAME. COMPUTEDINTRK—SC SCALE FACTOR AT INTRACK AZI PNTH = 0,DEG—XTRK SCALE FACTOR AT cROSSTRACK AaAUTH = 90 DEGALPHA '9(i SKEW ANGLE . WHEN ALPHA = 90 Di.G.•BETA SKEW ANuLE WHEN BETA = 9U OES.kii-FRA•E—[U 213 DEFINED FRAME ID

FLIGHT NU4bERDAYMONTH.YEARSTRAND INDICATOR (5 Ok 9)FRAMc:NUMuER RECTO-ES TO I AT MI Gi.!T EACH DAY

AcileviaLENT-KEYHOLE

27wmels7 ZWMAU

40fLOGGINIFF

NRO -APPROVED FOR RELEASE -DECLASSIFIED BY: C/IARTDECLASSIFIED ON 10 JANUARY 2013

COLUMN FORMAT

2-3•8 NN4L

9 A

UNITS

4.0.N.D.

11 M.D.

to t

rN% Moto.

N.:.

! . N:4,,N1 SEC.18•P?i...4 A '4•:•

:4.7)•GO ..".

28•3335•4042•"4749•505253-565b-6466-7274— S082•80

96-102104•110112•118120-132120-121122-123124-426127•126129130-132

NMN.NNNN.NNNVN.NNMNNNNNeNNN.MNNNWN.t UINNNN.NNNNNN.WNNNNNNN.NNNNNN.fiNN.HNNNNN.NNN

NNNNAAAMN

NUN

DEG.DEG.

.DEG.N•DiN.D.LOG BASE0EG.IN/SEC.SEC.FT.N.D.N.D.DEG.DEG.

N.D.N.D.N.D.N.D.N.D.N.D.

10

A,NANA$4m.:Y'


t'4

Explant

42 SYSITME CLK TTMF LAT-NAnIR nLONG HEIGHT INER V62 31788,66 0057-97141 5616.20N 1315.10E 442.121► 24130.62 317o9,26 105797349 5619,2=4 3313491E 452.133 24330.,62 51789,86 0057,7347 5612,21M 3312473E 452.136 2414.62 11790,46 0057,73=2 5610,17N 3311454E 452,130 24329,62 31791,06 005727355 56 8,13N 3310.35E 452.143 24329.62 11791,g6 005727300 56 6,09N 33 9.17E 452.144 24329,62 31792,26 305727363 56 9,0=N 33 7.99E 452.149 24323.62 11792,44 005727346 56 2,01N 33 6.81E 24329,62 11793,96 305'727371 5559,97N '.63F 452.156 24129,62 31794,06 305727374 5557,95N 33 4.46E 952.159 24329,62 31794,26 005727375 5557,2'%N 33 4407E 452.160 24329,

SNO REV HEADER DE SCRIPT ION3es 62 42 CAMERA EPHEMERIS AND PO370 SYSTIME SISTER TINE AT START OF

IN INCREMENTS OF 044 SE372 CLK TIME VEHICLE CLOCK TINE IN 4373 IN INCREMENTS OF 3 OCTA374 LAT-NADIR GEODETIC LATITUDE OF V E375 -LONG GEODETIC LONGITUDE _OF

ftkItiE376 HEIGHT 'ALTITUDE OF317 INER VEL INERTIAL VELOCITY OF SE318 VIH VEHICLE INERTIAL VELOC1

•

379 VEH AZN FLIGHT PATH ...AZIMUTH OF380 FLIP% V EHICLE FLIGHT PATH ANS3e1 0112E11111_ GEODETIC LATI TUDE OF PR382 -LONG

-•__ _•.7-7.GEODETIC LONGITUDE OVP

383 4n-PR _ • -__ S TT PICEIVCAZINIO:TH.384 ON THE LOCAL HORIZONTAL385 -SLR SL ANT RANGE OF PRINCIPE!386 EL-SUN SUN ELEVATION AT PRINCI387 -A2m SUN AZIMUTH Al Nuncios•

Handle viaTALENT-KEYHOLEChannelsTCS-27601181

PPROVED FOR RELEASE/TART

IF : 10 JANUARY 2013

on of Entries-Line 42/62

V/H..n089.0059.0089.0089

5 .0089.0089.0089

2 .00897 .00893 .0089

.0089

VEH A2M195.1254195.640195.825195,811195.797195.782195,768195.754/95.740195.725195,721

FLTPTH.2314.2312.2310.2308.2306.2304.9303.P301.2299.2297.2296

LAT-PR5615.40N5613.44N5611.48N56 9.53N56 7.56N56 5.60N56 3.64N56 1.68N45550.72N4557.76N5557411N

4ITIONIN6 DATA

6HI6H RES, .10NDSZ1TAL AT START OF

.:, CLOCK STEFSrjk;dICLE NADIR

1H!CLE NADIR

HIGH RES.

JULE!Y DIVIDED 811 HEIGHT

sum RAY _ RAY

PROJECTION OF ._ INE PRINCIPAL RAY

RAY-LONG AZM•PR RAY•OLR4033.61E 273,247 521,364032,04E 273,224 521.364n30.48E 273.202 521.374028.92E -273479 521,374027,36E 273.157 521,374025,80E 273,135 521,384024.25E473.112 521,384022.70E 273,090 521,344021.15E 273.068 521.394019,60E 273.046 521,404019.09E 273.038 521.40

COLUMN

FORMAT

2-3

NN9-16

NWINNANN

18-26 ~MINN

28-35 UNHAND311 40_ _ NPIONNADMO48-54 NNNANN

WINIMAY6S-69 .NNNN-

79-85 NN.ANNNNIONAIND_

96-104 NNNNN.NNO-106-112 NNMANM

EL-SUN-62M54.1 170,454,1 170,154,1 170,054,2 170,054,2 169,954,2 169,954,3 169,854,3 169,854,3 169,754,4 169,754,4 16%7

UNITS

N.D.SEC.

.2 SEC.

E6, MIN0E6, MIN •

:JELISECA_RAO/SECA

E6.0E6.DES.s RIA.

E6. 11 MINE6.

RAY --.1.10=120 YYYM.MY 141.1a.RAY INTERSECTION WITH THE 6ECID 122-126 UNA 0E6.

RAT INTERSECTION WITH THE 6(010 I24•132 0E6.

28

29


Exposition of Eosin►Lin.43113

KEY HEAUEK

OESCRIPTIoN

03

43

CAvERA rRi1e.E COANEWar .0:0%ALIESRtV

KIN ICJ !it,,LP

(Nu hEm.;00

STR ANQ uErl (5 On 9)ACC

FRAtiE ALCESSAC,N LITARTS AT 1 car'.E.:X.LA1*O*

LATITja. OF C.:M.0i ULONG

LONWLAX OF CO.CiEPLMT*Z* LATITUDL OF CORNER ZLONG LONGITULJE OF ORkER ZLAT*** LATITUDQOF CORNER WLONG LOPJGITUL'E OF CORNER *LAT*x* LATITUOg. OF 4;ORNLR XLONG LONGITUuE OF CORNER Xwv**Y* OISTANCt: FROM V 10 Y*V**u* UISTANCL FROM V TO U*V**** uISTANCE•FROA V TO w*Y**x* UISTANCt.. FKO.4 Y TO Xwy**,4* DISTANCE FROM Y TO 2F-AREA FRAME AKEA ENCLOSED 6YF FILM DRIVE SPEED REGULACU NOT wIidiM HARO:ARE CAPA0IL TAKE-UP MOVLNENT DURING HIGH RLSOLUTION PHOTOGRAPHYM STEREO AIRROR MOVEMENT DURING, HIGH RESOLUTION PHOTOC

CRAB ERkOR REaUIkE0 eY HULL uOINT LOCK-UPS SLIT DID NOT ACHIEVE REQUIRE., ,IuTh

Handle viaTALENT-KEYHOLEChannel*TCS-27601181

10 JANUARY 2013

COLUMN FORMAT UNITS

2-3 is1•1•5-8 Pi', "I •10 '1 • .) •11-13 .1•1-1•lo-21 1:14.:4419 DES.23-29 1 1NW Mt r) OVA •32-37 MN.NND DEG.39-45 NNN NND DEG.48-53 NN.NNO . DEG.55-61 NMI NND DEG.64-69 NN.NND DEG.71-77 • /INN. NND DEG.80 ,-05 NNN • NN99-93 MI NN N.'AI97-101 NN.NN N•MI.105-109 NN.NN NI • MI it113-117 ttN.NN N120-125 NNNNN.N (N.MI. )2127 1, 1/0128 N 1/0129 N 1/0130 N lin131 t4 1/0

••4 ...A' •


47

6757b767!37A767476767

IN FRAME TO m I AT

4 9701 6415 0 5i,90m

12/016814 3 53,901

117016419 n 53,90N

1szo1615 n 53.70 m

16201641 9C 53,70N

157016814 n 53.70 N

012016820 n 53.50m

092016419 0 53,50u

052016815 O 54,10N

087016814 C 54,10r

LONG28.42E27.97E27,52E28.42E

7.97E:27,52E24,42E27,97E28,42E27.97E

0 T-ALT1000.1000.1000.1000.1000.1000.1000.1000.1000.1000.

VFC1.28901.27531.2604109151.27791.2631 .1.293q1.28041.28651.27PA

Explanation of

RFS FW A4 '40.4 90 30 24,33.1 95 55 19.152.4 99 3545.7 40 3032.3 95 3045.6 95 2553.1 90 3032.8 95 3534.4 90 30 37',7!.34.1 95 35 3 --I

r.-..pf:A..-ezi453 61 47 TARGETS IN _FRAME DATA .451 • Ti FOR INTtOSECTIN6 TARGET, OTHEWi...452 IN F9AME 10 TARGET IN FRAME IDENTIFIER'451

4____ . _~. PHOTOGRAPHIC COVERAGE OF TARGET

454 0 11 OVERLAP N A NO OVER45! LAT GEODETIC LATITUDE OF TARGET wN456 LONALONGITUDE OF TARGET SE OR W IN

461-• ---6--- TARGET DIAMETER CODE •458 T ALT TARGET ALTITUDE459 ire. . • --to piiiiiTo FILM SPEED - ---460 RES COMPUTED RESOLUTION - BASED ON 461 Fk FORECASTED WEATHER462 Ah ASSESSED WEATHER463 INTR-0 1NIPACK DISTANCE ON FILM FRCM 0464 __ TIMBJ TO CENTER OF TARGET465 -4111 • CROSBYNTUT6ISTANCE ON FILM FRO466 OF TARGET-41T- CLN FOR POINT T ROETS PERCENTAG PR

46e FOR CELL TARGETS THE PERCENT ARE469 -------iiit- PERCENTAGE PROBABILITY POINT TAR410 MAR- PERCENTAGE PROBABILITY POINT TAR411 - . -----Thriliiii HEXA-DECIMAL MASK OF THOSE 3113412 SEEN. ONE CHARACTER PER COLUMN

-NIT C40- oNNE LT T 0 N474 -COMP COmPUTED SLIT WIDTH - DOES NOT.04 SNOW OR REOUIREMENi IIASE5--416 HA HIGHEST REFLECTANCE OF . TARGET477 501 GEOMETRIC NEANOFLECTANCE OF T478 LR LOWEST REFLECTANCE OF TARGET479 P2 PROBABILITY OF ACHIEVING.REGQI480 P3 PROBABILITY OF ACHIEVING REQUIR481 P4 PROBABILITY OF KNIEVINGREDUIR

REV HEADER DESCRIPTION

482 PS_483 P6484 P7485 Pat

Handle viaTALENT-KEYHOLE Channels7CS-276011111

PROBABILITY OF ACHIEVING REOUIRPROBABILITY OF ACHIEVING REQUIRPROBABILITY OF ACHIEVING REOU•RPROBABILITY oF oCKWING REQUIR

pc•GM LR P2 PSP3 P4

DFCORRELERte'siY: C/IIART

SIFIED ON: 10 JANUARY 2013tries-Line 47/67

K•0•XTM CLN

3 50..5 13.6 99..8 27.0 12.

o6 29.o9 11.1 99e.1 24.6 113,

oR So.0 8.6 29..0 2.6 12..2 16.1 3.3o

INT MARFFF000FFFFFF000007FF0000FFFFFF000OFFE00000esseec111000331111

CMD-SLIT-COMP HR.00620.00620.00620.00620.00620.00620.00620.00620.00620.0062 0

P7 P899 99 99 99 9999 99 99 99 9999 99 99 99 9999 99 99 99 9999 99 99 99 9999 99 99 99 9999 99 99 99 9999 99 q9 99 9999 99 99 99 9999 99 99 99 99

.00540 14. 11. 8. 99 99

.00540 14. 11. 8. 99 99

.00540 14. 11. 8. 99 99.005840 14. 11. 8. 99 99.00540 14. 11. 8• 99 99.00540.714. 8. 99 99.00540 14. 11. 8. 99 99'400540'14. 11. 8. 99 99.00540114. 11. 8. 99 99.00540 14. 11. 8. 99 99

COLIUMN2-3 _61•16-----10

FORMATRR_A

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JPOP-9601461—

PART H: TARGETING

MISSION TARGET FILE

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The target file for KH-8 missions is made up of target entries, whichdescribe the physical properties of the targets, and requirement entries,which describe the reason for photography, the required conditions of photo-graphy, and the worth of the target image under those conditions. Eachtarget is limited to a maximum of 10 requirements; the total file is con-strained to 32,767 targets and 65,535 requirements.

TARGET ENTRIES

The target entry consists of its COHIREX identification (ID) andseven descriptors:

Target location (latitude, longitude)Country codeDiameterTarget, location uncertaintyElevation above mean sea levelHigh, mean, low reflectanceNational Tasking Plan code.

The ID and country code are used for bookkeeping and reporting; loca-tion and elevation are used to calculate vehicle pointing; diameter andlocation uncertainty are used to determine frame length; and, finally, re-flectance data are required in determining the resolution values used in thetarget weighting and selection process. National Tasking Plan (NTP) codeand country code (CC) are used to determine National Imagery InterpretabilityRating Scale (NIIRS) set.

Although the community (ICRS) assigns the target parameters, it isworth the time of the individual user to evaluate them in terms of his orher needs. If repeated coverage of a target demonstrates a consistent 'bias or error, it is probably due to a problem in one or more of the targetparameters. A typical example is where the target complex is centered inthe frame but the object of interest is consistently in the camera start-uptransient. This situation indicates a problem with the target diameter ormay indicate that a change in the aiming point coordinates or establishmentof a new target is required to ensure desired coverage is obtained.

REQUIREMENT ENTRIES

Requirement entries are supplied by both the ICRS and the individualuser. Although the user is obviously most concerned with the photographicconditions that must be specified, the effects of the ICRS-specified itemscannot be ignored.

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ICRS-Specified Requirement Parameters

The dominant property of a requirement is its value. ICIS specifiesthis value on the basis of its worth to the entire user community. Theparameters used are priority and shade. The priority range is from zero(highest) to nine. After priority is set, shade provides a means of discrim-inating between requirements of the same priority.

Another ICRS-specified term that can significantly affect photographiccollection is the probability objective. This is the probability that atarget will be imaged to a certain level of satisfaction.

The remaining ICRS-specified items are: date of last confirmed coveragethat satisfied requirement, requirement type, and problem set identifier.

User-Specified Requirement Parameters

The individual user may specify a number of conditions required of theimagery, so as to maximize its utility with respect to such factors as lookangle (both vertical and horizontal), sun elevation and azimuth, etc. Withthe exceptions of mode and resolution, these parameters are optional, andif not specified, no restrictions are imposed. The mode and resolutionlimits will be set by ICRS if not supplied by the user.

Target-to-Vehicle Elevation

Target-to-vehicle elevation is the vehicle's location as seenfrom the target and is the vertical angle measured in degrees from thetarget's horizon to the vehicle. Two limits must be specified: an upperelevation and a lower elevation. These limits describe two concentriccones with their common vertexes at the target. If imagery is to satisfythe specified requirement, the vehicle must be in the volume between thetwo cones at the time of the photography.

Target-to-Vehicle Azimuth

This requirement is the horizontal angle in degrees measured atthe target from true north to the vehicle. The azimuth constraint consistsof an initial and a final limit which together define a sector of a circlecentered on the target (Figure 12). The sector is the area clockwise fromthe initial to final limit. By specifying such limits, the user is statingthat photography collected only from within this sector will meet viewingrequirements.

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FIGURE 12. TARGET-TO-VEHICLE AZIMUTHS

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Final Azimuth•

Solar Elevation

Solar elevation limits are specified the same way target-to-ve-hicle elevations are specified - an upper and lower limit, measured indegrees above the target's horizon, specifying the highest and lowest solarelevation acceptable.

Solar Azimuth

Solar azimuth limits are specified the same way target-to-vehicleazimuths are specified and define a sector that the sun must be in if Accep-table photography is to be obtained.

Exposure Modification

The nominal exposure may be altered by specifying an amountof over or underexposure through an entry on the requirement specification.If nominal exposure is required, this entry should be ignored or set to zero.

C

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If the exposure is to be modified, the value and sign of the entry will in-

dicate the amount and direction. The value of the entry can be calculatedusing either of the two following equations:

MOD = 1.2385 AS

or

MOD = 3.0 Af,

exposure modification entry, integer with

range -99 to +99,

number of slits over or underexposure required,

number of f-stops over or underexposure re-quired. •

The MOD entry will modify the exposure only of the acquisitions specified.

Snow Inhibit Flag

Typically, the presence of snow cover that meets certain criteria,because of its higher reflectance, will result in a calculated underexposure.

The snow inhibit .flag, if set, will prevent. this underexposure from occurring.

Film Requirement

The user may specify a particular film by keying in a coded entrywith a value range of 0 to 15. These codes vary from mission to missiondepending on specific film loads. Typically, codes will be provided forsuch film requirements as

No preferenceAny black-and-whiteAny colorAny true colorAny IR colorAny specific black-and-whiteAny specific color

Since the film load for a specific mission is based on require-ments for specific films or generic film types, these requirements shouldbe provided to ICRS in accordance with established time lines.

Mode

where MOD =

AS =

Af =

Mode options, discussed in Part I, will be specified to the sof t-ware via a mode designator, or code. The exact codes will be published byICRS prior to each mission.

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Resolution

supplied by the user, it will be added by ICRS. The required resolution

is extremely important, as it operates as the upperattemptedphotography. For example, if c requirement calls fo(GRD) and the expected resolution on a given targetthen no attempt will be made. The predicted resolution is abased on a model that uses folded means of the distribution of the qualitydegraders (smear, defocus, exposure error, etc.) along with geometry of theaccess and target reflectance data.

APPLICATION OF THE REQUIREMENT CONSTRAINTS

The requirement parameters just defined can be applied by the user invirtually any combination. The only limitations typically imposed on a

requirement are resolution and mode. As more constraints are applied, theprobability of attaining the required conditions decreases. In fact, it isquite common to have requirements with conditions that are impossible tomeet. This does not mean that the use of limits should be avoided butthat the requester should use care in setting them.

The purpose of the discussion that follows is to provide the user withsome basic information that will aid him in specifying the requirements justdescribed. It is aimed primarily at the interpreter or analyst who has aspecific need or problem and desires imagery tailored to meeting that need.

Requirement parameters can be divided into three broad classes andare discussed below in that order:

L..

GeometricVehicle azimuthVehicle elevationMode

SolarSun azimuthSun elevation

QualityResolutionExposure modificationSnow inhibit flagFilm


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Geometric Constraints

The target-to-vehicle azimuth and elevation constraints define avolume in space that the vehicle must occupy at the time of photography.

For photography to occur, however, the vehicle must be able to point theoptics at the target from its position within this volume. This is not

always possible.

The KH -8 vehicle is a pointing system that uses a strip camera. Atany instant of time, the point on the earth's surface that can be imaged by

the vehicle is defined by the pointing parameters pitch and obliquity.Pitch is the in-track position of the stereo mirror; obliquity (the alge-braic sum of mirror crab and vehicle roll) is the cross-track position ofthe principal ray. The angles, shown in Figure 13, do not change duringphotography (i.e., a given frame has constant pitch and obliquity angles).This means that at a given obliquity there are only three times when thevehicle can image a single point on the ground, corresponding to the three

positions of the stereo mirror.

•

All these factors are combined in Figure 14, which shows the visibilitylimits to a target and the forward, vertical, and aft mirror position viewlines over the full obliquity. This illustration will serve as backgroundfor discussing the geometric constraints.

The vehicle elevation constraint is target centered and, essentially,the complement of the obliquity. Since the maximum obliquity is approxi-

mately 48.85° the minimum possible elevation is, therefore, about 41.2°.Any requirement with a maximum elevation less than 41.2° is impossible andwill never be attempted.

Figure 15 illustrates two methods of visualizing the elevation con-straints. In the vertical plane the limits form two fans radiating fromthe target. If the maximum elevation were 90°, there would be only asingle fan formed by the two minimum elevation radii. In the horizontalplane the limits define two concentric circles about the target's localvertical. Since this is the same projection used for the backgroundillustration, we can overlay a set of example elevation limits onto thebackground and create Figure 16. Here the required limits are superimpdsedonto the vehicle capabilities, thus showing where the vehicle must be tosatisfy the requirement.

_When viewed in the horizontal plane, the target-to-vehicle azimuth

limits describe a sector, as was shown in Figure 12. As mentioned pre-viously, the useful sector is measured clockwise from the initial to thefinal limit. A sample azimuth limit is shown on the background chart inFigure 17.

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Vehicle altitude(vehicle may beanywhere on thisplane *OR outof the page).

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Examples of typicalminimum and maximumtwist elevadansspecified in s requirement.

LocalVertical

Coverep annulusof minimum andmaximum verticalangles for givenvehicle altitudeTARGET

Ilocs1 vertical projection)

Horizontal Plant

FIGURE 15. TARGET•TO-VEHICLE ELEVATION BANDS

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Figures 1818 through 23 illustrate the interaction of azimuth and ele-vation limits with required mode. Figure 18 shows some example limits of50° and 80° elevation and 290° to 260° azimuth. The shaded area betweenboth the two azimuth limit lines and the elevation rings is, by definition,the only area where the vehicle can be for suitable photography to beattempted. In addition, it has been shown how the vehicle can photograph thetarget only when it is at a point on one of the three view lines. Thebold lines inside the shaded area therefore represent the points wherephotography is both possible and required. Subsequent illustrations willprovide sample vehicle traces and assess their impact on the photographicmode.

In Figure 19 the vehicle is passing vertically down the page to theeast of the target. Since the vehicle never passes through the shaded area,no photography will be attempted:

The sample pass has moved inboard toward the target in Figure 20.Here the trace passes through the shaded area and crosses each of theusable view lines. This means that each of the mirror positions, andtherefore every possible mode, is possible.

An almost direct overhead pass is shown in the next example. Thevehicle trace in Figure 21 passes through the shaded area twice but doesnot cross the view lines inside the required viewing geometry. In thiscase the requirement would not be a candidate for uhotoaraphv.

The fourth example is shown in Figure 22. This pass crosses the viewlines inside the shaded area for both the forward and aft mirror positions.As a result, any mode except vertical mono, stereo or laterial triplets,or half stereo can be accomplished. If, for example, the requirement werefor a stereo triplet mandatory mode, it would not be a candidate. On theother hand, if the mode were stereo triplet preferred/stereo pair accept-able, the requirement would be an active candidate for photography.

Figure 23 shows the last example. -Here the vehicle cuts only theforward view line while inside the shaded segment. As a result the only_modes that would allow photography would be those that alloW monoscopiccoverage with the mirror in the forward position.

As this discussion has shown, obtaining a normal stereo pair, becauseof the characteristics of the require that one frame must be collectedprior to the closest approach to the target and one frame after that point.When the user has specific azimuth requirements, he must assess the impactof the azimuth limits on mode. To do this he must know the direction ofthe vehicle when it is at his target latitude. This data is provided inTables VI and VII. Data in these tables is for northern hemisphere descend-ing passes. Table VI is for the usual 96.4° (sun-synchronous) inclination;Table VII is for the 110.5° inclination used for some previous 101-8 missions.Azimuth data for the entire orbits are shown in Figures 24 and 25 for thetwo inclinations. Use of the vehicle azimuth data is illustrated in Figure26. Given this, the user can determine the effect of the azimuth limits.


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TABLE VI

VEHICLE AZIMUTH vs. TARGET LATITUDE:

Latitude(deg. N)

INCLINATION 96.4°

Azimuth(deg.)

80 219.975 205.570 199.065 195.360 192.955 191.250 189.945 189.140 188.430 187.420 186.810 186.50 186.4

TABLE VII

VEHICLE AZIMUTH vs. TARGET LATITUDE:

Latitude(deg. N)

INCLINATION 110.5°

Azimuth(deg.)

65 236.060 224.555 217.650 213.045 209.740 207.235 205.330 203.825 202.720 201.910 200.80 200.5

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90FIGURE 24. VEHICLE AZIMUTH VS. TARGET LATITUDE - Inclination 96.4-

FIGURE 25. VEHICLE AZIMUTH VS. TARGET LATITUDE • Inclination = i10.5°

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Vehicle uimuth + 800Target latitude

Target

FIGURE 26. LINE OF CLOSEST APPROACH FROM VEHICLE AZIMUTH

Solar Constraints

Limits on the sun's elevation or azimuth should not be imposed withouta basic knowledge of the target/sun geometry. Once the orbit and the launchdate and time are determined, there is no further control of this geometry.Even if the orbital and launch parameters are based on a specified target'ssolar constraints, there is little or no manipulation possible. Thetarget/sun geometry is predetermined for each instant of time, and the solecontrol is over the time at which the vehicle is present. If the desiredgeometry never exists, the arrival time of the vehicle is of no consequence.

The first step in knowing the target/sun geometry is to determine thelocation of the sun. The equatorial plane is inclined to the eclipticplane by an angle of roughly 23.5°. This means that the solar sub—pointwill fall somewhere between 23.5° North and 23.5° South, depending uponthe day of the year. The sun's latitude, or declination, is plotted inFigure 27. The other coordinate, longitude, is based on time of day. Fora target at longitude X, the sun is at that same longitude at local noon,X+45° at 1500 local, X+180° at 0000 local, etc. Thus, given a date andtime, the position of the sun can be easily approximated.

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FIGURE 27. SUN DECLINATION (Latitude of solar sub-point by day)

Most dual-mode missions will be launched toin the region of local noon. There will be some

provide target overflightdeviationdeviation but probably not

will be 30°the KH-8between 35°between 90°

beyond the 1000-to-1300 loCa1 range. The result is that the sunof the longitude of most targets at the time they are visible tosystem. Also, since the great preponderance of KH-8 targets areand 65° North, this means that.the solar azimuth will usually beand 180° (i.e., generally south).

The use of orbits near local noon also confines the range of solar ele-vations at a given target. The maximum solar elevation occurs at localnoon and can be obtained using the equation

nMaX 90 - 1 6s - •T 1,

where nmax = maximum sun elevation, deg

6s solar declination, deg

OT target latitude, deg.

This is a maximum for a given date; if the target overflight time is notlocal noon, the solar elevation will be lower. Figure 28 shows the maximum

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FIGURE 28. NORTHERN HEMISPHERE SUN ANGLES (Lines of maximum sun elevation for latitude and day)

sun elevations by date and latitude. The approximate sun elevations at twohours before or after local noon are shown in Figure 29. These two illus-trations can be used to provide the requestor with an approximation of the

r expected solar elevation during a mission.

Quality Constraints

The user has relatively firm control over the photographic quality ofhis requested imagery by specifying film type and levels of acceptable re-solution and exposure. These are interdependent factors, however, and theuser must weigh them and specify requirement constraints that provideimagery pertinent to the need.

The required resolution is a limit beyond which photography will notbe attempted. It defines the lowest resolution acceptable to the requestor,not a specific value. Predicted resolution is based on such parameters asvehicle altitude, roll, stereo mirror position, sun elevation, camera-target-sun geometry, and so on. Resolution is also based on the film in use andthe exposure.

The relationship between resolution and film is obvious. Typically,the best resolutions are available from the slow speed, fine grain, black-and-white films. Color emulsions, either true color or the false color


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camouflage detection material, cannot yet return the high quality imagery available from the best black-and-white films. Since the user specifiesboth the film and the required resolution, he should beware of setting upcombinations that give a less than desirable result.

One such result would be lack of coverage. If a re • forexample, calls for color film and a GRD of no worse than then itis extremely unlikely that any imagery ollecte . is cur-rently no color film that would retur hotography under normalKH-8 operating conditions. If the requ remen had been written for 60-inchresolution or any available film, it is probable that imagery would havebeen obtained. The image quality, however, could possibly be lower thanthat needed by the user.

j

The target selection process is too complex to include a "look-ahead"feature; instead, decisions are made on a pass- s. If a 60-inchrequirement is available at 59 inches today an omorrow, theselection software cannot make a decision to wa t. e on y method ofimposing patience is to specify more stringent constraints. A user mayalso box himself in by the interaction between resolution and exposuremodification. The operational software recognizes that the resolution willbe degraded through mis-exposure whether it is an error or a deliberatechoice. A stringent resolution requirement can be undermined by including

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an over or underexposure constraint. Even if the predicted resolutionoriginally meets : the required quality, a small exposure change can causethe prediction to exceed the quality limit.

The individual requester must keep the combined constraints logical.If a particular analyst had a need to see into the doors on the north faceof a building located at 50° North, he might specify an azimuth range of330° to 30° and an elevation range of 40° to 50°. Since the north facewould be in shadow, he might also require a tw - xposure. Allthis is logical. Adding a resolution limit o ould not belogical.

These factors are under his control, and he should use them to hisadvantage by careful application of the constraints.


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SPECIAL OPERATIONSOPERATIONS

AREA REQUIREMENTS

Capability

The KH-8 has some capability to obtain high-resolution (low altitude)area coverage. This can range from simply increasing the length of framesaround known point targets to mosaicking a geographic area from coverageis the only practical mode. Examples of the various types of coverage areshown in Figure 30.

Specification

Specifying requirements for any type of area coverage is accomplishedby clear text messages from the ICRS through the NRO Satellite OperationsCenter.

For lengthening frames around point targets, the information needed

is:

The COMIREX target identifierRequirement priorityMode required: mono, stereo, lateral pair, etc.Length of extension in nautical miles.Preference for direction, if any (i.e., if conflicts exist,would extending photography south of the target be pre-ferred to extending north?)Preference for resolution or area. If the preference isfor area, extensions can take advantage of high obliquityangles, thus maximizing area coverage. If the preferenceis for quality, they must be limited to lower obliquityangles.

For area coverage, the information needed is:

Coordinates of the corner points defining the area.Priority of the requirement relative to point targetsin or near the area.Preference for point target coverage in the area prior tobeginning of stripping operations.Preference for high resolution or maximum area.


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Special Viewing Conditions

Capability

Users may request special viewing requirements through the re-quirements specification format, which varies among users, or in clear text.

Specification

When expressing special viewing requirements in clear text, thefollowing information is required:

•

Brief general description of the problem to be solved.Orientation of the object or objects of interest withrespect to true north.Parts of the object to be seen.Mode required or desired.

(5) Exposure considerations, if needed (i.e., if the objectis always in shadow or if the requirement is to look intoa tunnel or hanger, an exposure adjustment may be needed).

Exposure Bracketing

Requirements for exposure adjustments in employing both camera subsys-tems which cannot be expressed easily in the requirements specificationformat may be requested in clear text. The information needed is:

COMIREX target identifiersRange of exposure and increments around nominal exposure.

Mixed Stereo

The normal or routine operation for multiple stereo would be a stereopair with each camera subsystem, since at any given time each camera wouldnormally contain a different film type. These routine operations can bespecified by a combination of clear text and the requirements specificationformat. Requirements for other combinations of coverage are best statedin clear text; for example, "two stereo pairs with one pair in black-and-white and the other in color." The information needed is:

COMIREX target identifierFilm types to be used and the modes required (film type,not camera, should be specified.)

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Linked Coverage

"Linked coverage" is coverage of two or more targets within some speci-fied period, i.e., one pass or one day. This must be requested in cleartext. The information required is:

COMIREX identifiers of the targets.Period of coverage (pass or day).

OPERATIONS PROCESS

Target Selection Functional Flow

The target selection functional flow consists of six basic segments,as illustrated in Figure 31: the target/requirements file, the acquisitionmodule, the target selection module, the vehicle commanding module, andthe Mission Correlation Data/Countdown module.

The target/requirements file contains the physical description andthe specific collection requirements against each target. This file alsocontains the results of previous imaging operations against this targetduring a given mission. As images are accumulated against a target/re-quirement, its value for future collection is diminished.

The target acquisition module determines which targets the vehiclewill pass over on each revolution and which requirements against each targetcan potentially be satisfied. Those target/requirement pairs that can besatisfied are then considered as candidates for photography on each rev.

The target selection module is the critical module in the selectionprocess. Based on the candidate targets passed by the acquisition moduleand the relative worth of the target/requirement pairs and predictedweather, the selection module determines the best series of targets toimage over the entire revolution. This process is described in more detailin the following section on the target selection process.

After a best set of targets is selected for imaging, the module deter-mines the on and off times for each frame of photography.

The vehicle commanding module uses the list of photographic framesdetermined by the selection module to assemble the proper sequence ofsatellite vehicle commands necessary to collect the imagery operations.

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The MissionMission Correlation Data (MCD) module determines the actual geo-

graphical area and targets imaged. This is done based on the actualexecution time of each camera on/off and the best estimate of the vehicle'slocation at the time of photography. The best estimate of the vehicle'slocation is obtained from tracking data acquired before and after the photo-

graphic revolution.

The countdown module updates the coverage status in the target/require-ments file. It examines each target identified by the MCD to determine

which requirements were satisfied. Requirement satisfaction requires meet-ing resolution, mode, and any geometric constraints. For those requirementswhich were satisfied, the weather assessment is combined with the assess-ments from past attempts to determine the cumulative probability of havingcompletely satisfied the requirement at this point in the mission. If therequirement has been satisfied, no further photography will be attemptedagainst that requirement. If it has not been satisfied, further attemptsmay be made. A target with more than one requirement will be a candidatefor photography until all its requirements are satisfied.

As can be seen from Figure 31, there are two feedback loops in thetarget selection process. The first is rev-by-rev, in which the selectionmodule is informed of which targets have already been attempted at anypoint during a day. This is important at high latitudes, where targetsmay be accessible on 2 or 3 successive resolutions. The second is a dailyloop, which updates the target/requirement file and incorporates assessedweather and after-the-fact tracking data. It is also the point at whichuser reports are generated.

Target Selection Factors

Whether a target is selected for imaging and is successfully photo-graphed is determined by several factors, the two most important of which,from a user's viewpoint, are a target's worth relative to other targets andhow a photographic frame is constructed.

A target's worth, or weight, is the sum of the weights of each indivi-dual requirement levied against it. The weight of an individual require-ment is a function of its priority and shade, the mode required, the pre-dicted-versus-required resolution, the predicted weather, the cumulativeprobability of having already satisfied the requirement during the mission,and the probability of being able to completely frame the target with agiven operation. The higher the total weight of a target, the higher theprobability of its being imaged. This is especially true in areas of hightarget density, such as Moscow.

A frame of photogaphy is constructed based on the diameter of thetarget or targets that are to be imaged plus the target's location uncer-tainty, ephemeris uncertainties, vehicle pointing uncertainties, and thevehicle clock granularity (the camera can only be turned on or off in incre-

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mentd of 0.2 sec). This total process is depicted by the error ellipsoidsin Figure 32.

In the case where two or more targets are so close that their required"camera on" times overlap, the camera would be lefton . to cover both tar-gets with one frame (see Figure 33).

The target diameter : is an important parameter. The larger the diameter,the longer the camera must be turned. on, and therefore the less time there.la available to operate against other targets'close by. However, if thediameter specified does not represent the total area desired, the user willnot obtain the coverage desired.

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Camera On

7". •••n

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'1% 4.14'..♦

. el" 1 0.0

te•••

Clock Granularity.

Pointing Uncertainty

Ephemeris Uncertainty

Target Location Uncertainty

FIGURE 32. TARGET COVERAGE (Figure is not to scale but for illustration)

Camera Off

FIGURE33. MULTIPLE TARGET FRAMING

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GLOSSARY

Aspheric reflector

Companion camera

Companion coverage

Crab

Cross-track

-A concave spherical mirror, formed from the inner'surface of a portiontof a sphere. Called the"primary mirror" in the KH-8 system.

-Camera subsystem using the 5-inch wide film.

-Term used to indicate s that a target was phOtographed simultaneously by both the 9.- and5-inch-cameras.

-Rotation of the stereo mirror about the roll axisof the vehicle to compensate for the earth'srotation.

-Perpendicular to the direction the vehicle ismoving

•

Ground-resolved distance -The minimum test target element distance resolvedon the ground (the sum of one bar and one spaceon a tribar test targ with a systemthat produces a GRD o the smallestbar of the millih

istinguishableas a width.of.

In-track -Parallel with the direction the vehicle ismoving.

Main camera -.Camera.subsystem using the 9.3-inch-wide fili.

Mode -Manner in which the imagery is acquired:. mono-scopic, stereoscopic, lateral pair, etc..

Nadir -Point* on.the earth directly beneath the vehicle..

Obliquity -Angle between vehicle nadir vector and the.principal ray.

•

Pitch -Apparent rotation of the vehicle about the hori-zontal axis perpendicular to vehicle motion,accomplished by movement of the stereo mirror(displaces the optical line of sight in track). ,

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Principal ray Projection o

ri

f of the optical line of sight to the relground. Manipulated by +45° vehicle roll capability LIand stereo mirror pitch positions) and crab

(+3.85°• capability. Its ground trace in stripcamera imagery is a line through the center of aphotograph along the axis of the film.

Requirement priority -Ranking of a requirement relative to other require- rlments on a ten-point scale, 0 being the'highest • LIand 9 the lowest.

Roll -Rotation of the vehicle about the longitudinal r:1

axis of the vehicle (displaces the optical line• of sight cross-track).

r,iSemi-field angle -One-half the optical field of view. Ll

Slant range -Line-of-sight distance from image plane to r.target. L.

Start-up transient -Time and film used to accelerate the film vylo- ricity from zero to the proper speed for highresolution photography. L]

Strip camera -A camera which acquires imagery by moving film >

past a stationary slit at the same speed thatthe image moves past the slit.

Swath width -Cross-track distance on the ground subtended byL4

the optical field of view.

Sun-synchronous -Orbit whose parameters are such that the nodalregression rate is equal in magnitude and senseto the earth's mean rate of revolution about thesun. An imaging satellite in such on orbitwill pass over a given target at approximatelythe same local time each time this event occurs.

Target worth Sum ofof the weights of all requirements assignedto a target. For each requirement this includesfactors for priority, mode, quality, forecastweather, and past coverage.

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