ADDENDUM A-12 FLIGHT HANDBOOK PHOTOGRAPHIC EQUIPMENT

Created: 8/20/1963

OCR scan of the original document, errors are possible

3

Dear Jack:

The enclosed handbook is our present version of the instructions to pilots for use of our photographic equipment. ouldyour looking at it critically with regard to additions or deletions which we should make.

Because of the security nature of the contents of this Addendum, it will not be includedegular part oflight It wilL be made available to operations and pilots for useecure fashion.

Please advise mc as to who you believe should have copies of thia Addendum and how many.

Best regard

Specific Instructions For Safeguarding This Information ;

This document contain* information affecting the national defense-of the United States within the meaning olEspionage Lawn Title lo. USC. The transmission or the revelation jf its contents in any manner lo unauthorised persona is prohibited by law.

The nature of this document is such that dissemination and handling will be carried out with strict adherance to the following policies :

will be controlledtrict, officiallybasis.

accountability of each document will be maintained.

document will be controlled inashion toloss, destruction.or falling into the hands of

In the event this document is lost or Is subject to unauthorizedor other possible subjection to compromise of classified information, such fact will be promptly reported to the authority responsible for the custody of the material for appropriate action.

LIST OF ILLUSTRATIONS

Figure

Camera Configuration

Aerial Panoramic Photography, Type

Ground Coverage Format, Level Flight, Type I

l"4- ay Package Type I, Physical

ay Package Type I, System

ontrol

t-7- aynd Article AttitudeCondition

Vehicle andttitudeCondition

Typicalission

ackage Frame FormatGround Coverage Pattern

Data Recording on

2-l- Aerial Panoramic Photography, Type

Ground Coverage Format, StraightFlight, Type II

ay Package Type II Physical

LIST OF ILLUSTRATIONS (conl)

II Control3

Package Type II and Vehicle

Relationships, Caged Condition

Type II Mission

II Package Format Relationship

Ground Coverage Pattern

Coverage Format, Straight

Level Flight, Type III

Package Type III Physical

III Control

Type III Mission

EQUIPMFNT.

Information.

The primary payload of the airplane consists of various camera

configurations. These different groupings are designated as Type

I, Type II and Type III. Any one of these may be Installed in the equipment bay aft of the cockpit, depending upon the selectivity of the operating command. The characteristics chart., provides data for each of the different configurations.

Three types of lower equipment bay hatches are provided with proper window locations and sizes for the corresponding camera configuration.

1 - General.

Thequipment bay package is an aerial panoramic camera system with the mission of obtaining photographs of the earth from an airborne vehicle. The camera system photographs the earth

transverse to the vehicle line of flight. Two optical systemsa single camera package (stable platform) are employed totheorward system and an aft system.

Focal Length

Resolution of NADIR

Operating Cycle Modes Operation

1

in.

Stereo

swath widthaut miles

foot

in.

8 sec.

sweep which iseach sideertical centerllne

II

Stereo

swath widthaut. miles

t.

in.

7 sec. sweep whichach sideertical centerline

III n.

Stereo

swath widthaut. miles

t.

1 isin.

ec.

position sweep, three position stereo

Vertical0 sec. Vertical only

in.

naut. miles

FIGURE

CAMERA CONFIGURATION CHARACTERISTICS

Photographic coverage of the camera system is represented In. The forward optical system scans the earth fromto the left of nadir toto the right of nadir. The aft optical sy.trm scans the earth fromto the left of nadir tofrom the right of nadir. Each mission can0 nautical miles of flight line coverage0 frames andoautical miles (ortotal transverse coverage. The scan overlap provides full stereo viewing of mission results for all points on each frame format. See.

The package con .lists of two major assembliestable platformupporting frame assembly. See. The stable platform is an aircraft type structure that contains both camera systems and associated subsystems, and the stabilisation system. The stabilized platform is gimbal supported at Its center of gravityimbal support rod that is fixed to the frame assembly. The frame assembly is Installed directly inay at four isolation shock mounts.

The platform ia normally in either one ol two condition* caged or uncaged. In the caged condition, the platform ie locked to the frame and therefore fixed with respect to the vehicle (except" isolator freedom). In the uncaged condition, the platform ie freely suspended from the glmbal support rod. and it allowed to stabilize with respect to rate and vertically. The caging system provides an effective means to quickly and automatically change the condition of the platform.

The control panel for theackage is shown in.

The control panel is located on the left cockpit console, and occupies an areanchesnches.

The large STATUS selector switch. . controls the operation of the package. Theption selector switch controlsnput for camera functions. TheFF toggle switch controls the data recording on the film and the automatic exposure control programmer. Three indicators are: CAGEDnd OPR (green). Control panel switches and indicators are listed in Table I. Package failure ia indicatedAYOUT indicator (red) located on the warning light panel, center console.

b

cont)

(clouds)

ensor input and, therefore, provides an uncorrectedignal for camerapredeterminedormal vehicle ground speed and nominal altitude above ground scene. Used during conditions ol cloud cover to preventnformation from controlling system operation.

applicable

(emergency)

an uncorrectedignal for camera operationfor an emergency vehicle ground speed and emergency altitude above ground scene used in event of loss of one engine.

applicable

osition

toggle Switch)

system exposure program tape and data from operating, Used during preflight system checks.

applicable

ER

on exposure programmer and allows data flasher to operate (Data information will be recorded on film during OPERATE condition only. ) Timer must be turned onreselected time, usually during reiueling.

applicable

I-II. The STATUS switchposition selector switch. Positions and

functions are:

B' osition. This position energises the forward and aft camera

scanner drives, the gyro spin motors and all electronic subsystems for warmup. The scanner cubes are exposed to heat via the vehicle windows;esult, the scanner optical elements may tend to expand. Thermal expansion of the optical elements is evenly maintained and possibleof the optical surface is prevented by having the scanner cubes rotateonstant idle velocity priorission run This position also energizes theackage data recording mechanism stepping motors. The stepping motors must be synchronised with the INS inputs to reflect correct latitude, longitude and ground speed. The INS (Inertia! Navigation System) and the data recording stepping motors areprior to take-off At that time the data recording mechanism readouts follow INS signals. Data information, however, is not recorded on the film until the TIMER switch is placed to the TIMER position. Theosition of the STATUS switch also places critical systemarmup condition, Theackageritically aligned assembly both mechanically and electronically. Thermal stabilization of all critical components is achieved for proper operation of the overall system by placing the STATUS switch in theode prior to take-off.lso energizes the gyro spin motors to allow time for them to reach proper rpm

b. osition. Theosition energizes the magnetic data flight recorder and maintains all of the conditions determined by STBYhe flight recorder tapes critical system functions for post (light evaluation of overall system operation. Theosition thus maintains tho magnetic data flight recorder in operation during intermittent operation of thequipment.

c OPR. position. The OPR (operate) position of the STATUS switch places the package in the photography mode. When the STATUS switch is placed in OPR. the following events normally. The system "starts up". The green indicator light comes on.

Film is transported through each camera, all phasing andof components occur, and photography takes place. Time from Initial start-up to normal operating speed requires1lnutea.

The system will uncage if the vehicle attitude is within discrete altitude limits. The red caged indicator will not light, or

The system will remain caged if the vehicle attitude is not within discrete attitude limits. The red indicator will light.

d. OFF position. The OFF position of the STATUS switch shuts down the entireackage.

CAUTION

The OFF position is equippedpecial detent to prevent accidental placement to the OFF position. The STATUS switch must be simultaneously pushed in and turned In order lo place switch fromo OFF position.

ption Switch. ption switch controlsnputs to the camera system. Three typesnputs art provided for threeflight conditions. These are:

*. SENSOR position. The SENSOR position is the normal position forPTION switch. This position is selected during normal flight conditions and cloudless weather conditions.

b. CL (clouds) position. The CL (clouds) position Is selected duringflight conditions where partial cloud cover intermittenly obstructs the ground scene.

EH (emergency) position. The EMER (emergency) position is selec-

ted during abnormal flight conditions when one vehicle engine is out and an emergency vehicle altitude is necessary

TIMER switch. The timer toggle switch controls the data flasher

and the camera exposure programmer. The main purpose of the timer is to permit the operator to control the operation of theission and thus assure tint camera operation during preflight checks will not inadvertently cause the data chamber tothe operational base coordinates on the film.

NOTE

The Data Flasher can operate only when the TIMER switch is in the TIMERand the STATUS switch is in the OPR position. The Exposure Programmer will operate when the TIMER switch ie In the TIMER position and the STATUS switch ia in STBYr OPR position.

Thoackage ia dynamically influenced by the vehicle under normal conditions in two ways:

Power. Vehicle attitude

The package normally derives its power from inverter number 2. Power requirement* and input configurations are such that operation of theshould not be affected by the loss of one engine or by switching Inverters

Photographic performance of the package depends upon platform attitude Platform attitude should be level in pitch and roll and

parallel in azimuth with the vehicle line of flight. The package is installed in the vehicle such that in the caged condition the platform is level in pitch and roll when the vehicle is at nominal cruise attitude ofin pitch andin roll. See.

The package will uncage in the operate mode only when theis coarse levelithin +of true vertical. The vehicle must be within tin pitch and roll of Its nominal cruise attitude as shown in.

In the uncaged condition the package will stabilize with respect to rate and verticality and will automatically align itself with respect to the vehicle flight path. The package will remain uncaged and stabilise within the following vehicle attitude limits :

+ 3

+

+

The package frame physically prevents the stabilized platform from exceeding the above limits. When any limit has beenorresponding clearance switch will close and cage the platform.

-J

Q-Bay Package Is Level In Pitch And Roll When Vehicle Is At Nominal Cruise Pitch

Vehicle Andttitude Relationships, Uncaged Condition

In lhe caged condition the package is fixed with respect to the vehicle and i> level in pilch and roll only when the vehicle atlllude Is :

Yaw

ormal mission-run, the package is expected to cage and

uncage possibly more than once due to vehicle altitudehat exceed the platform caging limits. Uncaging is accomplishedompressed helium supply of limited quantity. When theis exhausted, the platform will not uncage.

It is possible for the platform to experience at leastncaging and caging cycles during one mission. Should the number of caging cycles exceedt any time during the mission.then the possibility exists that the platform will remain caged for theof the mission.

peration.

Theackage does not operate continuously throughout the entire mission. The package may be operated continuously for

a portion of the mission, or it may be operated intermittenly for an extended portion of the mission. The flight plan will normally indicate the exact operating procedure.

The package will operate properly and should be operated when required eitheraged condition or an uncaged condition. Beetperformance, however, can be expected in the uncaged, self-stabilized mode. When the package is being operated in the caged condition, vehicle attitude rates directly affect theperformance. Vehicle flight should be kept smooth and changes in vehicle attitude should be accomplished as smoothly as possible. This will minimize photographic degradation.

Two typicalission profiles are shown in.

hows continuous operation of the packageegment of the entire mission. hows intermittent operation of the package for arbitrary portions of the mission. In practice, the package will always be placed in theode atduring the final pre-flight check and shall remain there untilwitch is selected. Specific flight instructions will state thesequence of operation of the status switch for thend operate mcdes. as shown In.

2 FLIGHT HANDBOOK

Principal Point Indicator

Card

. Aft Nadir Time (Approx. )

i Sec Separation

Fwd Nadir Point (Exact)

Principal Point Indicator

tatus

i. Data Recording On Film

A2 FLIGHT HANDBOOK

Typeeneral.

The Type II equipment bay package is an aerial panoramic camera system with the mission of obtaining photographs of Lhe earth from an airborne vehicle. The camera system photographs the earth transverse tothe vehicle line of flight. Two cameraingle package {stable platform) are employed to accomplish theorward system and an aft system.

Photographic coverage of the Type II system is represented in. The forward camera scana the earth fromto the left of nadir toto the right of nadir. The aft camera scans the earth fromto the left of nadir tofrom the right of nadir. Each mission can0 nautical miles of flight line coverage8 frames andoiles (ortotal transverse The scan overlap provides full stereo viewing of mission results for all points on each frame format. In addition to normal stereo, convergentvailable within the scan overlap ofeach side of the vertical centerlinc. See.

I

Tht package counUts of two major assembliestable platiormupportin^ frame assembly. See Figure 2J. The suble platform consi .isdentical camera* and the stabilization system. The entire assembly is installed inay at three isolation shock mounts. The majority of the supporting electronic equipmentwith the Type II package is installed within framework on theay hatch.

The platform Is normally in cither one of two conditionsaged or uncaged. In the caged condition, the platform is locked to the frame and therefore fixed with respect to the vehicle (except" Isolator freedom). In the uncaged condi lion, the platform is freely suspended from the gimbal support, and is allowed to stabilize with respect to rate and vertlcallty. The caging system provides an effective means to quickly and automatically change the condition of the platform.

Tlie control panel for the Typeackage Is shown in.

The control panel is located on the left cockpit console,rennchesnches.

ormal mission-run, the package is expected to cage and

uncage possibly more thin once due to vehicle attitude perturbations that exceed the platform caging limits.

Type_ Operation.

. The Type II packagenot operate continuously throughout the entire mission. The package may be operated continuouslyortion of the mission, or It may be operated intermittenly for an extended portion of the mission. The flight plan will normallythe exact operating procedure,

. The package will operate properly and should be operated when

required eitheraged condition or an uncaged condition. Best photographic performance, however, can be expected in the uncaged, self-stabilized mode. When the package is being operated in the caged condition, vehicle attitude rates directly affect theperformance. Vehicle flight should be kept as smooth as pojslble and changesvehicle attitude should be accomplished as smoothly as possible. This will minimize photographic

ypical Type II mission profiles are shown in.

hows continuous operation of the packageegment of the entire mission. hows intermittent operation of the package for arbitrary portions of the mission. During initial ascent after refuel, turn HEATER switch to ON position. flight instructions will determine when the RECORD switch is to be turned to the ON position as shown in.

AY EQUIPMENT OUT indicator (red) on the warning light panel, center console, will light in the event of package failure. Should the failure light illuminate, turn RECORD switch to OFF position. Waitinute, and return RECORD switch lo ON. If failure light comes on again, turn RECORD and HEATER switches to OFF.

ission-run will be flownreat circle route; the

Type II package will operate in an uncaged condition all of the way; the mission flight path will be exactly as expected; the photographic results will include the area of earth desired.

The earth below the vehicle and extending too il miles on

either side is being photographed when the vehicle is at minimum lo maximum altitude. When the (light path is not as expected. It is belter In terms of photographic performance to continue without flight path correctiondirect hit" not being important as far as obtaining the necessary photographic coverage.

Caged operation, however, requires the utmost attention. Vehicle attitude rates must be kept low; the vehicle must fly as smoothly as possible to minimize photographic degradation.

If photography with the aid of the periscope wide field is desired, system operation, in most cases, will be programmed according to time and earth coordinates. However, circumstances could be that the operator is responsible for determining photographic coverage through use of the periscope.

If an object to be photographed appears on the periscope, turn RECORD switch to RECORD position. Photography will take placene minute delay period.

Results of the Typeamera systems arc panoramic photographs at shown in. Photographs from the forward camera and corresponding photographs from the aft camera are aligned as shown also in along with the asuociatcd datarec ordcd alongside of each frame. 4 photographs with recorded data can be expectedull film supply0 feet from each camera. Film width Is5 Inches. Individual frame dimensionsnchesnches.

atitude, longitude, timing track, principal point, missiondate, caging signal, aircraft altitude and camera unitare recorded for each frameredetermined code form.

Typeeneral.

i-2. The Type illy package ie an aerial camera system with the mission of obtaining photographs of the earth from an airborne vehicle. The camera system photographs the earth transverse to the vehicle line of flight. ingle camera is utilized that sweeps laterally to take photographs In five basic positionswo right oblique, one vertical and two left oblique.

i-i. Photographic coverage of the camera system Is represented in. There are two distinct modes of operation with the Type III package. weeps continuously through the five basic positions whilehotographs continuously at the same rate, however,ertical position only.overs approximatelyeach side of nadir. overseach side of nadir . Eachcan0 nautical miles fUght line coverage0 frames andoautical miles (or approximatelyof total transverse coverage. The scan overlap provides stereo viewing approximatelyeach side of nadir or an approximate total of See.

The Type III package consistsingle assembly which mounts directly to ihe vehicle through vibration isolators. See.

The control panel lor the Type III package is shown in.

The control panel i. located on the left cockpit console, andan areanchesnches.

The two position POWER swilch when turned to the ON position provides power to the camera, but will not start operation until SCAN (moder VERTICAL (modeosition is sulected on OPERATE switch. The STANDBY position of the OPERATE switch is to be selected when camera operation Is not desired.

The package utilizesolt D. C. electrical power from the Essential D. C. Bus.

The package is Installed In the vehicle such that it is level when the vehicle isominal cruise attitude ofin pitch.

2 FLIGHT HANDBOOK

. Type III Control Panel

Typeperation.

Theackage docs not operate continuously throughout the entire mission. The package may be operated contin aoualyortion of the mission, or ft may be operated intcrmittenly for an extended portion of the mission. The flight plan will normally indicate the exact operating procedure.

Vehicle flight should be kept smooth and changes in vehicle attitude should be accomplished as smoothly as possible. This willphotographic degradation.

Two typicalission profiles arc shown in.

hows continuous operation of the package for aof the entire mission. hows intermittent operation of the package for arbitrary portions of the mission. In practice the package will always be placed in the STANDBY po iltion at some point during the final pre-fllght check and will remain there until the start of the missi on.

AY EQUIPMENT FAILURE indicator (red) on the warning panel, center console, will light in the event of package failure.

Should ihe TypeUI package fail during normal operation, the following procedure Is recommended :

the OPERATE switch lo STANDBY. AYlight on the warning panel will go out.

IS seconds.

OPERATE switch to VERTICAL or SCAN positions. Ifcomes on again. turn OPERATE switch to STANDBY, wait

econds minimum, and then turn POWER switch to OFF.

issi on-run will be flownreat cioute; the

Type III package will operate satisfactorily ail the way; tho mission flight path will be exactly as expected; the photographic results will include the area of the earth desired.

The earth below the vehicle and extendingoautical miles on either side is being photographed when the vehicle is atto maximum altitudes. When the flight path ia not as expected, it is better in terms of photographic performance to continue without flight patha "direct hit" not being Important as far as obtaining the necessary photographic coverage.

If photography with the aid of the periscope wide field is desi red, system operation, in most cases, will be programmed according to time and earth coordinates. However, circumstances could be that the operator is responsible for determining photographicthrough the use of the periscope.

If an object to be photographed appears on the periscope, turn

OPERATE switch to SCAN or VERTICAL posi tions and photography starts immediately.

Results of theamera are sets of photographs in the for-

mat shown in. Each frame contains recorded data and Indentificat ion of frame posi tlon, i.ne through five. 0 photographs with recorded data can be expectedull film supply0 feet. Individual frame size isnches by

nches.

Mission number, time, date and frame position are recorded for each frame.

_2_ "

3

Dear Jack :

The enclosed handbook is our present version of the instructions to pilots for use of our photographic equipment. ouldyour looking al it critically with regard to additions or deletions which we should make.

Because of the security nature of the contents of this Addendum, it will not be Includedegular part oflight It will be made available to operations and pilots for useecure fashion.

Please advise me as to who you believe should havo copies of this Addendum and how many.

Best regards.

kid

Specific Instructions For Safeguarding This Information :

document contain* information affecting the nationalthe United States within the meaning of the Espionage LawsUSC. The transmission or theits contents in any manner to unauthorized persons islaw.

The nature of this document la such that dissemination and handling will be carried out with strict adherance to the following policies :

will be controlledtrict, officiallybasis.

accountability of each document will be maintained.

document will be controlled inashion toloss.destruction,or falling Into the hands of

the event this document is lost or is subject to unauthorizedor other possible subjection to compromise of such fact will be promptly reported to thefor the custody of the material for appropriate action.

- Ow

- Optr

- Ops r

0

Title

Camera Configuration Characteristics

Aerial Panoramic Photography, Type I

Ground Coverage Formal, Straight and Level Flight, Type I

Q-Bay Package Type I, Physicalay Package Type I, System Dimensionsontrol Panel

Q-Baynd Article Attitude Relationship! Caged Condition

Vehicle andttitude Relationships, Uncaged Condition

Typicalission Profile

ackage Frame Format Relationship To Ground Coverage Pattern

Data Recording on Film

Aerial Panoramic Photography, Type II

Ground Coverage Format, Straight and Level Flight, Type II

Q-Bay Package Type II Physical Description

LIST OF ILLUSTRATIONS (cont)

ontrol

Package Type II and Vehicle

Relationships, Caged Condition

Type II Mission

II Package Format Relationship

Ground Coverage Pattern

Coverage Format, Straight

Level Flight, Type HI

Package Type III Physical

III Control

Type UI Mission

Revised :

PHOTOGRAPHIC General Information.

The primary payload of the airplane consists of various camera

configurations. These different groupings are designated as Type 1, Type II and Type III. Any one of these may bo installed In the equipment bay aft of the cockpit, depending upon the selectivity of the operating command. The characteristics chart.. provides data for each of the different configurations.

Three types of lower equipment bay hatches are provided with proper window locations and sir.es for the corresponding camera configuration.

Type 1 - General.

Thequipment bay package is an aurlal panoramic camera system with the mission of obtaining photographs of Ihe earth from an airborne vehicle. The camera system photographs the earth transverse to the vehicle line of flight. Two optical systemsa single camera package (stable platform) are employed totheorward system and an aft system.

Focal Length

Resolution of NADIR

Ground Scale

Operating Time

Time

of Operation

I

in.

Stereo

swath

widthaut. miles

foot

rnin.

8 sec.

sweep which iseach sideertical centerline

U n.

Stereo

swath widthaut. miles

t.

in.

7 sec. sweep which isach sideertical centerline

IU n.

Stereo

swath widthaut. miles

Mode I

isin.

0 sec.

position sweep, three position stereo

Verticalsee. Vertical only

in.

naut. miles

FIGURE

CAMERA CONFIGURATION CHARACTERISTICS

Photographic coverage ol the camera system is represented in. The forward optical system scans the earth fromto the left of nadir toto the right of nadir. The aft optical syitem scans the earth fromto Ihe left of nadir tofrom the right of nadir. Each mission can0 nautical miles of flight line coverage0 frames andoautical miles (or Itotal transverse coverage. The scan overlap provides full stereo viewing of mission results (or all points on each frame format. See.

The package conjists of two major assembliestable platformupporting frame assembly. See. The stable platform Is an aircraft type structure that contains both camera systems and associated subsystems, and the stabilisation system. The stabilized platform is glmbal supported at its center ol gravityimbal support rod that is fixed to the frame assembly. The frame assembly is installed directly inay at four isolation shock mounts.

L ormalun, ihe package is expected Lo cage and

uncage possibly more than once due to vehicle attitude perturbations thai exceed the platform caging limits.

. Typeperation.

2-IS. The Type II package does not operate continuously throughout the entire mission. The package may be operated continuouslyortion of the mission, or it may be operated intermillenly for an extended portion of the mission. The flight plan will normallythe exact operating procedure.

The package will operate properly and should be operated when

required eitheraged condition or an uncaged condition. Beat photographic performance, however, can be expected in the uncaged, self-stabilized mode. When the package is being operated in the caged condition, vehicle attitude rates directly affect theperformance. Vehicle flight should be kept as smooth as possible and changes si vehicle attitude should be accomplished as smoothly as possible. This will minimize photographic

Two typical Type II mission profiles are shown In.

hows continuous operation of the packageegment of the entire mission. hows intermittent operation of the package for arbitrary portions of the mission. During Initial ascent after refuel, turn HEATER switch to ON position. flight instructions will determine when the RECORD switch Is to be turned to the ON position as shown in.

AY EQUIPMENT OUT indicator (red) on the warning light panel, center console, will light in the event of package failure. Should the failure light illuminate, turn RECORD switch to OFF position. Wailinute, and return RECORD switch to ON. If failure light comes on again, turn RECORD and HEATER switches io OFF.

ission-run will be flownroat circle route; the

Type II package will operate In an uncaged condition all of the way; the mission flight path will be exactly as expected; the photographic results will include the area of earth desired.

The earth below the vehicle and extending tooiles on

either side is being photographed when the vehicle is at minimum to maximum altitude. When the flight path is not as expected, it is better in terms of photographic performance to continue without flight path correctiondirect hit" not being important as far as obtaining the necessary photographic coverage.

Caged operation, however, requires the utmost attention. Vehicle attitude rates must be kept low; the vehicle must fly as smoothly as possible to minimize photographic degradation.

If photography with the aid of the periscope wide field is desired, system operation, in most cases, will be programmed according to time and earth coordinates. However, circumstances could be that the operator is responsible for determining photographic coverage through use of the periscope.

If an object to be photographed appears on the periscope, turn RECORD switch to RECORD position. Photography will take placene min* delay period.

Results of the Type II camera systems are panoramic photographs at shown in. Photographs from the lorward camera and corresponding photoftraphs from the aft camera arc* aligned .is shown also in along wilh the associated datarecorded alongside of each frame. 4 photographs with recorded data can be expectedull film supply0 feet from each camera. Film width is5 Inches. Individual frame dimensions arenches3 inches.

atitude, longitude,ack, principal point, missiondate, caging signal, aircraft altitude and camera unitare recorded for each frameredetermined code form.

i- 1. Typeeneral.

The Type IU equipment bay package ia an aerial camera system wiih the misaion of obtaining photographs of the earth from an airborne vehicle. The camera system photographs the earth transverse to the vehicle line of flight. ingle camera is utilized that sweeps laterally to take photographs in five basic positionswo right oblique, one vertical and two left oblique.

Photographic coverage of the camera system is represented in. There are two distinct modes of operation wilh the Type III package. weeps continuously through the five basic positions whilehotographs continuously at the same rate, however.ertical position only.overs approximatelyeach side of nadir. overseach side of nadir . Eachcan0 nautical miles flight line coverage0 frames andoautical miles (or approximatelyof total transverse coverage. The scan overlap provides stereo viewing approximatelyeach side of nadir or an approximate total of See.

The Type III package consistsingle assembly which mounts directly to the vehicle through vibration isolators. See.

The control panel for the Type III package is shown in.

The control panel is located on the left cockpit console, andan areanchesnches.

The two position POWER switch when turned to the ON position provides power to the camera, but will not start operation until SCAN {moder VERTICAL (mode Z) position is selected on OPERATE switch. The STANDBY position of the OPERATE switch is to be selected when camera operation is not desired.

The package utilizesolt D. C. electrical power from the

I

Essential D. C. Bus.

The package is installed in the vehicle such that it ie level when the vehicle isominal cruise altitude ofin pitch.

2 FLIGHT HANDBOOK

. Type III Control Panel

peration.

The Type III package does not operate continuously throughout the entire mission. The package may be operated continuouslyortion of the mission, or It may be operated intermlttcnly for an extended portion of the mission. The flight plan will normally indicate the exact operating procedure.

Vehicle flight should be kept smooth and changes in vehicle attitude should be accomplished as smoothly as possible. This willphotographic degradation.

Two typical Type III mission profiles are shown in.

hows continuous operation of the package for aof the entire mission. hows intermittent operation of the package for arbitrary portions of the mission. In practice, the package will always be placed in the STANDBY pontion at some point during the final pre-flight check and will remain there until the start of the mission.

AY EQUIPMENT FAILURE indicator (red) on the warning panel, center console, will light in the event of package failure.

)

'3

Should the TypclU package fail during normal operation, the following procedure is recommended :

the OPERATE switch to STANDBY. AYlight on the warning panel will go out.

econds.

OPERATE switch to VERTICAL or SCAN positions. Ifcomes on again, turn OPERATE switch to STANDBY, wait

econds minimum, and then turn POWER switch to OFF.

ission-run will be flownreat circle route; the

Type HI package will operate satisfactorily all the way; the mission flight path will be exactly as expected; the photographic results will include the area of the earth desired.

The earth below the vehicle and extendingoautical miles on either side is being photographed when the vehicle is atto maximum altitudes. When Ihe flight path is not as expected, ii is better in terms of photographic performance to continue without flight path correctiondirect hit" not being important as far as obtaining the necessary photographic coverage.

photography with the aid of the periscope wide field ie dcsi red, system opcrat ion, in most cases, will be programmed according to time and earth coordinates. However, circumstances could be that the operator is responsible for determining photographicthrough the use of the periscope.

If an object to be photographed appears on the periscope, turn OPERATE switch to SCAN or VERTICAL posi tions and photography starts immediately.

Results of the Type III camera are sets of photographs in theshown in. Each frame contains recorded data and indentlficat ion of framene throughhotographs with recorded data can be expected from

a full film supply0 feet. Individual frame size isnches.bynches.

Mission number, time, date and frame position are recorded for each frame.

The control panel consists of two switchesa RECORD switchEATER switch. The RECORD position of the RECORD switch places the package in the photographic mode and the following events normally occur :

he system "startsilm is transported through each camera, all phasing and synchronism of components occur and photography takes place.

The system will uncage if the vehicle attitude is within attitude limits.

or

The system will remain caged if the vehicle attitude is not within discrete attitude limits.

The Type II package is dynamically influenced by the vehicle under normal conditions in two ways :

(1) Power inputsehicle attitude.

The package normally derives its power from inverter number 2.

Power requirements and input configurations arc Such that operation of the package should not be affected by the loss of one engine or by switching inverters.

Photographic performance of Ihe package depends upon platform attitude. Platform attitude should be level in pitch and roll and parallel in azimuth with the vehicle line ol flight. Tht- package is installed In the vehicle such that in the caged condition the platform is ltvel in pitch and roll when the vehicle ss at nominal cruise attitude ofin pitch andin roll. See.

, The package will uncage in the operate mode only when the rate gyro senses rate changes of lessredetermined number of degrees per second.

In the uncaged condition, the package will stabilize with respect to rate and verticality and will automatically align itself with respect to the vehicle flight path. The package will remain uncaged and stabilize within the following vehicle altitude limits.

+ 3

The package frame physically prevents the stabilized platform from exceeding the above limits. When any limitenorresponding clearance switchose and cage the platform.

5 @e

AY EQUIPMENT OUT indicator (red) on the warning

light panel center conaole. will light in the event of package The package failure indication on the warning light panel can only occur when the status switch is in the OPR position. ayload failure occurs, the package will automatically switch from the operate mode to theode, the green OPR indicator will go out and the amberight will light.

Should theackage fail during normal operation, the following procedure is recommended:

the STATUS switch from the OPR position lo the STBY AY EQUIPMENT OUT light on the warninggo out. On the control panel, the amberight willlight.

econds.

STATUS switch to OPR position. One of three possiblewill occur:

(1) IfAY EQUIPMENT OUT light lights immediately, place the STATUS switch to the OFF position

IfAY EQUIPMENT OUT light does nol light

immediately, but does lightoticeable time3 toeconds) return the STATUS switch toosition and waiteconds. Then place the STATUS switch to the OPR. position and observeAY EQUIPMENT OUT indicator. If the indicator lights, then the STATUS switch should be placed in the OFF position.

or

IfAY EQUIPMENT OUT light does not light withineconds, then the package can be considered operational.

All three control panel indicators are of the press-to-test type. AH three indicators should be checked during the pre-flight checkout.

ission-run will be flownreat circle route; the

ackage will operate in an uncaged condition all of the way; the mission flight path will be exactly as expected; the photographic results will include the area of earth desired.

AD2 FLIGHT HANDBOOK

owever circumstances may beission-run that the flight path is not as expected or the package has been operating caged most of the way.

Caged operation, however requires the utmost attention. Vehicle attitude rates must be kept low; the vehicle must flv as smoothly as possible to minimise photographic degradation.

If photography with the aid of the periscope wide field ie desired.

system operation, in most cases, will be programmed according to time and earth coordinates However, circumstances could be that the operator is responsible for determining photographic coverage through use of the periscope.

If an object to be photographed appears on the periscope wide fieldime when theackage is in theode, themust be placed into the OPERATE mode withineconds after the object's first appearance on the periscope wide field. If the STATUS switch is not placed to the OPR position within the object's firsteconds of visibility on the periscope then the object will probably not be within the photographic field of view during the time of photography.

Results of theamera system are matched sets of panoramic photographs in the format shown in Figure Paired photographs one forward scan and the corresponding aft scan, appear with the associated data information recorded in an area between themuch paired photographs with recorded data can be expectedull film supply0 feet. Film width isnches. Individual frame dimensions arenches8 inches.

Vehicle gsound speed latitude, longitude, Greenwich Mean Time.

and the mission flight number are recorded for each frame. See aged status indication is also provided for.whetheray package was caged or uncaged for any particular frame.

Original document.

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