r• 20 October 1966

' 1

EARLY "DISCOVERER" HISTORY

The first of the Discoverer series, an agena with no

payload, aborted on the pad on the day of launch. Due to a

vehicle sneak circuit, the separation retro rockets and explosive bolts fired when a hydraulic motor was exercised at

T-60 minutes, causing fireworks on the pad.

The second agena (Discoverer No. 1) made orbit February

28, 1959, although in radio silence. Speculation at the time

was that the protective nose cone over the antennas was ejected

just before the agena firing and the agena then rammed into the

nose cone and damaged the antennas to the point Where no radio

contact. was made. Orbit was confirmed by radar skin-track. •

•

The first recoverable type Discoverer payload consisted

of a bio-medical capsule containing four live mice. The capsule

itself was similar to our present ones, although smaller. On

the first try at laundh, the mice were dead as indicated by

telemetry. At first it was thought that they were asleep, so.

a cherrypicker was sent up and a technician banged on the side

of the vehicle in an attempt to wake them up. Catcalls and

meows were used to no avail. It was later found that the

mouse cage had been sprayed with krylon to make it smooth;

but the krylon had chipped off the screen, the mice found

it tasty and that ended that.

The second try several days later was almost aborted

When the capsule life-cell humidity sensor suddenly indicated

10096 humidity, out-of-band on TA. Panic prevailed until the

humidity then gradually crept down to a normal level. On

evaluating the trouble, it was found that the humidity Sensor.

is located right under the cage when on the pad and that a

mouse merely did what comes naturally, but when the moisture

dried out, all was forgiven, and it was launched -- into the

ocean.

At the insistence of the SPCA, it was decided not to use

live mice again until the orbit and recovery systems had been

perfected, so the next Ddscoverer had four "mechanical" mice,

merely small transistorized multivibrators to give a TA

readout, with simulated life-support. systems. This capsule
•

made orbit, but due to an orbit timer problem, it was ejected

over the North Pole and came down is the snow near Spitzenbergen, off Norway. It is felt that recovery functions

occurred, but the capsule was never retrieved - by America.

This payload was also distinguished by a notable member

of our A/P facility - Harvey Boissier. It was desired to

develop a system Whereby our doors could be hidden from

inquisitive eyes during the time our payload was on the pad.

The Fairing was covered with paper, under which were two

pieces of piano wire with ping-pong balls attached, with the

idea that hopefully the wind caused by liftoff and launch

would blow the ping-pong balls to the rear and the wire

would tear the paper off, exposing the Fairing.

•

To test this concept, a test Fairing with paper, pingpong balls and all, was mounted on a sports car and was

driven up and down Bayshore at 90 per. This was quite a.

spectacle and attracted the attention of the local Gendarmes,

Who ticketed the driver.

On launch day, Harvey had the honor of attaching the

balls to the top of the payload. Can you imagine how silly

he. felt at 2 a.m. on a foggy cold morning, with searchlights

blazing and blockhouse TV watching, as he attached the pingpong balls on a million dollar satellite? While this was

happening, the whole missile started to erect and Harvey, for

a moment, had the uncanny feeling he was going into orbit.

Anyway, it was launched, without Harvey, and the paper

never came off. For all we know, the two ping-pong balls

are still in orbit.

Then came the era of disappoinment -- our "C" instrument

either did not work, did not go into orbit, or the capsule was

not recovered. It is interesting to note the frustration-that

followed Discoverer NA when the instrument worked all the way,

but no recovery. 0 •

It was about this time in the course of "witch hunts" to

locate our problems that it was felt the Fairing Interface was

heating up during ascent. It became Frank Watson's chore to

devise a Fairing cooler. Frank had a water receptacle installed

around the leading edge of the Fairing, the idea being that the

water would boil during ascent and the steam would carry away

the heat.
1

V :it ••• • •

..

r

•

In order to contain the water and prevent sloshing,

Frank wanted something absorbent, soft and easy to work.

Kotex fulfilled these requirements so Frank bribed Ethel

• Jackson to get some for him.

The reservoir was filled using a large hypodermic

.needle through the small external holes. Of course this led

to tricks and Harvey Boissier again • entered the picture.

He rigged up a display for visiting VIP's, so that to satisfy

their desire to touch the hardware they could use the hypodermic to squirt water in, but it squirted right out again

throUgh anoter hole, to the eMbarressment of a drenched VIP.

Remember 1054, Discoverer X, the first payload recovery?

A perfect laundh, but the Thor Ushtailed and was destructed -

at 10,000 feet. The. payload came down about a mile from Pad

5, and was located by helicopter, which landed payload people

to guard it and render the pyrotechnics safe. Recovery was

made by Jeep, rather an unsuspicious ending for a reconnaissance

. payload.

It was decided that Discoverer XII was to be a "diagnostic"

capsule, loaded with instrumentation and telemetry to tell us

what was happening. It went into the ocean.

Discoverer XIII is famous. It was another diagnostic

capsule and it worked all the way. Its capsule now reposes

in the Smithsonian Institute, Washington, D.C., as the first

object to be recovered from orbit. It was later determined

that our capsules were being destroyed by.explosions of small

rockets used for spin and despin. Starting with Discoverer

XII, our present cold-gas spin and despin system was inaugurated,

and several successful recoveries ensued.

Discoverer XIV was a "C"

completely successful, ending

snatched on August 19, 1960.

project was on its way to the

instrument and the mission was

with 20 pounds of payload airThe spell had been broken; our

success it is today.
First Recovery from Space
First Aerial Recovery

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. Table 1-1 Operating Characteristics

Lens type

Configuration of cameras

Film

Filter

Lateral angular coverage

Forward angular coverage

Overlap

Format size

Film capacities

Relative humidity environment

Temperature environment

(lens cell)

Pressure environment

Power consumption/camera

System life

24-inch focal length, f/3.5 Petzval

30-degree convergent stereo

Type 3404 thin-base 70-millimeter

film (former designation 4404)

Wratten 21 or 25

70 degrees (f35 degrees)

5 degrees 15 minutes (at format

center)

10 percent (at format center)

2%6 by 29 Y4 inches

M System - 15,600 + feet

J System - 31,200 + feet

2.15 to 6.0 seconds/cycle

043 2.15 seconds

Exceeds 130 lines per millimeter

at 2:1 target contrast

60 percent maximum

70 * 10 °F

1 x 10-1-to 1 x 10-8 mm

500 watts

30 days

Cycle rate

Maximum cycle rate at V/h = O.

Dynamic resolution
Table 1-1 — Summary of Physical Features and Operational Parameters

30-degree convergent stereo panoramic

cameras

24-inch focal length, f/3.5 Petzval design

15,750 feet of 70-millimeter, 3.0-mil,

polyester-base film per camera

31.632 x 2.754 inches

29.323 x 2.147 inches

1620 watt-hours (24 vdc, unregulated, at

2.5 radians per second)

270 watt-hours (115 vac, 400 cps, at

2.5 radians per second)

Approcimately 437 pounds

Approximately 597 pounds

1.5 to 4.2 seconds per cycle

Variable

Fixed at 7.6 percent

Variable (2 position)

0.0525 to 0.021 radians per second

80 to 200 nautical miles

118 to 290 nautical miles

7.73 to 19.33 nautical miles

41,167 nautical miles at 80-nautical mile altitude

169 minutes at 80-nautical mile altitude

Physical Features

Configuration

Lenses

Film capacity

Film size

Usable format

Power

Weight (empty)

Weight (with film)

Cycle period

Exposure time

Overlap

Filter

Operational Parameters

V/h range

Altitude

Cross-track coverage per frame

Along-track coverage per frame

Total along-track coverage

Total operating time


TOP

/Th

LAUNCH BY PROGRAM BY .EAR 1951:jk

YEAR DISC/ MIDAS/ 10. NASA 102 201 APSHOT 638/ TOTAL

162/241 461 vr.,A

0 *0 0 o

1 0 0 0

h 2 0

0 ..

1 6 2 3

0 0 0 0

0 7 0 0

0 4 0 0

14

25

37

27

hl

29.

59 8 0

60 11 2

61 17 2

62 22 2

63 16 3

64 16. 0

65 12 0

,/t/.// /4://iikezmzzz

TOTAL 102 9

243.

CAPSULES

LAUNCHED REC .

YEAR

CA PSK,F,5

MUNCHED

CAPSULES

RECCCERED

AIR SEA

59 8 0 0

60 3 1

61 16 4 3

62 21 16 0

63 18 , 10 2

64 28 • 22 1.

65 22 • . 21 0

113-TOTAL 123

tND TOTAL 123

. •

4
: • ,

•

Characteristics 

•

Operational ground resolution capability of, 3' to • 5 feet or. better a

. •

high and 2:1 contrasti reepectively, from 110 ill; miles including

digridation due tauhcoapena4edaMigemotion . and vehicle stabilisation

.

. . . . . , . • -

residuals.. Camtra4 dynamic resolution test sPecification - 80 limot'AMAR

2:1 contrast on 80-132 using MIL-STD450A.'-Scale 1/120,000.

. • -

:Altitude - System.specifications arelor orbits in the altitude ran

over target from 90 to 175 nautical miles. The design readily

accoimalates elliptical orbits permitting versatile operational use.'

Design altitude - 110 114

Orbit Life - 4 days - selected targets on command -. ground selectivitY..:..

of 5 alternate programs.

Coverage - 42.3 nautical mile swath width at 110 nautical miles over

220 panoramic scan. Format 4.5 x 25 inches. About 3,600 photos each

7.5 x42.3 nautical miles or approximately 1,000,000 square nautical

mile0ertical coverage at 110 n. miles.

Lens, diffraction limited, 66" r/5. Lens-film resolution with S0-132

100 limMAWAR at 2:1 contrast. 175 1/MmAWAR at high contrast - 160'

lbs..

Mirror - 241 diameter beryllium - 40 lbs.

Film - CapaCity 75 lbs., corresponding to 8,000 feet of 5* 3-mil

Eatar film.

1. Overlap - Minimum 10% npminal at nadir maintained for full V/h range.

1. Stereo - ± 15° fore and a ft. 30° convergence.

a •

• 3. Exposure - &pi:lure selectable by inserting one of,ten . flied slits

prior to'launch providing 1/75 . to'1,4500. secondexops7eat nominal

..ktv • • .AI

t .J,•4 •
•

•

. • •

'•'•*.r,!r

••

• "

.filias at any t1e .of year...

713.ter Wratteii. 21.

. • I. . Film Type - 80-130, 80-206, or 80-132 fiLa may 10:used•depaexting On . . . ,..

miassion requirements. 

 .

130-132 for ground. illumiXation- greater than

... . 2,800 ft-caiidles corresponds to solai altitude' greater than 22° or • - ... . .„ 

.... ,,

. ..,.. s • • for noon iaimah ci.orrespi O ond t . Airil 10 to Septaither 5 .

. for 35° tO•

-

.

75° noith latitude. 80406 *ill increase latitude to 88° or cover

same latitutes as 1,32 for 9 additional masks at idight penalty. in

dmage quality. 

. • ,

For solar altitude leis than 22°, 430-206 for maximising

area •of fbiat reso-Aution or 80-130•1or ziaidadsing northern-most • .

•

tly hefore launch:firi.theiest three-Line a.k.".:****''.:

tion tothe expected T/h 0Vbrpcivruil altitude range.

p.

Wt014".

1 • •

n. Environimait--* 

4

.Unressritk ; temperatuie . 70 + 10°F. Passive

.04 .

n6 IMO 4 11C arkd cycling rate are vari414 

_ :

proportional to • V/h in .

the toogo'oi. :citat) to .0458 rad/sec Ocir;esponding to cycling rats.Of..:-.7.

:. .- .

1 -iii rio . i .;sicoiaii per frees. 1110'ilaocurata to within 1% ortiOimiSiiii5 • ; i•! • •:. .

.

, t

.

,. .....: . ' valui .. 111a V/h rate Is programmed iUternaili7to the camera as a

. ... ,

function orAlmo - Ten t/h fuictiont4nd tiii-V/h generator start timeSAk.,..,,

. • • .• • .

..

-

,,1 ,...•

t. '' . . ,,,,,:,4;:zin ::0- • :D..- • .

• • •• 0, can hik::: 

T.

kited. iiy. ground comessul. Each of the ten functions

n .

. •

•

The panoramic caiera System iOnorporates tbs.:following features: .•

a. 11:Steering.-The entire Camera • •

conttol ;for ;ant:of:muss

• o. W.

eiglat4,7,..p

•

:sq.:,0aeSTa 

. 610 lbs. - OassottO.1,5;.1

•

°1)300-4v4: .tarsettnt.

V;;;.-.4 .1:•• cover; 't•

•

• •• . ;

•

not •

.:

Lr6

OM.

•

Olid up to 30°. for • ..•

r.„t

; • .• • ; • • . • • • • • • • ...t•liST, • "•.:- ::* • '• ra.‘trapict attainraent of target4 •

• t]fmg•:theytlight

•

• , 2. DistinguishirstFeatutta
4.

I •

from ono 30° extreme to the °the:RV'

• • •

•• •- . for . rolline .."*..3.5°. •Indrement.' •

. . ,

. • • -

0.30#t.ely 5 seconds are roil:died:: •

•

adision.with.i0i834111/11 response tieis.of :stainida required for to :• n

• .

• A

b. Stereo - Stereo la provided as an aid tit photo-interpretation., The

•

direction the camera looks .• is controLled by-rotating the mirkor.tb .the • . • • •

• • •

—.• its

. : :

,F•n••••••!..ji".;

•

.so 

-.* litsitip-systes • ••

significant riaolfition loss. 'The roll stsfriAg is accomplished in '

.

. .

discrete angles

. .." • 00, 15°, and 1.'430° offering e 'total a?ailable .

swath 'Width of : 192 n...idles. The:system Pirate 200 roll excursions..iter :1;:.i.;::':,.:

forwards verticals or aft position and, )rldingi it stationary while ' ••

panoramic •scanning is accomplished. ..the camera accomplished a stereo

"burst" by expoOing 8 frames Idth...thi camera looking ibrward

the camera looking baok...:;....„ 15°over the fame area. The

r

•

4 :

ded to repeat so .

s4"1 •

=; xposed film is. intermittently supplied to

Transport controlled4 •

t 4hrough film path for

he

. • .* eel

•

•spools are cOntr0

.

7••

tomatically adjusted darling roll steeringt

1r.roA, : •

additti•

• C.

•

Yi- ;-

high**:iie1teh and'ainimmi

and :;h434.-ata : cry during photo

.!.: •

provi Clot tension with rlie;

8 fr •

came

144): •••

ceset teeny' shut oft

1:7

, . .-• of 16 frames.

eta" m'

d.

its tiociStji.s

. .ei......4.. such - ..0.euh ter-rotate in the - e each at . a unifd

4

'

i..:-.. :-.7........., . 4.•::,:".

speed.,:: .eanieKlising vehicle dis Anternal vibration

,.:.-• •

F $ 4,-,:" :,,.. - -0-..wi

.

d. -. ... : 'kir', ".

...roPk"

-: . ad

:

.

.. . ••

...5.

waster less of over ticin upon recei :

..

.4.•:.

•

elee;...., - 0* pour. The Cate*

••••":: •,.,4 '',.1,.:.•••,..•••••-'?.-fst,i v:.. .44,3

.:'.4*.•

. PI /1 ..

i.

‘•n 2..4,

t.{.•,•-'',.: --!

...• ,,,, - .. • : ••

. :. • • I : , • I. • • .

.1 • • • 1

, * . t.y.d- 5.--;?-4

jtp

• 

to speed without.f ,:4:,"

...•...

'. .:. . 1.,• ..1 . .. ....,44

- .

• •

e'V r

Bot .rotition :flat' plate '

v, 7:• : -• ecialIN:, an

.,., ii0perational versa

:;:,;;;Ii - ... - ' • ••••• • *an is. acoomplis

•

•, ...,, .• ....!.i • •. :.

..Ous- offering • - .•,•41 4.4;

. :

ra

•

 ralation of the .lens.•:.1.1 AI

. -• . • e;::; 1'4'4

.• •

21v:rs .

resolution and

::.:; :• • •
,•••n•• •

•

:

TAi

rotat• ,e,140M4 :The labOrt , •.lil'ilaP

techniques tn

.

cluding extremely low friction to-rednee

- • • • ' •-•-• •

for panoramic scanning. To nest prob* DiG, the scan •velocity is

controlled by •*.high performance driii using a preciaicn AC tar:home - tar;

and a W.torquer-ehich eliminates direct mechanical coupling. The

, • • . .

•

plane'shOttir driven by a high accuracynichanism is coupled to the

.

, • , •••4(•

rigidity per wait; weight incorporating titanium fittings for- mixiiaum ..•••

••

strength to weight where required. The cia ►ere is mounted in the

vehiOle by . •e . Sfrii4e mounting flange . the .C.G. offering high

.• •

.

resiatanee . O.vehicle structural and.thernalAatreases on the camera

The structure consists of three partilioitia together at the main .

mountinitlaegeThe aft section contains : the lanai mirror, and all

4,

. .

.

electronini necessary for their/ operation. The inner-tube

•• .

•

. .

„ •

the Oaten end'reterences 

•:

it to the lens nodal point providing • .•

.; • • • . • • if• • vibratiOnAnd thermal isolation. Th • Oliterlibe supports the film ''

,

traniiPoresy stekhnd all electronics 'necessary for its operation. The :':.;;;:ge•'..

• ..-,

_ . . .

three'sictionaHmay beleadiXT and quieilfdisiasenbled to provide

,•

access . tO any part of the camera ayste147. • Vructures are i st

. • :

prodUced by.UseCt special jigs and tint during manufacture

. •

••,-- •

• such 'that a ..strustwal section is interchangeable with the sating

. , 

• section tof •any :other structure. This, feature -facilitates ease.'Snd

rapidity of •both assembly and field opersitiOriii. • . :• '1 •

"• •

f. Electronics Configuration - The amplifiere and control circuitry

!

of the camera are built-in plug-in easily replaceable nodules.

Multiple usage of nodules simplifies spares provisioning. Maxiamia

reliability is achieved by use of Billion traisistore screened

• _ . . . •

by X-ray . inapeCtion tend by po • ting W.. .200-telour'bui:0-ihfpi all

•

. • :

ivarPreciid**-Pr-hr°'

Structure - The structure is semi-mom ocoque siegnesium for soxiiiimL'' .

.

• •

•

. .
-

civlifieiviiriorto Installation. ..i‘%'''

k 4Yto * 1 • ' - Jo . , 1• .4rPfit re e

. r. . !I , , . • ..*" J4 --

',"1.44 *".41 

• %.. - , g. Auxiliary Data - Worded on a digital data block on each frame.

May be read by human or machine.

Time to 1/100 second - 29 bits

. ,

Scan Velocity Error, 1614.'

Stereo Mirror. Position •

R034.steertirgPesitial . vs., cm wur424*......001

h. Stellar/Index Cameias -'Stellar and index cameras are coordinated

with Pan photography, to provide 'attitude'', cartographib, and

position information, The `atellar and index cameras operate

to expose 1 frame, for every 10 panoramic frames providing

55% overlap. These may be operated independent of the panoramic,.

and both have 400 frame capabity.

Indei Camera - 38 mm f/4.5 - 21x 21 inch format on 70 mm film.

Stellar Camera - 85 pr:1f/1.9 approxiMately. 1-inch circular

format on 35mm film.
AR INTERNAL USE ONLY

Ilg. -- Flint threading diapent
DRAFT

History of Resolution Testing in the Field 

The original concept for the 'C and C i program included dynamic resolution

tests at A/P and VAFB using p ortable collimators. The VAFB tests were

eliminated due to unstable dolly mounting of the system resulting in resolution

data that was meaningless relative to system performance. The VAFB tests

were eliminated prior to any successful recoveries.

Resolution test procedures for the C and C' cameras established a

so called "figure of merit" approximately 20 percent below the values determined

at Itek-Boston. With the exception of the last few C I units which required major

mechanical maintenance in the field no adjustment of the optics was made at the

A/P facility.

The C program continued the portable collimator concept with a change

in procedure during the program to thrrhil f

fitocus tests instead of the "figure of

merit" determination of performance. Because of inadeauacies in the test

system, determination and confirmation of focus provided more useful data

than rra ximum resolution figures.

A change in test procedures was established for the M program 6 • 7.€

on the premise that unknown system effects due to interaction of two instruments

may result in some quality degrEclation. A seismic block was installed in

rtatioettf. Waltham with the capability of installitlir and both instruments

ar; 4‘..g Nish"ro during resolution tests. A similar but inadequate

installation was made at the A/P. facility to determine complete system effects.

Inadeqaucies of the test bed relative to vibration effects, precluded the use

of "figure of merit" ast maximum resolution data as a criteria for acceptance.

Resulting data was inconsistent if an attempt was made to compare resolution

values with that obtained at Waltham. Therefore a thorough focus procedure was

established with maximum allowable deviation joht61 ► Itek-Waltham data

specified. It may be noted that all M systems were within the specified tolerances.
Absolute quality resolution data obtained has not been correlated with flight performance

due to some known and/or unknown systems effects that cannot be simulated by

any feasible type of testing at the A/P facility. The disharmony and time wasting discussion resulting from quality determination tests conducted in the field with

inadequate simulation of systems effects and compronlising test procedures and

equipment are not needed in present or future programs.

If the integrity of an optical system is in doubt as a result of shipping and

handling, it has not been properly qualified for flight. If the qualification program

is assumed to be adequate then shipping, handling and test procedures should be

modified to insure the camera is treated as an optical instrument not as a football.
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.

.

Pan Camera Subsystem ASSEMBLY

CHECKOUT

TEST

INTEORATCON

vac (AM

Engineering Design

Manufacture of:

-Spice Structure

-Ilect.Copponente

-a=

F;AIRCEILD

n•n=110.

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Assembly

Static Altana.

Wood° Tests

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?met."

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Tracking

C/W

Cycle Metes

Pyro

Int.Pace.Ver.

Rec. Comm.Seq.

it

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c.Rete Verity

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PMU

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Optical Callb.

Maintenance.

Accept.

Test

•

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Inspect Paint

Weigh Component That

3..Weeks

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R-10 Readiness'

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-- 1.1 .

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Disassembly

Pyros Installed

Electrical c/o

Cold Gas

1716bsystem.Assembly

Load Payload

Light Leek

End to End Test

Pyros Installed

PHD •

Flt.Slit Assembly

S/I Load

11

R-3

R-2 READINESS (Mated

Confidence Tests

Quick Look •

Pre Skip Audit & Critique

Dam

MENA

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PAD TESTS

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400-2000

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QVALInCATION

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15-20 2.1. g, 0-P

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11-2000 0.7 g O-P

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SYSTEM INTERNAL PIONNURN 10- 14 DM BO SIMULATION B°*) B•650

MAX 'ORATION 6 DAYS • • summon B. 0°, 40°, Too. . TNT OF REPRESENTATIVE =On MIRAN

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LOfi TBMPERATURE TWIT AT 50°F.

RX TEMPERATURE TEST AT 90°F..

SUM OPERATIONAL AT RIM & LW TINOS

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sco-saussiscAnciarausompts •
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No7fib7l1700WCYT.

COVERED* DOCIEDEITS

• t

DISC 6117

AO-J3-001

T3-6-ooe

T3-6-o63

Exhibit

SE-64-23

DOS 39TL1

General Environmental Specification for Ageba

Satellite Program

Requirement Specification "J3" PaylOad System,

Corona J Program

General Specification for Payload Qualification

and Acceptance

Test Specification for Acceptance and Qualification

of J-3 Payload Systems .

DISIC Performance Specification

Design Control Specification 3-3 Panaramic Camera System

S0010-02-0022 SW/ System . Design Specification

•
Density (gO/cps) Overall Aceelerakion 

• ben as) •

0.025

•

sivatasamTki TM ANUS ..

ACCIPIANCI

4

Copy # 

QUALIFICARTON

Sinusoidal Vibration 

Longitudinal Axis

Prequenc7 (221) Level

5-15 0.38 Inches peek to pink

15-20 4.0 es, 0-peek

20-400 3.0 g's, 0-peak

400-2000 3.5 g's, 0-pesk

Lateral Axes (220 Level Ws)

11-2000 2.0

Random Vibration 

Frequency Rangy (420 Density (e9.A)

20-400 0.05.

YESiL (W) . level

15-400 17b-Ps, 0 -

400-2000 •2.5 g's, 0 -.peak.

Overall Acceleration • 1110)

•

/too -2000 0.12 14.5 400-2000 0.09 13.0

Thermal Altitude 

Vacuum Ibmperature(aclemetil) Vacuum Temperature Nyclematic 

10-5mm Rg -220 to . +2500

lens Ng -120 to.+250°

. Shock

Longitudinal Axis 

Level (iteD Duration (12.)

15 6

Lateral Axes 

Level (re) Duration (au)

5 6

Number ( 2.1E.01

3

Number (ma)

3

10P-SNORNI-0-SPIDENIS

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th ' Copy #

Acceleration 

Longitudinal Axis + indicatep recent)

Level (1!) Direction

11.0

15.0

22.0

Lateral Axes 

Level (g!!)

6.o

8.0

Load Testing ( Structures)

00

to 100% load limit in 5% increments of

5 to 10 second duratiOn.

Direction • blot to be•perfonsed

eoneurnmtl ►) •
•

41.11BYSPECIAL HANDLING

VIP 88:-08038 •

WOBURN ANALYSIS TECHNIQUE

NOR

11/1111111111P

PANORAMIC CAMERASf. 21 JUNE 1968

iallIP/SPECIAL HANDLING •
111n6

PICIAL HARMING

681-06038

ABSTRACT 

A similified, graphic analysis . technique has been

'developed for the'selection and control of the variable

exposure capabilitea.of the 4111111PCR-systemi. The "mar

ccmputer program produces piinted plots which graphically

relate ideal camera slit width to orbit time-and geographic

pOsition. The technique provides directly observable, indications of the requirements for, as well as the actual per-

' formance of, the panoramic camera exposure Control system.

The display concept is equally applicable to fixed slit

systems or to continuously variable slit systems.
PANORAMIC CAMERAS 

.

!Carly in the history of the 41.1n Program LMSC recognized that a convenient . •

steam was needed to relate all of the variables influencing the exposure obtained

by a panoramic camera in a non-circular orbit. It was necessary to consider the

variations in exposure times produce • by a fixed slit in a camera subjected to

constantly changing panoramic scan rates as dictated by the image motion compenm.

nation requirements. It was also necessary to consider the corresponding variations

in exposure time resulting from the profiles of image illuminance experienced.

Pie-flight slit selection then became a matter of determining what slit size would

produce the most desirable combination of maximum area-of-interest coverage

(properly exposed) and minimum overexposure potential. Of course, no in-flight

-corrections or modifications to the exposure was possible.

.This basic routine for the analysis of exposure for the panoramic cameraswas

-&1iUA*1.1FIRICAS mid-1963 as a computerized program with the identifying

Alum "XPAN", and has been the basis for launch time and slit/filter recommendam •

-7tions on-all subsequent missions. The output of this original program was limited

:to a simple tabulation of the required analytical data. By using the actual

.o bital characteristics experienced, the XPAN routine has provided a post-flight r

eummary of the mission exposure performance. •

The OR camera system introduced a multiple-slit variable exposure control.capa- •

bility. The control system consists of a series of four discrete slit widths

* which are stepped in a pre-flight established time sequence. The exposure control

timer is activated by stored program commands from the Agana &etimer. Initiation

of the slit-changing sequence trails the activation by a real-time-controlled

' time delay, up to a maximum of 400 seconds. The only . other . real-time control•of

the exposure system is the ability to select any one of the four slits in. a fixed

mode. A failsafe slit is ale° provided to protect against system malfunction.

This variable exposure feature • added an additional degree of complexity to mission

planning and operations that was beyond the capability of thalassic XPAN program

.to analyze efficiently. The selection of slits now involved the new considerations

Of time sequence selectiOn and control, and of the dramatic impact on these factors

.created by dispersiOns in orbital parameters. For efficiency, a fully automated

-routine for slit and timing selections was devised, but was found to lack adequate.

flexibility fOr variations to accommodate special requirements; experiments, personal preferences and individual judgement and experience. addition, the fully

automated concept does not lend itself to mission operations support, nor to'readY.

visualization of the expected performance and the relative compromises involved.

•

111111'SPECIAL BANDUNG'

-1-
•

The first attempt to satisfy these inadequacies consisted of expanding the baiic

XPAN program to include a graphic, presentation of an ideal slit width function for

full, intermediate and primary processing levels, plotted against orbit time and

corresponding latitude locations. The plots proved to be so convenient for analysis

and.plimning, and the exposure performance so apparent from the Visual rePresentaflan, that further sophistication of the technique has not been pursued. It has •

Also become evident that the graphic displays are of much value in Ji systeps

planning.

• It is this expanded, graihicp ;PAN technique that is described in the following

paragraphs.

t •

•

Wiener

-The . pe/nmurt7ONUW program outputs two data forms for each condition analyzed. The

basic orbit, camera and illumination data are summarized in listing form for use as

reference and support information as required. This summary includes: A).. GroUnd

velocity and vehicle height with the resulting ground angular velocity (v/h) and

corresponding values of nominal cycle rate, format ground coverage and exposure time

achieved with various selected slits; B) Solar azimuth and elevation with corres-

. ponding ideal exposure times for each processing level; and C) The resulting ideal

..slit width-required to attain the ideal exposure when subjected to'the corresponding

-orbit dynamics. These data are all'summarized as functions of latitude.

The . second output form is a graphic representation of ideal slit width as a. function

of orbit time. As explained previously, these plots have become the "heart" of the

XPAN analysis technique. The time scale is linear in seconds from the ascending ' -

node, with the corresponding latitude ground locations also indicated for ready -

reference. The slit width coordinate is expressed in terms of a "slit-value" (Bv),

which is directly analogous to the concept of exposure value (Bv) such that a change

of 1.0 in Sv represents a change of 1.0 in Bv, which is equal to a change.of one

"photographic stop". 1 The curves plotted in this output form may represent ideal

slit width functions for one film/filter selection at each of three processing levels,

or any'three individual cosibinations of films, filters and processing.

An example of the content and format of these program output data forms is included

as as to this report.

CALCULATIONS 

The calculations included in the total XPAN program are very extensive, and much too

complex to discuss in a brief presentation. It should be sufficient . to describe the

program in terms of the nature of the various calculations that are performed.

'Figure 1.represents a simplified flow diagram of the DAN program calculations. '

An increase in exposure of one "photographic stop" represents a change of 160%,

or twice the exposure. A decrease of one stop is one-half the original exposure.

The concept is summarised by the expression B 2"7p•where B is exposure and By

is exposure value.

'SPECIAL HANDLING

-2-
GROUND ANGULAR VELOCITY ( ViR RATIO).

INC PROPORTIONALITY FACTOR )

. NCKINAL CAMERA I SCANzRATN REQ ID 

IENTIDNAlo EXPOS= TIME FOR PRIMARY, & FULL PROCESS

GROUND vswarrr 

Lima= ma= 

( TS, AS DRUM

I

ACTUAL EXPOSURE

TIME ACHIEVED 

'SOLAR ELEVATION & AZIMUTH 

(APPARENT OBJECT (BRIGHTNESS HOWL

ZNEIZEMMIKATARIMILMICIONIZ.

itgLaigna.

zugarasi . REV., LAUNCH • DATE & TIME 

(PL ING OR ACTUAL)

SLIT WIDTH HEW FOR IDEAL EIEPOSUBH

AT NOM. SCAR RATE 

1

•

(CONVERSION TO) (SLIT VALUES )

FIOURN 3. 
• '

Basicallyi the program. calculates the time profiles of groundvelocity $ height, and

solar elevation and azimuth for the selectelorbit $ pass, and launch time and date.

The ground velocity and height are combined to produce the ground . !mauler velocity

(TM function, from which is calculated the corresponding cycle rate-Which will

:provide properimage motion compeniatiOn. Selected slit widths are then Used to .

',calculate the exposure timed that will be achieved with this profile of computed

cycle retell. The solar elevations are compared with the applicable object brightness model‘, and the resulting apparent luminance profile modified .by the film,

:filter and camera characteristics to produce ideal exposure times for each . processing

level (Primary, intermediate and full). The ideal slit widths are Obtainedby

merely calculating the slit required to achieve the ideal exposure times when constrained by the corresponding computed nominal camera scan rates. ...

These calculations are all very straightforward computations. The utility of the

.results is dependent upon the form and format of the output data presentation. It

was found that plots of. the ideal slit width were inconvenient in that thephoto7

graphic effects of deviations (over-, and under-exposure) could not be quickly

quantitized.. Since the variations in slit width influence exposure'in a logarithf-.

mic manner, it became very convenient. to express the slit width profile as a

logarithmic function. By maintaining the popular-"photographic stop" concept, it

is possible to express the slit width in a function such that an increase of 1.0

directly corresponds to.an increase in E of 1.0, which is. equal to.one "atop".

This function may be stated by:

1/i =28v

8v "g11-111 Log 2 $

Where s = slit width, inches

Sv = "slit value"

which is mathematically compatible with the familiar expressions

1/t = 2 Tv

= 2E7 $ etc.

At any given scan rate (inches per second) in a given camera configuration, the

relationship eliv = h Tv = kakr may be applied. It is therefore possible to.

Obserie directly the magnitude of over- and underrexposuredeviations that would

be introduced by a given alit. It must be cautioned, however, that the difference

in the ideal Sv fUnction at two different. times in the orbit (or at two different

latitude locations) does not represent an equal change in By except in the occasional

instances where the camera'scan rate is unchanged. The awkwardness of transposing

slit widths to Sy values is more than offset by the convenience and ease of evaluation. A given slit will hare a constant By value, and will therefore be represented

by a straight line on the plots.

•

24' The object brightness model is an e‘irical correlation of apparent object .

luminance as a function of solar elevation. The model currently in use is an

-overall average, and does not attempt to account for- season variationsj,if any.

' The model is updated as sufficient support evidence is available. •

11111110ENCIAL HANDLING

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•

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- •

• • The relationship of ST to the exposure profile Of. Ev for an actual mission is

1.Uustrated in Figure 2. The data is taken from the XPAN examples presented in

the appendix. S •

.

. .

DIM TB XPAN P1018 

The XPAN technique of exposure' analysis and evaluation can be applied to all stages

'of mission support; a) pre-flight planning and slit selectiOn 4 b) in-flight operations evaluation and real-time control, and c) post-flight summary of. photCgraphic

performance. The entire exposure control Opitem flight requirements are established*

with this technique, including provisions for experiments and special considerations.

Since the abscissa of the XPAN' plots is linear in orbit time, it is possible to

superimpose the exposure. control' timing sequence directly on the slit function

with freedom of movement along the horizontal axis. In practice, this flexibility

is accomplished by plotting the selected slit values in their proper timing sequence

on a transparent overlay, which can then be positioned along the abscissa as deaired

to-obtain optimum exposure match. This is the technique employed to identify the

.requirements for Brush 51 and 52 5-timer. punch locations (these are the stored program commands that activate the exposure control system timer).

• ktypiCal 'overlay is included in the appendix with the. XPAN output examples * For

.ease in use, the overlay is indexed to the ordinate (slit .value) scale when the .

. • heavy, horizontal reference line near the lover edge of the overlay sheet is super- -

imposed directly over. the horizontal dotted line imeediately adjacent to the time

words on the XPAN plots. Horizontal movement of the overlay is acceptable; however),

the reference lines must remain indexed at all times. • A scale of the real-time con-

.trolled exposure sequence delay ( b.t1) is also included on the overlay for ease in

selecting changes in delay settings, and for rapid identification of the exposure

:• status with previous settings.

Two other points, of significance must be emphasized .in using these plots. First, it

must'be.kept in mind that over- and under-exposure comparisons must be made only

between the ideal slit at some point on the curve and the actual slit alternatives

at : that same point, for the reasons discussed previously. The area above the ideal

slit curve represents exposure less than nominal (under-exposure with respect to the

specific Curve) ) . and the area below greater than nominal (over-exposure). The second

point to remember is that increasing slit values (Sv) represent decreasing slit

widths. The chart shown in Figure 3 provides a convenient and rapid means of relating

slit width and slit value. For a more precise conversion, the pertinent relationships

are:. • . .

ST w 1.43 Ln lis

= 3.322 Log 1/s

= 28T

-1 = Ln (0.693 Sy)

** repe1(o.301 sv)

s= L12-1(..10.693

v

)

Where "s" is slit width in inches.

. .

(Natural logarithm)

(Base 10 logarithm)

(Natural logarithm)

(Base IO logarithm)

-

= Log i(-0.301' Sv) •

and

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111111111SPECIAL HAMDLING

6846o38

Inipection of the sample materials included in the appendix should make.evident

the uses of the =I technique. The more common applicatiOns may be briefly

described as follows: . *

A) Pre-flight 'planning and slit selection is accomplished Using nominal

'planning orbits" for-input parameters. Initial runs will cover a wide '

span of launch times, from which is eventually selected the desired time,

date and orbital configuration. Normal seleätion of slit widths consists

of selecting the 4 values that provide the optimum matching of the appropriateldeal slit width profile over the . areas in which the instruments

will be operated during the life of the mission. This selection must-.

consider the timing limitations of the exposure control system, and the

.possible dispersions in laOnch date and time and in actual orbit. pare- •

.meters, most significant of which is perigee location. The slit selection'

procedure must also considerprovisionslor.special experiments,' mixed

film loads, or other extraordinary conditions, where 60110.031e.

.21) Requirements for starred-program commends and timing intervals for the

exposure controlstem are determined by selecting the timing (within

system limitations

sy

) of the chosen slit values so as to produce an optimum ..

match with the ideal slit profile. The special provision situations previously mentioned must be kept in consideration. The Start commands

(Brushes 51 and 52 on the H-timer) are then located appropriately,. using.

an initial delay interval ( Ss.ti, which is real time commendable) which

will accommodate all reasonable dispersions..

In-flight operations support utilizes real, updated orbit parameters to

obtain XPAN plots for the actual conditions being encountered. By' utilizing

an overlay of the actual slit/time selections it IS possible to make

periodic evaluations of the exposure control performance throughout the

mission and to update the control settings as required. This is achieved

by indexing the overlay along the abscissa ouch that the c&ti position in

effect at the time coincides with the time- locationof the SEC Brush 51.

If a more optimum fit of the selected slits can be obtained by a different

pt. setting, the overlay is moved horizontally to the best fit, and the

system commanded to the AtI position now coinciding with the Brush 51

position. However, it must be remeMbered that these timing shifts are now•

restricted such that the Brush 51 position must always appear within the

limits of the pti delay time range. Real time commanding of any of the

-slits to a fixed positioh for special considerations, or for optimum control at the time, can be evaluated by positioning the various slits on the.

overlay in the area of interest (irrespective of the Brush 51 orientation,

but maintaining the base reference indexing). Fixed slit evaluation can

also be evaluatei by drawing a horizontal line corresponding to the appropriate slit value through the area of interest.

D) Post-flight performance evaluation of the exposure control system combines

the actual orbit parameters and command history with the slit/time settings

and stereo program to graphically depict the exposure history erperienced.

•

ONOWSPECIAL HANDLING

*;-/N.
Stia4ARY

• ..

Though, not highly sophisticated the XPAN technique for exposure analysis for the

CORONA syitem panoramic cameras is very effective in achieving a practical exposure

control, largely as a result of its simplicity of application and the visual con

prehension afforded by the graphic presentations. Perhaps the weakest part of the

analysis is the uncertainties in the object brightness model, which is currently

undergoing further revisions. The adequacy of this graphic analysis is well within

the limitations of the brightness model and the mechanics of the exposure control

system proper. •The XPAN program and analytical technique is adaptable to virtually

effortless revision as improvements are achieved in the model and/or the hardware.

The technique is equally applicable to any application, ranging from single fixed

slit to en infinitely variable exposure control.
•
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? 4-3S.

.

.

14‘I . C"' Summary 8/30/61 -;*1/13/ 1/13/0

6 systems #52 - 57 5r.

4 recoveries from 6 flights

"M" Summary 2/27/62 - 12/21/63 •

26 systems #1 - 26

.20 recoveries from 26 flights

•

?Vr2. -

-F-

 1t.62 54. recoveries out possible from 31

10/9

•

. Za;k flepAravn ENT1 it, "3

.

wgw"J" History

pl3 uCAl spe

144 lethif! SCA4; Systen

PIA ln

rdy

4..i• 7.A-0 56.4.46:

01414.ei

iuSf....yAt, of iv 1.9

„..; 7.:

. -10.

12

11

3••

15

•

17.

/ 13

.4

19

1.0C

21..

20 . 22

154/155 8/5/64 -

152/153 : 9/14/64

160/161 ....- 105/64

156/157 - 10/17/64.

158/159 11/2/64

162/139 '. 11/18/64

138/141, 12/19/6

132/X33.. .: 1/1505 1

140/165 4 -. 2/25/65

122/123 13/26/65 .f

172/173 ,, *--. 9/22/65.'-.

flights

I • 1

. B

•

11/7 ISheared Pins)

11/28 •

• • ,,,,,• • 12/30 "

7. •

. 1/25

.3; . .! • :r! :

.

• -

i A •

.3/4 (S Shatter) i

5/28 (q/On1.)/

6/16 (Oarti.a1). •

7/28 -; ;

8/26 •

S/N R-0

114/115 8/24/63

116/117 9/23/63

124/125 2/15/64

126/143 . 3/24/6k

146/147 . 4/27/64

143/149 6/4/64

144/145 6/19/64

150/157 7/10/64

'•

•

118/119 4/29/65

166/16T S/18/65.

136/07 • . 0/9/65

16/i69. 7/19/65

170/171 . • 8/17/65

A

8/28

9/26

2/18 2/22.

No Orblft

Power Prob. NO. Rec.

6/8.. v. -. 6/13 • .

6/23 6/2/

7/13 . • . 7/17.!

13/8:: • • 8/13/

=9/18 . -, • 9/23!.

•

10/20 10/22 1Veh.)

.;

.- •. 4. I

-•

64.•.: P..*P . ••••, •

P': I

. •

:

•`.___. •

,••

I:: ' ; • .4 1..,..-i.e, ..1%.',..• ;.....z .1 to. 4.1„. e .1.44.is

.7j`.??...f; I'. '`. ...;' 4:•.: . . • '.; 1 '. " • '

Z. kr 7 . r".."*" . .."...'"': '";• . . : `'• %• • 4 : •• s's 1 '

.. '..... . : A. • -. •• 4. . • I:. ..‘'4.14,‘

,

.

,

• .

••

••• • :414/'. I • • -• ••

1.1 : '?

ref-- -

•
• n

System,

JX28,

25 ,

JX27

26

.

S/N

1112/127

174/175

..164/163

176/177

27 178/179

29 1821183

.184/185

28 /0011.4

3 I# • 31 v • 3 . .44 &

11.

, •

I

I

...

I

I

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i THE ko vp4,0,ezom

f,04.4.41

c 'eel;

Akeol.v.fie#4#

-ra '49/ c Iv, Co'

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i ••

•

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•

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;•

.so

A B

•

-:.

-,-;

•

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.....,...

_ 1 f .- ..4

id)/

-1:

't '

6012r /Si F4 heed 110 as/ . i )41,—

451i;t7e niss• (17.4,4reefoi.

/too ithibedo wA2 •CAA.,9.6 a I-

- - • ,

.1028/61

12/9/65

4/7/66

10/10 .10.5

11/2 1117

L. 12/10 (80%) 12111 (Empty)

12/29 1/2

2/7

3/14 3119

4/14 4/18

eivici-/i- Teis eft094-r 4 —S

dee/h/SE ,1r774e IT "/"/ , -

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