apollo experience report photographic equipment and operations during manned space-flight programs

8/8/2019 Apollo Experience Report Photographic Equipment and Operations During Manned Space-Flight Programs

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N A S A T E C H N I C A L N O T E NASA TN D-69ht .

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APOLLO EXPERIENCE REPORT -PHOTOGRAPHIC EQUIPMENT A N D OPERATIONSDURING MANNED SPACE-FLIGHT PROGRAMS

by Helmut A. KzcehnelManned Spacecrafl CenterHouston, Texas 77058N A T I O N A L A E R O N A U T I C S A N D S PA CE A D M I N I S T R A T I O N W A S H I N G T O N , D. C. SEPTEMBER 1972


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1. Report No. 2. Government Accession No.NASA TN D-69724. Titye and Subtitler- POLLOEXPERIENCE REPORT 3. Recipients Catalog No.- - ~~PHOTOGRAPHIC-EQUIPMENT AN D OPERATIONSDURING MANNED SPACE -FL IGH T PROGRAMS7. A u th o rb )Helmut A. Kuehnel, MSC9. Performing Organization Name and AddressHouston, Texas 77058Manned Spacecraft Center

12. Sponso ring Agency Name and Address

5. Report DateSeptember 1972+-. Performing Organization Code8. Performing Organization Report No,

MSC -30910. Work Unit No.924-23-26-00-72

11 . Contract or Grant No.

13. Type of Report and Period CoveredTechnic al Note

19. Security Classif. (of this report) 20. Security C lassif. (of this page)None None

National Aeronautics and Space AdministrationWashington, D . C. 20546

21. No. of Pages 22. Price66 $3.00

14. Sponsoring Agency CodeI

15. Supplementary NotesThe MSC D irec tor wa ived the us e of the International System of Units (SI) for thi s ApolloExperie nce Report , becaus e, in his judgment, the use of SI Units would impa ir the usefu lnessof the report or resul t in excessive cost .The evolution of cre w-op erat ed photographic equipment and the pro ced ure s for manned space-flightphotographic operations are reviewed. The establishment of pr ogr am r equ i r ement s is descr ibed.Photographic operations are discus sed, including prefl ight test ing and infl ight operations .

16. Abstract

* Photography in SpaceOper at ional P r ocedur e s.Photography ApplicationsPhotographic Equipment

~~18. Distribution Statement

* For sa l e by the f ta t i ona l Tec hn ica l In fo rmatLon Serv i ce , Spr lng f le ld , V i rg in la 22151


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CONTENTS

Section Page1UMMARY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1NTRODUCTION1STABLISHMENT OF PROGRAM REQUIREMENTS . . . . . . . . . . . . . . .1hotographic Requirement s . . . . . . . . . . . . . . . . . . . . . . . . . . .3

Ground-Support Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 03 3esolution Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Photographic- Equipment Require ments . . . . . . . . . . . . . . . . . . . .

OPERATIONS 3 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 33 3

Integra tion of Mission Req uirement s and Equipment Capability . . . . . . . .Development of Photographic Procedures . . . . . . . . . . . . . . . . . . .Integration Into Time Line and Flight Plan . . . . . . . . . . . . . . . . . . 35Operational Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 6

37upport of Photography Fr om the Mission Control Center . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37rew DebriefingProb lem Discussion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 8

39ONCLUDING REMARKS AND RECOMMENDATIONS . . . . . . . . . . . . . .40E F E R E N C E S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

APPENDIX- POLLO 1 2 PHOTOGRAPHIC AND TELEVISION PROCEDURESDOCUMENT EXCERPTS . . . . . . . . . . . . . . . . . . . . 41

iii


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TABLE

TableI PHOTOGRAPHIC EQUIPMENT AND APPLICATION . . . . . . . . . . .

FIGURES

Figure12

3

45

678

91011

12

13

The 16-millimeter camera used on early Gemini flights . . . . . . . .The 16-millimeter sequence camer a (used on later Gemini flightsand on the fi rs t Apollo flight) . . . . , . . . . . . . . . . . . . . . .Hasselblad 500c 70-millimeter still cam era with 80-millimeter

lens . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Film magazine for 70-millimeter camera . . . . . . . . . . . . . . .Hasselblad 70-millimeter super-wide-angle camera with38-millimeter lens . . . . . . , . . . . . . . . . . . . . . . . . . .Engineering documentation of EVA on Gemini . . . . . . . . . . . . .The EVA umbilical of Gemini IX . . . . . . . . . . . . . . . . . . . .Gemini VI and VI1 vehicle inspection af ter exposur e to launch andorbital flight(a) First view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(b) Second view . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Agena rendezvous sequence . . . . . . . . . . . . . . . . . . . . . . .Agena stationkeeping and vehicle inspec tion . . . . . . . . . . . . . .Agena docking, showing Agena display panel (just below antenna),which is used as a docking-status indicator . . . . . . . . . . . . .Gemini IX crew station, showing Astronaut Thomas P. Stafford in

the left-seat position and the 16-millimeter camera mountedin the window . . . . . . . . . . . . . . . , . . . . . . . . . . . . .Gemini IX tar get docking adapter . . . . . . . . . . . . . . . . . . . .

iv

Page4

Page1 2

12

1313

131414

14141515

15

1616


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Figure Page14 Engineering documentation of vehicle-tether tests conducted duringthe Gemini Prog ram

16 .16

(a) First view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(b) Second view . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Vehicle inspection during Gemini EVA . . . . . . . . . . . . . . . . . 175

16 The Gemini window taken at a sun angle that acce ntuate s thewindow depo sit s . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1717 Synoptic-terrain and synoptic-weather photography

(a) First view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(b) Second view . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(c) Third view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 171818Spotmeter used in the Gemini Progr am, with exte rna l exposurescale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8 18

19 Hasselblad 70-millimeter electric-drive ca mer a with80-millimeter lens . . . . . . . . . . . . . . . . . . . . . . . . . . 19190

2 1Reseau plate on 70-millimeter data camera . . . . . . . . . . . . . .Hasselblad 70-millimeter electric data camera with 60-millimeterlens mounted to camera , 80-millimeter lens at left, and100-millimeter lens at right . . . . . . . . . . . . . . . . . . . . . 20The 500-millimeter lens used with the 70-mil limet er e lec tr icHasselblad . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2

23

24

25

26

27

2 8

20The 250-millimeter lens used with the 70-millimeter ele ct ri cHasselblad . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20Intervalometer used with 70-millimeter electric Hasselblad to obtainaccurat ely timed s ter eost rip photography fro m lunar o rbit

mul tis pec tra l photography . . . . . . . . . . . . . . . . . . . . . . .control cable . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

. . . . .Mounting of four 70-millimeter electr ic Hasselbla ds for simultaneous,

Lun ar topographic ca me ra sy ste m showing ca mer a, contr ol box, and

21

2 1

21Insta llati on of lunar topographic camera on command module hatchwindow (photograph taken in command module mockup) . . . . . . .

22ervice module damage on the Apollo 13 mis sion . . . . . . . . . . . .V


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Figure Page29 Lunar module mated with S-IVB before LM extraction (photographtaken fr om the command module during docking maneuver) . . . . . 2230 Lunar module in descent configuration as viewed from the commandmodule . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 223 1 Lunar module in ascent configuration before docking with commandmodule . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2232 Lunar module during docking maneuver with command module . . . . 2333 Lunar module docked with command module, showing conditionof LM th ru st er s and skin . . . . . . . . . . . . . . . . . . . . . . . 2334 Command module as viewed fro m the lunar module. Note the highlyrefl ectiv e skin of the vehicle . . . . . . . . . . . . . . . . . . . . . 2335 Lunar module, showing sunglint fr om sur fa ces, which complicat esspace photography . . . . . . . . . . . . . . . . . . . . . . . . . . .36 Handrail evaluation during orb ita l EVA . . . . . . . . . . . . . . . . .37 Use of photographic equipment during EVA operations . . . . . . . . .38 Part of Mare Fecunditatis and the cr at er s Goclenius, Magelhaens,Magelhaens A, and Colombo A . . . . . . . . . . . . . . . . . . . .39 Interior cre w station photographs, showing handling and documenta-tion of equipment in side the command module and gen era l views ofcrewman inside lunar module

(a) First view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(b) Second view . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(c ) Third view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 0 Egr ess of commander fr om LM . . . . . . . . . . . . . . . . . . . . .4 1 Egress of LM pilot from LM . . . . . . . . . . . . . . . . . . . . . . .42 Astronaut sett ing up solar-wind exp eriment. Photograph shows effect

. . . . . . . . . . . . . . .f low sun angle on photographic image43 Lunar module footpad . . . . . . . . . . . . . . . . . . . . . . . . . .44 Surveyor I11 on lunar surface . . . . . . . . . . . . . . . . . . . . . .45 Footpad of Surveyor I11 on lunar surface . . . . . . . . . . . . . . . .4 6 Shadow of LM on lunar surface . . . . . . . . . . . . . . . . . . . . .

vi

242424

24

2525252526

2626222


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Figure474849

50

5152

53

54

555657

58

5960

A- 1

A- 2A- 3A-4A- 5

Earth (photographed during transearth coast) . . . . . . . . . . . . . . 27Moon (photographed during translunar coast) . . . . . . . . . . . . . . 27Window contaminat ion (photograph taken in support of sp ecial-eventsstudy) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28Ecl ipse of t he sun (photograph taken in support of specia l-eventsstudy) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28Apollo 16-millimeter DAC system . . . . . . . . . . . . . . . . . . . 28The 16-millimeter DAC with lens and magazine attached, showingfunctional pa rt s . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28The 16- millim eter lunar s urf ace DAC syste m consisting of c amer a,10-mil limete r lens, cam era handle, battery pack, and mountingbracket . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29Spotmeter used in Apollo Pro gr am showing battery removed fr omhandle and neutral-density filter used to extend the photometerscale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

3030

Data acquisition cam era system tes t console . . . . . . . . . . . . . .Data acquisition camera calibration console . . . . . . . . . . . . . .The 70-millimeter ca mer a test console, showing came ra in position 31or shutter-speed and trac e test

shown on the test stand. . . . . . . . . . . . . . . . . . .

Ground-support and calibr ation equipment fo r the LTC. Ca mer a is 32. . . . . . . . . . . . . . . . . . . . . . .3232

Test se t used to mea sur e functional pa ram eters of LTC . . . . . . . .Spotme ter ground-support and calibration equipment se tup . . . . . .Fr on t s ide of command module pilot ( C M P ) and lunar module pilot 46

46(LMP) cue ca rd . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Back side of CMP and LMP cue ca rd . . . . . . . . . . . . . . . . . .47ro nt s ide of LMP cue car d . . . . . . . . . . . . . . . . . . . . . . .47ame ra settings for EVA photography . . . . . . . . . . . . . . . . .47he DAC field of view fro m c ra sh b ar positions 1 and 2 . . . . . . . .

v i i


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FigureA- 6

A- 7A- 8A-9

A- 10A- 11A- 12A- 13

PageAllocation of equipment and fi lm(a) Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 8(b) Film . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49Electric Hasselblad/C EX . . . . . . . . . . . . . . . . . . . . . . . . 55Electric Hasselblad/BW . . . . . . . . . . . . . . . . . . . . . . . . . 5Hasselblad data camera/HBW . . . . . . . . . . . . . . . . . . . . . 5Hasselblad data camera/HCEX . . . . . . . . . . . . . . . . . . . . . 5The CSM data acquisition camera . . . . . . . . . . . . . . . . . . . . 5The LM data acquisition camera . . . . . . . . . . . . . . . . . . . . 5Spotmeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5


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APOLLO EXPERIENCE REPORTPHOTOGRAPHIC EQUIPMENT AND OPERATIONSDU RIN G MANNED SPACE-FL IGHT PROGRAMS

By H e l m u t A. K u e h n e lM an ne d Spacecraf t Cen te r

S U M M A R Y

Photographic equipment has been carr ie d on board manned space craft fr om thefi rs t orbital flight to the pre sen t time. The photographic req uirem ents have incr easedwith mission complexity. The photography obtained has become a n important part ofth e technical data fo r each manned spac e flight and has been a major s ou rce of informa-tion to the world on the progress and accomplishments of the U. S. manned space-flightprogram.INTRODUCT ION

The evolution of photographic equipment and the procedures for manned space-flight photographic operations a r e reviewed in this report. This repo rt shows how andwhy the equipment and pro ced ure s we re developed fr om one pro gra m to the next. Thest atus of photographic equipment a t the majo r mil estones in the manned space-flightprogram is summarized.

ESTABLISHMENT OF PROGR AM REQU IREMENTSPhotograph i Requi eme nts

Fr om the time of the first manned orbital flight in Pro ject Mercury to the present,space-flight photographic equipment and photographic operations have greatly matur ed.The photographic equipment, the photographic procedures, and the accompanying opera -tions have developed in keeping with the requirements of the var iou s space-flight pro-gr am s. During Pro jec t Mercu ry, the consumables (for maneuvering), allowable weight,tim e, and sp ac e fo r photographic equipment were very limited. Ther efore , manyworthwhile photographic requirements could not be fulfilled. However, on the fi rs tMercury o rbita l mission, a hand-held camera w as carried, and interesting documentaryand scientific photography was obtained. During Pro jec t Mercury, no for mal proce -dur es existed for the acceptance, evaluation, an d incorporation of photographic


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requirements. Suggestions were made (informally) directly to the training and flightplanning organizations by per sonnel both within and outside of the sp ac e tas k group.These suggestions were incorporated as well as possible into the inflight activities.During the latt er par t of Pr oje ct Mercury, however, the photographic experimen tswe re somewhat more formalized; the accomplishment of photographic objectives wasprimarily a function of how much photographic activity could be incorpora ted into theflight plan.After t h e Mercury 6 mission, which proved that man can operate in spac e and he c an accomplish at least som e photography fr om his crowded spacecr aft with all thexisting restr ictio ns, the number of photographic requ ireme nts w a s increased, andconsiderat ion was given to expanding the photographic capability. On the Mercury 7and 9 missions, horizon-def inition photography was obtained in support of navigationsys tem s studies; and, on the Mercury 9 mission, dim-light-phenomena photography obtained. These experiments a r e noted as the first examp les of organized scientificoriented photography in the manned space-flight program. The most extensive photographic experiments, however, consisted of the weather and te rr ai n photography stainformally on the Mercury 6 mission and formally on the Mercury 8 and 9 missions.This photography started a catalog of synoptic-weather and synoptic-terrain photogra

that was continued during the Gemini P rog ram . The result s of these experiments arsummarized in referenc es 1 to 4.Throughout the Gemini Progr am, photographic req uir eme nts of two types we reestablished: (1) the operational and documented photography and (2 ) scientific photography. The evolution of experimen t-requirement s organ izations is summarized inreference 5.Fr om the beginning of the Gemini Pr og ra m through the Gemini VI11 mission, thphotographic requirements were stated in the flight plan in gene ral te rm s. As the interest in and demands fo r photography incre ased, it was deemed neces sary to delinethe photographic plan more specifically; consequently, a documented photographic pl

was introduced with the Gemini M mission. The purpo ses of thi s plan we re to definthe photographic requi rem ent s of the miss ion and to specify th e photographic equipmto be used. The photographic plan se rved as the for mal documentation for missionphotography.A significant in crea se in the photographic-equipment capability was re qui red inthe Gemini Pro gra m to make permanent r ec or ds of maneuvers during extravehicularactivity (EVA), docking dynamics, docked-vehicle dynamics, and tethered-spacecrafdynamics. Experiment photographic req uir eme nts are summarized in references 5and 6. The operational photographic req uir eme nts we re dictated by the mission re-quirements and objectives, as stated in ref erenc es 5 and 6. Photographic requiremin support of mission r equ ire ments will be discussed later in mor e detail, along wit

photographic equipment.The Apollo Pro gra m i ncre ased the demand fo r broader photographic requiremPhotographic requ ireme nts became mor e for mal , and the photographic plan was madcon tro l document. The plan w a s reti tled th e photographic and television proced uresdocument. Again, as in the Gemini Program, the operational photographic require-ments were dictated by the miss ion req uirem ents . However, an entirely new scienc(lunar mapping fro m orbit and lunar su rf ac e geology) became a part of the photograp

2


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requirements in the Apollo Program. The photographic req uir eme nts are usuallyrouted through the mission r equ ire men ts document to the photographic and televisionprocedures document. Photographic requirements and procedures a r e controlled bythe photographic and television procedu res document, which in tur n fur nis hes inputs tothe mission flight plan and onboard data.The additional requi rem ent s placed on photography in support of t he ApolloPr og ra m include detailed vehicle inspection, crewman mobility inside the vehicle, lunarsurf ace and specif ic-area mapping to support landing-site selection and determination,lunar surfac e crew-operational st udies, luna r-tr aver se and sample-collection documen-tation, inspect ion of vehic les on the lunar sur fac e, and many othe r engineer ing- andscience-related photographic documentation tasks. Det a i l s of the se photographic re-quirements are listed in the photographic and television procedures documents for eachmission. (Selected port ions of the Apollo 12 photographic and television proc eduresdocument are presented in the appendix to i llu str ate the mission documentation and de-gr ee of det ail requ ire d to conduct a successfu l photographic mission. ) The photographicand television procedures document is an operational document that p re sent s the photo-graphic objectives, crew procedures, cam era us e and exposure settings, time-line

integration and equipment, and spacecraft stowage descriptions.Photographic-Equipment Requirements

Photographic equipment has evolved during the manned space-f light pro gra m inaccordance with the photographic requirements or objectives. The major photographicequipment used on each manned spac e flight from Mercury 6 to Apollo 13 is shown intable I, as are film types and equipment applications. During Pro jec t Mercury, thephotographic-equipment requ ireme nts were conservative. On the first two Mercuryorb ita l flights, 35-millimete r ca mera s modified by NASA to be crew compatible wer euse d fo r miss ion documentation and fo r recording phenomena of int ere st o r of a n un-usual nature at crew discretion. The potential for orbi tal photography w as recognizedin reviewing the photography obtained on the Mercury 6 and 7 missions. More extensiverequ ireme nts we re established for synoptic-terrain, synoptic-weather, and horizon-definition photography. Theref ore , a 70-millimeter- f or mat professional-quality cam-e r a w a s needed. The Hasselblad 500c camera w a s chosen as the basic camera.Modifica tions by NASA included removing the ref lex viewing sys tem and dechroming thecomme rcial unit. Synoptic -ter rain , synoptic-weather, and horizon-definition photog-raphy was required on the Mercury 8 and 9 missions to support future navigational sys -tem studies. In addition, dim-light phenomena we re studied on the Mercury 9 mission;therefore, a specially equipped 35-millimeter camera with high-speed lens w a s providedf o r that requirement.

A 16-millimeter camera w a s carried on the Mercury missions to photograph thecrew man's rea cti ons to the new environment and to obse rve the instrument panel. Thepilo t-ob serv er cam era yielded particular ly significant data on the crewman's reactionto launch accelera tion s and zer o gravity and also on the crewman's position in the re -st ra in t sys tem . The photographic data were useful in the design of r es tr ai nt sy st em sfo r following miss ions . Fu rthe r information on the Mercury photographic operationsand results is contained in references 1 o 4.

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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION~~

Equipment Film size , mm Lens size, mm Film Task/targetMercurv 6

Ansco Autoset Eastm an color negative, Ter rai n, weather, sunsetI stock number 5250 I phenomenaMercurv 7Robot Recorder 35 55 Eas tman color negative, Ter rai n, weather, horizon def-inition, sunset phenomenatock number 5250

Mercury 8Hasselblad 70 80 Super Anscochrome D-200 Terra in, weather, sunsetphenomena

Mercury 9Hasselblad 70 80 Ultraspeed Anscochrome, Terr ain, weather, horizonFDC 289, D-200 defi niti onRobot f/O. 95 35 _ - _- Dim light

Gemini 111HasselbladMcDonnell motionpicture camera

McDonnell motion 5, 18, 75, and 25picture camera

Hasselblad

McDonnell motionpicture cameraSpotmeter

70

16

N A ~

I 70Hasselblad

Special or der (SO-2 17)SO-217 Crew activity (for evaluation)

Terrain, weather

n i O-217V Earth strip

SO-217 (black and whitewith red-blue filter)

SO-217

Gemini V80 SO-217

Ansco color reversal (D-50)

5, 18, 75, and 25

N A NAIGemini VI1

80

Terrain, weather, stereo-scopic coverage, EVA (fordocumentation and analy-sis), earth-limb definitionEVA and maneuvering unit

(for evaluation)

Terrain, weatherZodiacal light, airglow,spectrophotographyCrew activity (for evaluation)

Exposure value upgrading

SO-217Ektachrome infrared( I R) 8443Panatomic-X 3400Kodak 2475

Terrain. weatherVisual-acuity sitedocumentationDim lightDim light

4

aNot applicable.


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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - Continued

McDonnell motion 16 5, 18, 75, and 25 SO-217picture camera

Spotmeter N A ~ NA NA

Crew activity (for evaluation),rendezvous (for documenta-tion and analysis), station-keeping (for dynamic sevaluation)Exposure value upgrading

~

Hasselblad

N A

Maurer sequencecamera

Exposure value upgrading

70

16

802 5 0

5, 18, and 7 5

N Apotmeter N A1Gemini VIII

Kodak 2475 I errain, weatherSO-217

SO-217

Rendezvous (documentation),vehicle (inspection), dimlightRendezvous (relative-motionanalysis), vehicle(inspection)

Hasselblad 70

1aurer sequencecameraSpotmeter N A

80

5, 18. and 75

N A

HasselbladHasselblad SuperWide Angle (SWA)Maurer

Maurer sequencecamera

7 07 0

7 0

16

16

8 038

8 0 and 50

75

18

5

SO-217

- -

N A

Agena docking (engineering andevaluation), terrain, weatherRendezvous and docking, sepa-ration, vehicle (dynamicsanalysis)Exposure value upgrading

Gemini M-ASO-217SO-217

SO-217

SO-217

SO-217

SO-217Gemini X

Maurer 73 (ultra viole t (uv)) Kodak 1-0with uv objectivegrating and 50Hasselblad S W A SO-217

'%ot applicable.

Terrain, weather (Agena, EVA)Agena. EVA

Terrain, weather, zodiacallight, airglowRendezvous to 5 0 feet

Agena. EVA, rendezvous from50 feetEVA

S- 13 (uv astronomical photog-raphy), zodiacal light,airglowEVA, terrain, weather, Agenaservice propulsion system(SPS).Agena stationkeeping

5


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Equipment Film size, mm Lens size. mm Film Tasktarget

~

l au rer

daurer sequencecamera

70

16

Iasselblad SWA

80

daurerdaurer

daurer

SO-217

daurer sequencecamera

75

18

5

vlCDOMell motionpicture camera

lasselblad

SO-217

SO-217

Kodak 2475

SO-217

vlaurer

daurer sequence

70

7070

70

16

16

16

Gemini X - Concluded

38 SO-368

8073 uv (uv grating.uv prism)

80

75

18

SO-368Kodak 1-0

Kodak 103 ( 1 magazine)SO-166 (Kodak 0-85)

SO-36

SO-368

Ektachrome 2475( 2 magazines)SO-368

SO-368

Gemini xn70

70

80

80SO-368

SO-368Ektachrome 103DI 50 I

~~

Terra in. weather, AgeM SPSthru ster plumes. Agenaprimary propulsion system(PPS) burn

Rendezvous, final separation.MSC-12 andmark contrast

Rendezvous (50 feet to docking).bending-mode check, PPSburn. EVAS-26 (Agena ion-wakemeasurement)EVA

Terrain. weather. EVA. ter-rain fr om high altitude,Agena operationsTerrain. weather5-13 (uv astronomicalphotography)S- 1 1 (airglow photography)S- 29 (libration- region photog-raphy) - planned but notperformedRendezvous

Rendezvous and docking, S-26(ion-wake measurement),Agena PPS burn, dockingpractice, EVA, tetherevaluationS-26 (ion-wake measurement)

EVA (camera mounted outsidespacecraf t )ipollo sump-tank

S-5 (ter rain ). S-6 (weather).Agena opera tions

S- 5 (terrain), S-6 (weather)S- 11 (horizon airglow)S-29 (libration regions), S-51(sodium cloud) - no datareturn

6


15/67

TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - ContinuedEquipment Film size, mm Lens s ize, mm Fi lm Taskharget1

Gemini XI I - Concludedvlaurervlaurer sequencecamera

iasselblad

klaurer sequencecamera

relevision

3asselblad electric(EL)

1673 uv75

18

5

Spectroscopic 1-0SO-368

SO-368

SO-368Apollo 7

70

80

18and 75

SO-121 ( 6 magazines)

Panatomic X 1 magazine)SO-121 (5 magazines)

Kodak E F (7 magazines)-I I NAApollo 8

80

25 0 (mediumtelephoto)

50-368 2 magazines)

SO- 2 1 ( 1 magazine)

Kodak 3400 (3 magazines)

Kodak 2485 (1 magazine)

SO-368s o - 1 2 1Kodak 3400

S-13 astronomical uvspectroscopy)Rendezvous and formationflying, S-51 support dataDocking, undocking, formationflying, tether operations,entryEVA (c am er a mounted outside)

Simulated docking. s pace cra ft-LM adapter (SLA), windowcoating, terrain, weatherS- 5 (terrain), S-6 weather)Simulate d docking, SLA, ren -dezvous and SLA, windowcoating, terrain, weatherIntravehicular activity ( NA )Crew and spacecraft interior,earth

Earth (long distance), moon(long distance). lunarsurface targets, stereo-scopic stri pEar th (long distance), moon(long distance). lunarsurfaceLunar stereoscopic strip,lunar landmarks. e arth(long distance), moon(long distance), solarcorona, lunar surface tar-gets, lunar surface (red-blursurface study)Spacecraft exterior atmos-phere, lunar surface inearthshine, transient lumi-nescent phenomena, gegen-schein, zodiacal lightLunar surface target s. moon(long distan ce)Moon (long distance)Lunar terminator. image-motion-compensation ( I M C)training, moon (long dis-tance), lunar surface target:zer o phase angle

aNot applicable.

7


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Equipment Film size. nini Lens s ize. n i n i Film Task/targetIData-acquisitioncame ra (DAC)

Television

Hasselblad

Hasselblad SWA

DAC

Multispec tracamera (fourganged ELHasselblads)Television

16

N A ~

7 0

70

1 6

70

NA

2 0 0

75

18

5

_ _Apollo 9

8 0

3 8

75

1 8

5

8 0

- -

S O -3 6 8 (9 magazines)

S O -3 6 8

S O - 3 6 8

S O - 3 6 8

S O - 1 6 8 ( 2 magazines)NA

S O - 3 6 8

S O -3 6 8

SO- 16 8S O -3 6 8

S O - 3 6 8

S O - 3 6 8

SO- 1 6 8SO- 368. SO- 24 6 ( blac k-and-white IR). SO- 1 8 0 (colorIn). Ektachrome 3 4 0 0

NA

IMC training. ear th and moon(long distance)Earth and iiioon (long distance).lunar surfaceSeparation and Saturn IVB(S- NB) inspection. lunarsurfac e. earth and moon( l o n g distance)Exhaust effects on commandmodule (CM) windowsCrew activit iesCrew and spacecraft interior.earth and moon from lunarorbit

S - I V n 'SLA'LM (inspection).docking. EVA (fro m CM).LM (f ro m CM). LM landinggear. 1.M from C M an d C Mfrom LM during docking.ter rainDrohue-impact damage. EVAfrom 1. M porch. docking.weatherInterior crew activit iesAscent propulsion systemburn to depletionS-N~/SLA/LM inspect ion) .docking. LM ejection.docking target duringthird SPS burn. L M landing-gear de1)loynient. descentpropulsion system plumejettfronison .M). undocking. LM

Extravehicular transfer from1.M l o CM and return

Interior crew act wit iesMu I t ispc~ct a t e r r a npllotugrallhy

~n t e l ' l ~ l rf CM and LM. EVAaNot applicable

8


17/67

TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - ContinuedEquipment Film siz e, mm Lens size , mm Film Task/target

Apollo 10Hasselblad EL

Hasselblad EL

DAC

Television

Hasselblad EL

DAC

aNot applicable.

70

70

16

N A ~

70

16

80

25 0

7518

5

Apollo 1 180

250

80

7518

5

10

SO-368

SO-368

SO- 68SO-368

SO- 68

NA

SO-368

SO- 68 (LM)

SO-368

3400

3400

SO- 68SO-368

SO- 68

SO- 68

Transposition, docking, andextraction ( T D & E ) ; S-IVB/SLA/LM (inspection); lunarsurface targets; undocking;LM (inspection); rendezvousEar th (long distance), lunartargets of opportunity, moon(long distance)RendezvousTD&E, S-IVB/SLA/LM (ins pec -tion), undocking, LM (ins pec -tion), rendezvous, lunarsurfaceIntravehicular transfer(commander), cr ew activ-i t ies in spacecraftTransposi tion and docking,spacecraft interior, undock-ing, lunar targets

Earth from high altitude aftertranslunar injection, trans-position and docking, earthand moon, undocking, LM(inspection), lunar targetsLunar s urface through LM

windowEar th and moon (long distance ),lunar targetsMoon (long distance), luna rtargets. landed-LM locationLunar mapping (strip. CM).lunar sur face through LMwindowRendezvous. lunar targetsTD&E. undocking. LM (ins pection). rendezvous. dockingCrew. spacecraft interior.

entryDescent a s seen through LMwindow (60 00 feet to touch-down). EVA. ascent. CM atrendezvous

9


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I Task targetquipment Film size, mm Lens size, mm FilmApollo 1 1 - Concluded

~~

Zloseup stereo-

relevision (CM)scopic camera

relevision (lunarsurface)Hasselblad datacamera (DC)

fasselblad E L

)AC

Iasselblad DC

:loseup stereo-scopic camera'elevision (CM)

aNot applicable.

--N A ~

NA

70

70

16

70

- -N A

Apollo 1280

2 5 0

500

18

51 06 0

- _- -

S O -3 6 8

NA

NA

SO- 16 8

S O -3 6 8

3 4 0 0

S O -3 6 8

3 4 0 0

S O -3 6 8

SO- 16 8SO- 16 8S O -3 6 8SO- 16 8

S O -2 6 7

5 0 - 3 6 8

N A

Lunar surface details

Earth. moon, Spacecraftin ter ior , crewEVA, lunar surface. LM onsurfaceLunar surfac e, LM. crewmenduring EVA, deployedexoeriments

TD&E. earth, moon, undock-ing. lunar targ ets . FraMauro, rendezvou s anddockingVertical s tereoscopic s t r ip ,moon (long distance). luna rtargetsEarth and moon (long distance ).lunar targe tsHigh-resolution oblique photog-raphy of Lalande, Descartes,and Fra MauroTD&E. undocking. rendezvousand docking. LM jettison,high-resolution obliquephotography (concurrentwith Hasselbla d E L with5 0 0 - m m lens)EntryInterior crew activit iesL M descent. EVALunar surface during EVA,Apollo lunar surf ac e exp eri-ments package. LM.crewmenLunar geological targets. sam-ple documentation.Surveyor IIILunar surface details

Transposi tion and docking.intravehicular transfer,spacecraft interior.lunar surface. undocking.formation flying. docking.ear th

10


19/67

TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - Concluded

--

~~

Equipment Film size, mm Lene size, mm Film I Task/targetApollo 12 - Concluded

3400, 3401, SO-246 (IR) Lunar surface targets ( f romI CM)1I NAaTelevision (lunarsurface)

Multispectral cam -era (four gangedHasselblads)--

Hasselblad EL

Hasselblad DC

DACBattery-operatedDACTelevision

Lunar topographiccamera

7 0

70

1 616

NA

b5

-- Cre wme n durin g EVA, LM,lunar surface (Camerafailed during firs t EVA. )

Apollo 1380

25 06 0

80181 0

75

--b18

SO-368

SO-368SO-168

SO-168230-368SO-368

5 0 - 3 6 8

3400

NA

Transposition and docking,moon (long distance) ,serv ice module, s pacecraftinteriorWeather, s ervic e moduleLunar surfa ce during flyby,service moduleService moduleTransposition and dockingCrew and spacecraft interior

Service module aft erseparationSpacecraft interior and intra-

Not used because of ear lymission termination

vehicular transfer

aNot applicable.bInches.

In the Gemini Pro gra m, equipment was requi red to continue the synoptic-terraina requirement for a motion picture cam era to document the dynamic near -spa ce opera-tions (such as EVA, rendezvous, and docking) and to provide a continuous photographicst ri p of the earth fo r us e in corr elat ing the sti ll photographs. Consequently, a low-fra me- rat e motion picture camera , later to be r epl ace d by a sequence camer a, becamepart of the Gemini ca me ra inventory. The motion picture c am er as generally had acomplement of three lenses: a 5-millimeter lens for close-range wide-angle photog-raphy re qui red fo r EVA and crew station operations, an 18-millimet er lens requ ired formoderate-range photography (such as during docking), and a 75-millimeter lens re-quir ed for longer ran ge photography (such as photographs taken during rendezvous and

and synoptic-weather experiment s begun in Project Me rcury; however, there was also

ground strips) .

11


20/67

The first motion picture ca me ra used in the Gemini Pr og ra m (fig. 1)had a single-f r a m e rate of 6 fr am es per second and a fixed shut te r spe ed of 1/125 second, and wa soriginally battery operated. Later , this cam er a was modified to opera te with space-cra ft power, which considerably improved the fr am e- ra te and shutter-speed accuracy.However, t h e camera still lacked the flexibility requi red f or the p ro gr am photography.Consequently, early in the Gemini Prog ra m, procu remen t of a mo re flexible and ac-cur ate sequence cam era was initiated. The sequence camera incorporating fram e ratesof 1, 6, and 16 f ra m e s p e r second and shu tte r spe ed s of 1/50, 1/100, 1/120, and1/250 second (fig. 2) was introduced for the Gemini VI mission. The came ra fr am erate wa s independent of shutt er speed, unlike nor mal cinematic ca me ra operation. Thi scam er a was used on later Gemini flights and on the f ir st Apollo flight.

.'

Figure 1. - The 16-millimeter came raused on early Gemini flights. Fippre 2 . - Thc 16- millimeter sequencecamera (used on later Gemini flightsand on the first Apollo flight).Three types of still cameras were used in the Gemini Program (table I ) .The 70-millimeter Hasselblad 500c cam era , modified fo r space-flight us e (fig. 3), wasthe pri mar y ca me ra used fo r the synoptic-weather and synoptic-t errain photographyin the Gemini Prog ra m. Photography obtained with this c am er a contributed significantlto the program, as reported in reference s 7 o 13. A magazine for the 70-millimetercamera is shown i n figu re 4. On the Gemini M o XI1 missions, a 70-millimeterscientific ca mera and a low-light, ultraviolet lens to meet specific experiment requi re-ments wer e introduced. Valuable photographic re su lt s we re obtained (ref. 5); however,the cam er a did not provide the requ ire d reliability and was later abandoned. A thi rdstill camera, the 70-millimeter Hasselblad super-wide-angle ca me ra with 38- millimetelens (fig. 5), wa s introduced fo r the Gemini M mission to fulf ill the wide-angle photo-graphic re quir ement s of EVA and al so to provide wide r angle ground-coverage data insupport of synoptic- ter rai n and Synoptic-weather req uir eme nts . Some of the mostvaluable and widely published photography of the Gemini Program was obtained with this

.

12


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Figure 3. - Hasselblad 500c70- millimeter still cameraw i t h 80-millimeter lens.

Figure 5. - Hasselblad 70-millimetersu per -wide-angle cam era with38 -millimeter lens.

Figure 4. - Film magazine for70-millimeter camera.

sys tem. Reference 8 contains a summary of later Gemini photography.ground-support equipment is discussed later. Representative still photographs takenduring the Gemini mis sions in support of the photographic requir ements for engineeringdocumentation, experiments, and vehicle inspection a r e shown in figures 6 to 1 7 .

The required.

1 3


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F i g u r e 6 . - Erigineering d o c u m e n t a t i o nof EVA 011 G e m i n i m i s s i o n s .

(:I) First v i c w . ( t ) ) Sccotid v i e w

1 4


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-Figure 9 . - Agena rendezvous sequence.

Figure 10. - Agena stationkeeping andvehicle inspection. Figure 11. - Agena docking, showingAgena display panel (just belowantenna), which is used as a docking-status indicator.

1 5


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Figure 12 . - Gemini IX crew station,showing Astronau t Thoma s P.Stafford in the left-seat positionand the 16-millimeter cam eramounted in the window.

(a) Fi rs t view.

-7

(b) Second view.Figure 14. - Engineering documentationof vehicle-t ether te st s conducted dur

ing the Gemini Pr ogr am.

Figure 13.- Gemini IX target dockingadapter.

1 6


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Figure 15. - Vehicle inspection during Gemini E V A .

T

(a) Fi rs t view.Figure 17. - Synoptic-terrain andsynoptic- w eather photography .

Figure 16. - The Gemini window takenat a sun angle that accentuates thewindow deposits.

17


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L - 4

(b) Second view

.

Figure 1 7 . - Concluded.A spotmeter (fig. 18) was firs t in-troduced to the manned space-flight inven-tory on the Gemini V mission for thepurpos e of measurin g light values in sit ua-tions in which light prediction was difficult,fo r example, inside the spa cec raf t and on

areas of specific interest on a target vehi-cle. One example of the usefulness of thespotmeter was on the Gemini IX missionduring photography of the fai led dockingadap te r, when engineering photography w a srequ ired of deta iled pa rt s of the vehicle.An example of thi s photography is shown infigure 13 . The spotmeter w a s als o ex-tremely useful in confirming predictednominal exposure values over differentearth surfaces such as water, desert, andvegetation at various sun angles.eral problem of exposure determinat ionw i l l be discussed later.

The gen-

The photographic re qu irements of theApollo Program necessitated the upgrading

(c) Third view.

Figure 18. - Spotmeter used in theGemini Pro gra m, with extern alexposure scale.and expansion of photographic equipment us ed for the Gemini Program.Pr og ra m requir ed photographic equipment of sufficient quality to upgrade the avail abllunar maps and to map a r e a s of the moon as an aid in landing-site selection.

The ApolloAlso,

18


27/67

landing-approach s tr i p photography was required for crew training. Documentation andphotogrammetric data of lunar surf ace features and of collected sam ple s wer e requi redf or lunar geology. Continuous photography of the lunar module (LM) descent and as centwas req uir ed to aid in LM landing-site location analy sis. Vehicle-inspection photog-raphy was requir ed during the LM engineering mis sions to determine that all vehiclessuffe red no damage during separati on, docking, or rendezvous and that the landing gearon the LM deployed properly.To meet the requi rement s of the Apollo Pro gra m, the 70-millimeter sti ll cam-eras, the 16-millimeter sequence cam era , and the spotmet er wer e upgraded; the70-millimeter data cam er a (DC) and the 5-inch-format lunar topographic ca me ra wereintroduced; and various lense s wer e added (table I) . Also, a change was made to themodified Hasselblad ele ctr ic ( EL) ca mer a (fig. 19), which is a motor-driven camerarequi red for the lunar s tr ip photography and for crew operation on the lunar surfac e.The modification work was contracted to the c ame ra manufac turer which resul ted inincre ased product control and quality. Camera subc ontra ctors were al so brought intodir ect involvement and handpicked the optics and assem bled specia l sh utt ers fo r theNASA cameras. A special vers ion of the Hasselblad 500 EL ca me ra with a newly de-signed 60-millimeter lens and reseau plate (fig. 20) was produced and was designated

the Hasselblad DC. Thi s ca me ra was intended initially fo r photo gramm etric work onthe lunar surfac e and later fo r orbital mapping. The 70-millimeter DC is fitted with(1) a glass rese au gr id at the film plane and a special 60-millimeter lens for lunar su r-fa ce geo logical and e ngineering photography, (2) an 80-millimeter lens for orbital

fFigure 2 0 . - Reseau plate on70-millimeter data came ra.

Figure 19. - Hasselblad 70-millimeterelectric- drive cam era with80-millimeter lens.

19


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photography. and ( 3 ) a 100-millimeter photogrammetric-quality fixed-focus lens fo rorbi tal mapping.inventory, the lens is expected to be used on the later Apollo missions.Although the 100-millimeter lens has not been made part of the flight

This equipment has yielded outstanding photographic re su lt s and has operatedreli ably in the lunar envi ronment. The appendix contains additional desc ript ions of theApollo 1 2 photographic equipment. The basic s ti ll camer a equipment used in the ApolloProgram is shown in fi gu re s 21 to 27. Represen tative photographs taken with the70-millimete r sti ll cam er as in fulfillment of the photographic objectives a r e shown infigures 28 to 50 .

--Figure 2 1. - Hasselblad 70-millimeterelectric data camera with60-millime ter lens mounted to cam -er a, 80-millimeter lens at left, and100-millimeter lens at right.

Figure 2 3 . - The 250-millimeter lensused with t h e 70-millimeter electricHasselblad.

20

Figure 22. - The 500-millimeter lensused with the 70-millimeter elec tricH a s selblad.Upgrading of the 16-millimeter se-quence came ra s used in the Gemini Pro gra m

resulted in the 16-millimeter data acquisi-tion ca mer a (DAC). The sequence modeswer e changed to 1, 6, and 12 fra mes per sec-ond, and a 24-frame-per-second cinematicmode was added. Shutter spee ds we rechanged to 1/60, 1/125, 1/250, 1/500, and1/1000 seco nd. The DAC had inc rea sedfilm capacity, improved accu racy of fra mera te and shutter speed, and improved reli-ability and ruggedness. Lens es fo r the16-millimeter DAC wer e standardized forthe Apollo Program, and a 10-millimeterlens and a 180-millimeter lens were addedto the inventory. The new lens es, alongwith the upgraded cam er a body, significantlyimproved the 16- mil lim ete r-c ame ra photo-graphic quality and flexibility.


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Figure 24. - Intervalometer used with70-millimeter electric Hasselbladto obtain accurately timed stereo-st ri p photography fro m lunar orbit.

Figure 26. - Lunar topograpnlc camerasystem showing camera, control box,and control cable.

Figure 25. - Mounting of four70-millimeter electricHasselblads for simultaneous,multi spect ral photography.

Figure 27. - Installation of lunar topo-graphic camera on command modulehatch window (photograph taken incommand module mockup).

2 1


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Fihwre 2 8 . - Service moduledamage on the Apollo 13mission.

Figure 30. - Lunar niodule in descentheonfiguration as vicwcd fromc om ma nd niodu le .

22

Figure 2 9 . - Lunar module mated withS-IVB before L M extraction (photo-graph taken from the command mod-ule during docking maneuver ).

Fibpre 31. - Lunar module in asce ntconfigura tion before docking withcom man d ni odu le .


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1

Figure 32 . - Lunar module during docking maneuver with command module.

Figure 3 3 . - Lunar module docked with Figure 3 4 . - Command module as viewedhighly refl ect ive skin of the vehicle .comma nd module, showing condition fr om the lunar module. Note theof L M thr us te rs and skin .

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Figure 3 5 . - Lunar module, showingsunglint from surfaces, whichcomplicates space photography.

Figure 3 7 . - Use of photographicequipment during EV Aoperations.

24

Figure 36. - Handrail evaluation duringorbital E V A .

Figure 38. - P a r t of Mar e Fecunditatisand the c r at e r s Goclenius, Magel-haens, Magelhaens A , and Colombo


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(a) Firs t view. (b) Second view

( c ) Third view.Figure 39. - Interior crew station plioto-gra phs , showing handling and docu-Inen a ion of equip iieii inside t liecoiiiniaiid iiiodule and general viewsof crewiiiaii iiiside lunar iiiodule.

Figure 40 . - Egress of conixiianderfroin L M .

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Figure 4 1 . - Egress of LM pilotfrom LM.

Figure 4 3 . - Lunar module footpad.

Figure 4 2 . - Astronaut sett ing u p solar-wind expe rimen t. Photograph s h o w seffect of low sun angle 011 photographiimage.

Figure 4 4 . - Surveyor 111 0 1 1 lunarsurface.

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Figure 45. - Footpad of Surveyor I11on lunar surface. Figure 46. - Shadow of L M onlunar surface.

Figure 4 7 . - Ear th (photographed duringtransearth coast) . F i p r e 4 8 . - Moon (photographed durin gtranslunar coast).

27


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Figure 4 9 . - Window contamination (pho-tograph taken in support of specia l-events study). events study).

Figure 50. - Eclipse 01 the sun (photo-graph taken in support of spec ial -

The flexibility of this equipment has p roved to be a substanti a1 as se t t o the overalApollo photographic program in that, when camera equipment was committed to COII-tr ac t, a l l the photographic requi reme nts were not defined. However, such things asadditional lenses, calibrate d fr am e ra te , and data output (for 70-millimeter-photographcorrelation) were designed into the system; thus, a wide variety of new photographicrequirements w a s relatively easy to accomplish. The Apollo 16- milli mctcr c am er asystem is shown in f i w r e s 51 to 53.

1 6 - m m D A T A A C O U l S l T l O NC A M f R A . SEB 3 3 1 0 0 10 0[RIGHl ANGLE MIRROR

SE B 3 3 1 0 0 0 5 118-mm-LfNSSf B 3 3 l O O O l 8 7

/m-/v/ - --100056 /RING SIGHT 1 m m D A l A A C O U l Sl T lO N C O N l R O LSEB 1 3 1 0 0 0 3 1 M A G A Z I N E SF8 3 3 1 0 0 1 2 5 S E B 33100010

Figure 51. - Apollo 16-millimeter DACsystem.

28

a , * 1 6 .m m D A T A A C O U I S I T I O NM A G A Z I N E S I B 33 1 0 01 2 5 ~ T T ~ ; ; ~ E NA G A Z I N ESHUTTER SPEED c - -/ELECTOR

\ F ?

S t B 3 3 1 0 0 0 1 0

Figure 52. - The 16-millimeter DACwith le ns and magazine attached,showing functional par ts.


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Requirements for high-resolutionphotography of proposed landing si te s we redefined ea rl y in the Apollo lunar-landingprogram. Thes e requirements wer e ful-filled for the fi rs t thr ee landing site s byphotography from the onboard 70-millimetercam era s ys te ms and the unmanned lunarprobes such as the Lunar Orbi ter. How-ever, mo re detailed photography was re-quired to evaluate the rougher si te sproposed for later lunar-landing missions;consequently, the lunar topographic ca m-er a (LTC) (fig. 26) was introduced on theApollo 13 missio n. The LTC is a 5-inch-format reoccurrence-type cam era with an18-inch-focal-length fixed-focus lens in-corporating image- motion compensationand capable of continuous overlapping s t r ipphotography. The ca me ra w a s designed fo rmounting in the command module hatch win-dow and operation within the command mod-igure 5 3 . - The 16-millimeter lunarsu rfa ce DAC sy st em consisting of ule environment. Th is design approachca mer a, 10-millimeter lens, cam- considerably simplified the spacecrafte r a handle, battery pack, and interface and crew operational requ ire-mounting bracket. ments, which wer e majo r fac tor s in pro-curing this ca mer a in the short timerequired and within the budgetary re st ri c-tions. Unfortunately, the LTC wa s not used for luna r photography on the Apollo 13 mis-sion, because the spacecraft did not atta in lunar orbi t. Reference 14 contains a detaileddescription of this equipment, and a photograph of th e LTC syst em and the commandmodule hatch mounting is shown in figure 27.

The sp otm ete r was upgraded by s emi -automating the exposure-value read-out andincorporating a photometer scal e. The cur-rent spotm eter configuration is shown infigure 54. This instrument is required forinterior crew station photography (possiblein the Apollo P ro gr am to a much greaterextent than previously because of thegr ea te r space). The crew activities in thezer o-g environment can therefore bestudied. Phot omete r readings of the eart hand moon contributed to the accuracy ofphotographic exposure valu es. A photom-e te r or photographic light meter can signif-icantly contribute to defining the lightingenvironmen ts encountered in orbit withnearby spacecraft and natural satellites,bec aus e the lighting conditions in space ar eve ry d iffe rent (because of the absence oflight diffusion and r efle ctio ns) fr om those

Figure 54. Spotmeter used in ApolloProgram showing battery removedfr om handle and neutral-density filt erused to extend the photometer scale.29


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on earth. Based on analysis of photographic results, predictions of photographic ex-posures f o r al l no rm al and predic table s ituations have been very good; however, thecrewman does need an aid to determine light levels during unplanned situations and dur-ing situations that come to his attention only. The Apollo automatic light mete r has a1" sensitive a r ea within a la rge r viewing field, has proved extremely easy to operate,and has yielded reliable data.

Grou nd -S u pport EquipmentAn important p ar t of any space-f light ope ration is the ground- support equipmentrequired to make the flight equipment flight ready. In this case, the term ground-support equipment may be somewhat misleading because, actually, a ground-supportfacility rather than only equipment is required. Flight-readiness preparation includesreceiving, inspection and acceptance testing, sto ring in bonded storage at a centralstorage a n d control point, data ana lys is testing, calibrating, applying decals , cleaning,and fina l packaging in a clean room. Equipment tes ting and checkout are accomplishedon semiautomated consoles for sy st em s with a la rg e amount of equipment to be proc-essed, such as the 16-millimeter and 70-millimeter camera systems, and on laboratory

setups when the test require ments a r e not as extensive. All tes ts and calibrations a r econducted in accordance with established and controlled procedures.Major tes ting and calibration of the 16-m ill imeter DAC are per for med on two s y s -tem test consoles (figs. 55 and 56). The sv st em test console (fig. 55) is used to verifythat a camera and magazine are performingaccording to specification requirements.The console is a self-contained unit thatneeds only a standa rd 115-V a c power input.The console measures al l parameters(shutter speeds, shutter j i t ter , fra me r ates,telemetry pulse outputs, cu rren ts, voltages,

run time, etc. ) and provides a visual dis-play to the opera tor. Thus, the console

Figure 55. - Data acquisition cam erasystem te st console.

IF . 8

--

I

7-

Figure 56. - Data acquisition cameracalibration console.30


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provides an insight into the camera for all functions except actual photography.Photographic quality is ver ifi ed by testing of the len s and complete photographicsystem, using standard resolution targets.The calibration console (fig. 56) is designed to provide extremely a ccu rat e dataabout the operation of the 16-millimeter camera. The data needed for lunar surfacephotographic correlation required accuracies 100 tim es be tter than that for which the

camera w a s designed. This calibration console prov ides this accu racy by spec ialmeasu ring and recording techniques, whereby the actual fr am e ra te s are measured onef ram e a t a t ime and the data a r e printed by a high-speed re co rd er . A series of data isreco rded before flight, and another se ri es is reco rded aft er flight. An extrapolation ofthe two sets of data yields the probable per form ance du ring flight to an accu racy of0.03 percent. Since the development of this console, other us e s have been applied, andthe calibration feature is now perfor med on all ca me ra s on a mission.All 70-millimeter still cameras are tested on a tes t console (fig. 57) before ac-ceptance by MSC. The test console cons ist s of a power supply, light source, oscillo-scope, amm et er , voltmeter, appropriate connecting cables, and switching circuitry .

After a mechanical tes t of the ca me rasystem, the camera is connected to theconsole for elect rical continuity tes ts,diode checks, and motor operating-currentmeasu remen ts. All shutter speeds aremea sur ed, using the light so ur ce and os-cilloscope. Resolution tes t photography atall aper tures is performed with each cam-era system during the last phase of ac-ceptance testing.Testing and checkout of the LTC a r e

performed, using the equipment and setupshown in figure 58. Such pa ra me te rs as theshutter speeds, f ra me spacing, forward-motion-compensation (FMC) ra te s, datarecording, and electronic-circ uit pulse sa r e checked to verify prope r operation andperf orman ce within the specification re -quirements. For example, the ca me ra testset, mounted i n the cen tr al par t of the con-sole (fig. 59), is used to monitor the op-erating cur ren ts and to provide e lectricaloutputs, such as the FMC-start signal,shu tte r-s tar t signal, film -advance signal,and pulse-code-modulation signal, whichcan be checked and monitored, using theoscilloscope and remaining test-cons oleequipment. The shutter-spee d and fr am e-spacing tests a r e performed, using unex-posed film and a light source-stroboscope for the shutter-speed tests.

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Resolution TestingThe ground-support equipment is intended pr ima ril y to check the mechanical andOptical pe rform -lect ronic per for mances of the photographic and r ela ted equipment.ance is verified on a tota l sy st em basi s by photographing U . s. National Bureau ofStandards high- and low-contrast resolution ch ar ts and analyzing the result ing film

image. All testing is done inaccordance with established sta ndar d practice. For the mo re c rit ica l photographicapplications, the te st s a r e suppleniented by exacting calibrat ions of distention , s pect ra lresponse, and whatever s pecial characteristics a re pertinent to the application. In theApollo Program, much of this work is done in coopera tion with U . S. Geological Surveyand the NASA Manned Spacecraf t Center Mapping Sciences Labora tory personnel. whohave estab lished photometri c and photograiiiiiietric calibrat ion faci liti es.

This test is pa rt of the predelive ry accep tance tes t.

OPERAT I O N S

Operations involving flight photographic equipment fall into two basic categori es:(1)preflight t esting of equipment and spacec raft int erface support and ( 2 ) inflight opera -tions. The preflight testing of equipment and spa cec raf t inte rface support is i n accord-ance with establi shed requirements.discussed previously. ) (Preflight or ground-support equipment has been

Integration of Mission Requirements and Equipment CapabilityPhotographic-requirement inputs ar e fir st as sembled in the mission requirementsdocument (MRD), usua lly in the for m of detailed te st object ives .objective (DTO) defines tes t conditions, succe ss cr it er ia , and the background and justi-

fica tion fo r each photographic requ irement. In par all el with the publication of the MRDis the publication of a miss ion equipment stowage li st containing the typ es and amountsof photographic equipment allocated . It then becomes the task of the assi gned photo-graphic engineer t o write the photographic and television procedu res document to det er-mine whether the equipment in the stowage lis t is sufficient to satisfy the requ ireme ntsin the MRD. An important fi rs t st ep is to deter min e the total amounts and types of filmneeded to sati sfy all the re qui rem ent s and then to verify that the quantity is compatiblewith the number of magazines on the stowage lis t. Thi s procedur e al so includes de-ter min ati on of the nec ess ary mission-peculiar equipment, such as fil ters, brackets.and inte rval omete rs. The photographic and television proc edur es document lis ts theobjectives, equipment allocations, fi lm allocation, and spa cec raf t stowage.f r o m the photographic and television procedures document fo r the Apollo 1 2 missiona re included in the appendix.

Each detailed test

Excerpts

Development of Photographic ProceduresTh e development of photographic pro cedure s begins with the definition of photo-Most of the ta sk s a re defined to s om e extent in a preliminaryThese tasks a re then reviewed and analyzed for any obvious in-graphic requirements .version of the MRD.compatib ility with the cu rr en t edition of the flight plan and with the crew and spa cec raf t

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capabilities. After the initial review, proc edu res a r e reviewed with those perso ns whoinitiated the photographic requir emen ts f or discus sio ns of any appar ent problems andcollection of any additional information requir ed to develop cr ew pr oced ure s o r integr a-tion of the task into the flight plan.When the photographic equipment, ca mer a setting. film usage, and spac ecr aft -attitude requirements are known. step-by-step crew procedure s a r e written for each

tas k. Pa st photographic and television procedur es documents descri bing the sam e o rsimilar tasks are used as guidel ines. By determining the number of fr ame s of eachfilm type required, a preliminary analysis of the film budget is made.personnel a re then consulted to determin e that adequate stowage i s available for thefilm magazines.ability of the selected film type and any spec ial film process ing r equ ired .a cre w briefing on al l photographic pro ced ures is held.ful in ref ining the var ious photographic pro cedur es . The photographic engineer is incontact with the crew and the flight planner to coordinate changes in photographic re-quirements and procedures.

The appropriatePhotographic laboratory personnel a r e consulted to confirm the avail-At this stageThe crew's comments are use-

The dura tion of the inflight ta sk , landmark tar gets , sun angles. spacecr aft atti-tudes, and effects on other cre w activities must be cons idered before photographic-proced ure integration into the flight plan. Lunar sur fac e photographic procedu res a reinserted into the lunar surface time line. A final ana lys is of lunar su rface photographictas ks follows numerous simulations of the lunar su rfa ce activiti es. Much of the photo-graphic procedural development is accomplished during these e xer ci ses when the photo-graphic e nginee rs and the crewmen have an opportunity to ob serv e the operation anddetermi ne the most efficient w ay of accomplishing the tas ks. Ca me ra settin gs and otherprocedu ral details must be complete by the ti me cr ew training pro gre sse s beyond thepreliminary or developmental stage to ensure adequate crew-training time in all detailsof th e photographic pr oce dure s and to ass ur e that al l proc edu res are updated in the on-board data for both training and flight.

Many of the cam era set tings ar e determined by the data u se r s and oth er personnelsupporting the photographic t asks. The require d camer a sett ings for the lunar su rfa ce.engineering, and Public Affairs Office photography a re determined jointly by the geolog-ical investigators and the photographic e nginee rs. Ca mer a set tin gs a re required earlyin the procedures-development cycle. necess itatin g an ear ly esta blishm ent of fi lm typeswith the photographic user and processing laboratories s o that. 3 months before flight,al l aspect s of the photographic operations ar e esta blishe d. At this time. a preliminaryphotographic and television proce dures document is published. The document catego-ri ze s the photographic tasks and li sts the crew procedu res requir ed to accomplish thetas ks. Diagram s outlining photographic acti vit ies on the lunar surf ace ar e included.Such diagrams m a y include a view of the L M ar ea . planned deployment locations forexperimental and operational equipment, and illust ration of the standard procedure fordocumentation of geological sa mp les.

Included in the appendix is an example of the res ul ts of the trade-offs made inobtaining the final photographic procedu res. showing the ni:Inner in which al l the dataa r e integrated into the operational docunicntat on. Came ra decals indicating surf ace-and orbital-photography camern settings an d the onboard cue card fo r lunar sur facetar get s of opportunity and other mi scella neous photography a r e als o presented.line summary of all photographic ta sks i s included.configuration code and designates the film magazine to be used fo r each task.A time-This sunimary states the camera

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The pre limi nary photographic and television pro cedu re document is published toaid in filial training preparation, to provide a partial input to the onboard data. and toallow for a final review before publication of the final photographic proc edur es. Thefina l copy of the photographic and televis ion proc edu res document is published 1 monthbefore flight and represents the photosrapliic tasks and procedures a s they a r e to beaccomplished on the mission.

Integration Into T i m e Line and Flight PlanThe succ essful accomplishment of the niission photographic objectives is depend-ent on the prop er integrat ion of the objectives and associated pr oce dur es into the flightplan. On ea rly Gemini and Apollo mis sio ns . the photography was mostly limited tooperational photography. On late r missi ons. the scientific objectives and associate dphotographic operations became more extensive.generally con sis ts of coverage of the nominal mission events. the major task of integra-tion into the flight plan is making the photographic p roc edu res compatible with the cre wprocedures and checklist for the particular mission phase. These events include ren-dezvous, docking, undocking. extr aveh icul ar activity . intravch icular activity, andtran sfer and reentry. Other events, such as lunar descent and ilscent. lunar suriaceactivity, and futu re- landing- sit e mapping. a re considered opera ioiia 1 pholography andare accomplished on every lunar mission. On Gemini miss ions , the photographic pro -cedu res wer e placed in a sect ion of the flight plan se pa ra te from the time-line sect ion.On Apollo missi ons, the procedu res a r e condensed into the caiiiera conliguration codeas defined in the photographic and television pro cedu res document and incorporateddirectly into the flight-plan time line. A photographic time-line summary is maintainedin the photographic and television proc edur es document f or the investiga tors prima rilyinte rest ed in photography; this document provides a ready refe renc e to al l the photo-graphic task s i f real-time reprograming should be required.

Because the operational photography

Contingency photography fo r a mission anomaly or a suspected anomaly is plannedin real time. A fair ly high priority is usually assigned to t h i s type of photography, andany of the onboard photographic equipment and fil m caii be made available fo r mi ssio n-evaluation photography. The photographic and television proced ures document is help-ful because i t is a ready reference for the selection of available film and equipment andal so con tain s previously defined photographic p roced ures codes to simplify updating i n -formation fo r the crew.Scientific photography is incorpor ated into the time line in much the sa me manner(Reference 14 contains a discuss ion on how the basi cs is the operatio nal photography.flight plan and trajecto ry are determined. ) When the traje ctory p arame ters and basicflight plan have been estab lished, the photographic integrat ion is refined to specify theexact tim e-l ine placement of the var iou s photographic ta sks . The appendix contains the

photographic ti me line and onboard data notations as incorpor ated into th e Apollo 12mission. Television procedure s and associated time lines are treated very s imilarly tothe photographic procedures and time lines, and a r e included in the photographic andtelevision pr oced ures document.

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Ope ra t i n a I C o n s d e r a t i n sMany operational considerations or constraints ar e of concern to the photographicengineer and the astronaut in obtaining space-f light photography. Th es e con str ain tsgeneral ly fa ll within the following cate gor ies .1 . Lighting2 . Time3 . Vantage point4 . Equipment

Thes e constrain ts will be discussed briefly.A review of spa ce photography (particu larly that taken inside the crew station,vehicle to vehicle, or on the lunar surfa ce) revea ls that, in many situations, the photo-grap hs we re taken into the sun (with a resulting flare) o r we re t aken with inadequate o r

excessive lighting. The photography als o revea ls har sh cont rast and sunglint situatio nsthat, although they are "dramatic" photography, do not nec ess ari ly yield maximumdata. With the absence of a light-diffusing atmos pher e, thes e adve rs e conditions mustbe over come . Photography taken ins ide the vehicle has areas of ove rex pos ure andunderexposure, with sun shafting causing bright illumination and underex posu re causingshadow areas. The crewman generally expos es the photographs at a n aver ag e settingthat usual ly does not yield good photography becaus e of the ex tr eme s in lighting and be-cause of the restr icted latitude of the film . Another lighting prob lem is encountered onthe lunar s urfa ce where the low sun angles re su lt in sunlight impinging on the lens fo rall photographs not taken in the quadrant fro m directly c ro ss sun to down sun. Theretroreflective properties also contribute to the general exposure proble ms for lunarphotography both on the sur face and in orbit.Time constraints are always pre sent in manned space-f light mis sion s and have adefinite effect on photography. The cre wma n, on many occasion s, does not have thetime to analyze the photographic situation and set hi s equipment accordingly . In an ef-fo rt to sav e time , photography is generally accomp lished with precomputed nominalexpo sure values. Although a light meter is available on each mission, its use is usu-ally reserv ed for off-nominal situations.The optimal vantage point i s perha ps one of the most cr it ic al consideratio ns.Much photography i s conipromised bec aus e the camera is not oriente d properly e itherin re lat ion to the photographic object o r in rela tion to the sun. Optimizing the vantagepoint generally requ ires the expenditure of sp ac ec ra ft prop ella nt, which is always a

sc ar ce coniniodity .Equipment co nstraints al so affect the photographic oper ations. The onboardequipment is limited in quantity and somewhat in flexibi lity. Onboard equipment isdictated by stowage volume and weight limitations. A gr ea te r vari ety of l ense s andfilm types could overcome som e of the lighting const rai nts a t the expe nse of greaterweight, volume. and crew time. A review of figires 6 to 1 7 and 28 to 50. showingGemini and Apollo photography, w i l l illus trat e som e of t hese points.

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Support of Photography From the Mission Control CenterSupport of photography f ro m the Mission Control Center (MCC) is a task s imilarto other con tro l-center functions. The MCC must, of course , have a clearly defined

bility for each specific mission must be integrated into these operations. The require-ments of this task must be identified, the required control-center facilities (such asconsole configuration and communications capabilities) must be provided, the appro-pr ia te proce dur es must be developed, and the personnel staffing the positions must beadequately trained. The personnel in the Staff Support Room who a r e direc tly concernedwith photographic operat ions support the Flight Activities Officer, who in tur n supportsthe Flight Director. Pri mari ly, this support involves photographic-procedures updates,raphy, and coordination and respo nse t o crew questions concerning photographic pro -cedures and equipment.

chain of command fo r all operations, and the appropriat e photographic support capa-

computation of s pacecraf t tra jec tory and atti tude data requ ired for conduct of photog-

The pre sen t capability of support operations to generat e the data required to pointa given spacecra ft line of sight a t a particular object at a particular time is highly de-veloped. With nominal traje ctory data, the photographic support personnel can providethe space craft roll, pitch, and y aw angles and mission time to point windows andbracket-mounted c ame ra s at various photographic targe ts. This information can betransmitted to the crew before the event. These angles and the related ground-elapsedtimes are calculated by the use of rea l-t ime compute r complex (RTCC) pro grams. Suchprograms were conceived and developed to fulfill photographic - s well asgeneral, the progra ms can point a fixed line of sight at any celes tia l o r ter rest ria l pointand compute the requ ired gimbal angles fo r the inerti al platform in the spacecraft.Other pro gra ms exist to compute the shaft and trunnion ang les of the navigational optic s;to calculate earth-moon-sun look angles; to provide star acquisition of s ignal and lossof signa l ti mes ; to provide closest-approach t im es of ground points; to supply such in-formation as north or south of track, distance off t rack , and elevation angle at time ofclose st approach; and to compute sunrise-sunset and moonrise-moonset time s for theprograms are simulated during the premission training to ensure that they a r e cor rec tand that the computers that a r e time s hared with other us er s will be available whenrequired.

operational - pacecraft-pointing requirements, such as navigational sightings. In

spacecraft, along with terminator rise and set time s. The procedures for the use of the

Crew Debrief ingAs a pa rt of every postmission crew debriefing, each crewman comments on theadequacy of photographic equipment, flight plan and checklist procedur es, and preflighttrain ing in photography and on the subject matter pr ese lec ted to be photographed. Each

crewman is al so ask ed to make suggestions for changes to improve the photographicplanning and to enhance the chances of obtaining bet ter photography on fu ture missions.At a fo rm al photographic debrief ing held approximately 10 days after recovery andattended by engineers and s cienti sts with a special interest in the mission photography,each crewman is able to correlate his visual observ ations with the photographs and toans wer questions fr om the photographic engineers.

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P r o b l e m DiscussionSome gen era l problems with the photographic syst ems we re encountered with cer -tain sealant compounds and lubricants and with extended shelf -life requirements anddefinitions. Ear ly in the Apollo Prog ram, considerable difficulty was encountered bymigration of sealant compounds used to prevent scr ew fas ten ers fr om working loose.The compound caused the shutter release mechanism of one cam era to fr eeze beforethe problem was detected. Ext rem e caution with the amount of this ma te ri al used andcareful application to ensure that the substance cannot work its way to delicate movingpar ts is necessary to prevent the migration.Another area of concern is the migration of silicon base lubr icant s. Lubricantmigrating from a motor gear box to the motor brushes caused a high resistance path.Also, when this lubricant migrated from its desired area, the area was left with insuffi-cient lubrication. The lubri cant migration was aggravated when the equipment remai nedon the shelf for long per iod s of time. The us e of d ry film lubrication re sol ved the prob-lem. Dry film lubricant should be considered for future program applications wherelong duration and vacuum operation may be a requirement. However, care ful analys is

is requi red to ensu re that the lubrication proce ss i s compatible with othe r mat eri alsused in the mechanism. In short, the requirement for a careful materia ls compatibil-ity analys is in the operational environment cannot be overemphasized.Testing requi rement s in support of space pro gra ms al so have contributed to so meof the problems encountered. Attention must be given to the number of equipment te sthours to ensure that the limit life of a mechanism is not approached. Although th ispoint may appear to be obvious and not worthy of mention, when all the various testingrequi rement s ar e totaled, it i s quite likely that the equipment can be subjected to anexcessive number of hours unless one is continually aware of the potential problem andmake s every attempt to limit testing to minimum requi rement s.compounded fur ther by the requi rement that photographic equipment be compatible witha vacuum and an oxygen atmosphere, a requi rement which resul ted in the us e of speci allubricants and motor brushes that are not necessarily compatible with extended ambientatmosp here operations.le ms of exceeding equipment shelf life; in situ ations like thi s, a procedure fo r periodicopera tion of the equipment should be considered.

This situation is

The slowdown in the Apollo P ro gr am a lso res ult ed in prob-

In photographic operations, the late definition of photographic requir emen ts ha sbeen a problem throughout the space-flight pr og ra ms because of the insufficient time todevelop the required equipment. (Compromise equipment did not always accomplish theobjective. ) Early definition is not always possible because often the results of one pho-tographic mission determine the requireme nts for the next. Also, because of othercommitments, some of the photographic in ves tig ato rs a r e not available for ear ly defini-tion on a total program basis.additions of it ems like l enses and film type can be r eadily accommodated in a basicphotographic system.

The solution is to ret ai n flexibility of equipment so thatThis design approach is strongly recommended.

During flight opera tions , difficulties were encountered with rapid and accura teselection of film magazines containing s el ec t film for speci fic opera tions and with se-lection of proper exposure par amet ers .the maximum exten t possible the number of different fil ms req ui red, by color codingmagazines f o r film type and application, and b y incorporating exposure information oneach film pack.

These problems were solved by limiting to

The resul t of this labeling is shown in fi gu re s A-7 to A-12.3 8


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One last problem encountered throughout the spa ce -flight photography pro gra mand not yet totally solved is that of recording identifying information on the film. Toachieve the most effective retrieval of data from the photography, cer tain bas ic data-such as time of exposure, aperture stop, and shutter speed- ust be available witheach photograph. Cur ren tly , only the LTC (fig. 26) has ti me recordi ng on film avai l-able.corporation of t his capability in all future photographic systems is highly recommended.Followon syst ems with onfilm data recording capability a r e proposed, and in-C O N C L U D I N G R E M A R K S A N D R E C O M M EN D A TI O NS

Photographic equipment and support have been important pa rt s of the mannedspace-flight pro gra ms from the first Mercury orbital flight to the pres ent time. Photo-graphic requirements have steadily increased as space-flight programs progressed,and the quality and quantity of photographic equipment and assoc iated cre w proced ureshave inc rea sed correspondingly. Methods have been established for translat ing missionobjectives into specific hardware requirements and flight procedures. These methodsappear adequate for pr esen t pro grams but need to be reviewed for future progr ams.A mor e advanced photographic system for future progra ms should incorporatecertain features that could not be incorporated to date pri mar ily because of the tightschedule of the manned space-flight program. Futu re pro gra ms should cons ider pho-tography as a major sys tem from the outset. Provisions for photography such as photo-graphic stat ions with optical ports and all required power and vacuum facilities can,therefore, be incorporated into the init ial design of the vehicles . Also, because pho-tography supports many different data disciplines , it is not always possible to predictall photographic requ irements; consequently, the photographic syst ems must rem ainflexible without, however, compromising photographic quality. Certa in bas ic capabili-ti es should be designed into future photographic syst ems , The bas ic capabilitie s could

include mission time rec ording on film, automatic recording of a pertu re and shut terspeed, and a tie-in with the vehicle navigational system so that vehicle attitude can bereadily retrieved ,tion and make the data usable for a la rg er number of investigator s.These basic features will grossly simplify photographic data reduc -

With the incr ease d emphasis on Earth Resources support by space-flight photog-raphy, the futu re need exist s for high resolution and photogrammetric cam era sys temswith large film formats. Also, from an economic consideration, these syst ems mustbe designed with inherent flexibility of lens types and film types and mus t be designedto ope ra te within the environmentally controlled cabin ar ea to allow for inflight mainte -nance a nd to avoid design and fabrication complications caused by t her mal and vacuumconsiderations.

Manned Spacecraft CenterNational Aeronautic s and Space AdministrationHouston, Texas, June 6 , 1972924 -23 26-00-72

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REFERENCES1. Anon. : Mercury P ro je ct Summary, Including Result s of the Fourth MannedOrbi ta l Flight, May 15 and 16, 1963. NASA SP-45, 1963.2. Anon. : Result s of the First U . S. Manned Orbital Space Flight, Feb. 20,1962.

Manned Spacecra ft Center , Houston, Texas, 1962.3. Anon. : Result s of the Second United St ates Manned Orbital Space Fligh t, May 24,1962. NASA SP-6, 1962.4. Anon. : Result s of the Thi rd United S tat es Manned Orb ita l Space Fligh t,Oct. 3, 1962. NASA SP-12, 1962.5. Anon: Gemini Summary Conference. NASA SP-138, 1967.6. Anon. : Gemini Midprogram Conference, Including Experiment Resu lts.NASA SP-121, 1966.7. Anon. : Earth Photographs from Gemini Ill, IV, and V . NASA SP-129, 1967.8. Anon. : Ea rth Photographs from Gemini VI through XI. NASA SP-171, 1968.9. Lowman, Pau l D. , J r . : The Eart h Fr om Orbit. National Geographic, vol. 130,no. 5, Nov. 1966, pp. 644-671.

10. Lowman, Pa ul D. , J r . : Photography fr om Space- eological Application.Annals of New Y o r k Academy of Science, vol. 140, ar tic le 1, Dec. 1966,pp. 99-106.11. Lowman, Pa ul D. , J r . ; McDivitt, Ja me s A. ; and White, Edward H . , 11: TerrainPhotography on the Gemini IV Mission: Prelimi nary Report.NASA TN D-3982, 1967.12. Lowman, Paul D . , J r . : Geologic Orbi tal Photography: Experi ence fr om theGemini Pro gram . NASA TM X-63244, 1968.13. Lowman, Pa ul D. , J r . : Geologic Applications of Or bi ta l Photography .NASA TM X-55724, 1967.

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APPEND I XAPOLLO 12 P HO TO G RA PH I C A N D T E L E V I S I O N

PROCEDURES DOCUMENT EXCERPTSP H O T O G R A P H I C T A S K C O D I N G M ET H OD U S ED F OR Q U I C KINTERPRETATION AND INS TRU CT ION TO THE CREW

The equipment to be used for each photographic tas k w i l l be denoted in the follow-

Film typeColor exterio r, SO-368High-speed color exterior, SO- 168 (ASA 160)Color inter ior, SO-168 ASA 1000)Black and white, 3400Black and white (DAC film), SO-164High-speed black and white, SO-267

ing coded form:

1

AAA/BBB/CCC/DDD - XXX, XXXX (M, , 0)The notations

apollo experience report photographic equipment and operations during manned space-flight programs

Documents