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f

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

NhOI

APOLLO EXPERIENCE REPORTPHOTOG RAPHIC 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 IC S A N D S PA C E 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 AND OPERATIONSDURING MANNED SPACE-FLIGHT PROGRAMS7. Au tho rb )Helmut A. Kuehnel, MSC9. Performing Organization Name and AddressHouston, Texas 77058Manned Spacecraft Ce nter

12. Sponso ring Agency Name and Address

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

MSC -30910. Work Unit No.

924-23-26-00-7211. Contract or Grant No.

13. Type of Report and Period CoveredTechnic al Note

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

National Aeronautics and Space Administrat ionWashington, D . C. 20546

21. No. of Pages 22. Price66 3.00

14. Sponsoring Agency CodeI

15. Supplementary NotesThe MSC Di rec tor wa ived the use of the Inter national Sys tem of Units (SI) for th is ApolloExper ience Report , becaus e, in his judgment, the use of SI Units would impa ir the usefu lnessof the report or resu l t in excessive cost .The evolution of crew-o perate d photographic equipment and the proced ures for manned space-fl ightphotographic opera t ions are reviewed. The establishment of prog ram requ i remen t s is described .Photographic opera t ions are discus sed, including prefl ight test ing and infl ight operatio ns.

16. Abstract

* Photography in SpaceO pera ti ona l Proce du res.Photography ApplicationsPhotographic Equipment

~~18. Distribution Statement

* For s a l e by the f ta t iona l Tech n ica l In formatLon Serv ice , Spr lngf le ld , V i rg in la 22151

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CONTENTS

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1NTRODUCTION1STABLISHMENT OF PROGRAM REQUIREMENTS . . . . . . . . . . . . . . .1hotographic Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . .3

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

Photographic- Equipment Requ irements . . . . . . . . . . . . . . . . . . . .

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

Integra tion of Mission Req uirements 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 came ra (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 inspection . . . . . . . . . . . . . .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 target 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 Program

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 deposits . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1717 Synoptic-terrain and synoptic-weather photography

(a) First view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(b) Second view . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(c) Thi rd view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 171818Spotmeter used in the Gemini Pro gra m, with exte rna l exposurescale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8 18

19 Hasselblad 70-millimeter electric-drive ca me ra with80-millimeter lens . . . . . . . . . . . . . . . . . . . . . . . . . . 19190

2 1Reseau plate on 70-millimeter data camera . . . . . . . . . . . . . .Hasselblad 70-millimeter electr ic data cam era with 60-millimeterlens mounted to cam era , 80-millimeter lens at left, and100-millimeter lens at right . . . . . . . . . . . . . . . . . . . . . 20The 500-millimeter lens used with the 70-millimeter elec tri cHasselblad . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .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 ele ctr ic Hasselblad to obtainaccurat ely timed s ter eost rip photography fro m lunar orbit

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 me ra , contr ol box, and

21

2 1

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

22ervice module damage on the Apollo 13 mission . . . . . . . . . . . .

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 fr om 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 orbi tal 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 insid e the command module and gen era l views ofcrewman inside lunar module

(a) First view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .b) Second view . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(c) Third view . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 0 Egress of commander fr om LM . . . . . . . . . . . . . . . . . . . . .4 1 Egress of LM pilot from LM . . . . . . . . . . . . . . . . . . . . . . .42 Astronaut sett ing up solar-wind exp erime nt. Photograph shows effect

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

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 special-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 par ts . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28The 16-m illimeter lunar su rfa ce DAC system consisting of c ame ra,10-mi llime ter lens, cam era handle, battery pack, and mountingbracket . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29Spotmeter used in Apollo Pro gr am showing battery remove d fr omhandle and neutral-density filter used to extend the photometerscale . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

3030

Data acquisition cam era system te st console . . . . . . . . . . . . . .Data acquisition camera calibration console . . . . . . . . . . . . . .The 70-millimeter ca me ra tes t console, showing cam era 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 me ra is 32. . . . . . . . . . . . . . . . . . . . . . .3232

Test set used to me asu re functional pa ram et ers of LTC . . . . . . . .Spotmeter ground-support and calibration equipment setup . . . . . .Fr on t s ide of command module pilot ( C M P ) and lunar module pilot 46

46(LMP) cue car d . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Back sid e of CMP and LMP cue car d . . . . . . . . . . . . . . . . . .47ront side of LMP cue car d . . . . . . . . . . . . . . . . . . . . . . .47ame ra sett ings 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 lma) Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 8b) Film . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

Electric 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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APOL LO EXPERIENCE REPORTP H O T O G R A P H I C E Q U I P M E N T A N D O P E R A T I O N SD U R I N G M A N N E D S P A C E -F L IG H T P R O G R A M S

B y H e l m u t A . K u e h n e lM a n n e d S p ac ec r af t C e n t e r

S U M M A R Y

Photographic equipment has been carr ie d on board manned spacecra ft fr om thefi rs t orbital flight to the pre sen t time. The photographic requ irem 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 source 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.

ESTA BL ISHMENT OF PROGRAM REQU IREMENTSP h o t o g r a p h i Requ i em e nt s

Fr om the t ime of the first manned orbital flight in Pro ject Mercury to the present,space-flight photographic equipment and photographic operations have greatly matu red.The photographic equipment, the photographic procedures, and the accompanying opera -tions have developed in keeping with the requirement s of the var iou s space-flight pro-gr am s. During Pro jec t Mercury, 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 orbit al mission, a hand-held camera was carried, and interesting documentaryand scientific photography was obtained. During Pro jec t Mercury, no for mal proce -dur es existed for the acceptance, evaluation, a nd incorporation of photographic

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requirement s. 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 experim entswe re somewhat mor e formaliz ed; 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 spa ce and the c an accomplish at least som e photography fr om his crowded spacecr aft with all thexisting restr ictio ns, the number of photographic requirem ents w a s increased, andconsiderat ion was given to expanding the photographic capability. On the Mercury 7and 9 miss ions , 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 examples of organized scientificaoriented photography in the manned space-flight p rogra m. 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 Pro gra m. The results of these experiments arsummarized in refe rences 1 to 4.Throughout the Gemini Prog ram , photographic req uir eme nts of two types we reestablished: (1) the operational and documented photography and (2 ) scientific photography. The evolution of expe riment-r equi remen ts organizations is summarized inreference 5.Fr om the beginning of the Gemini Prog 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 mis sion and to specify th e photographic equipmto be used. The photographic plan se rved as the for mal documentation for missionphotography.A significant incr eas e in the photographic-equipment capability was r equir ed inthe Gemini Progr am to make permanent rec ord s 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 mi ssion re-quirements and objectives, as stated in refe rence s 5 and 6. Photographic requiremein support of mission req uir eme nts will be discussed later in mor e detail, along wit

photographic equipment.The Apollo Pro gra m incr eased the demand for broader photographic requiremPhotographic requ irem ents becam e mo re fo rma l, 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-ment s were dictated by the missio n requi remen ts. However, an entirely new scie nc(lunar mapping fro m orbit and lu nar s ur fa ce geology) became a part of the photograp

2

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requirements in the Apollo Program. The photographic req uir ement s are usuallyrouted through the mission req uir ement s 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 oth er engineering- andscience-related photographic documentation tasks. De ta 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 proceduresdocument 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 successful 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.P h o t o g r a p h i c - E q u i p m e n t R e q u i r e m e n t s

Photographic equipment has evolved during the manned space-f light pro gra m inaccordance with the photographic requiremen ts or objectives. The major photographicequipment used on each manned s pace 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 irements were conservative. On the first two Mercuryorb ita l flights, 35-millimeter ca me ra s modified by NASA to be crew compatible wer euse d fo r mis sion 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 irem ents w ere 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 came ra w a s chosen as the basic camera.Modifications by NASA included removing the reflex viewing system and dechroming thecomm erci al unit. Synoptic -ter rain , synopt ic-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 resul ts is contained in references 1 o 4.

3

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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION~~

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

Ansco Autoset Eastman color negative, Terr ain , weather, sunsetI stock number 5250 I phenomenaMercurv 7Robot Recorder 35 55 Eastm an color negative, Terr ain , weather, horizon def-inition, sunset phenomenatock number 5250

Mercury 8Hasselblad 70 80 Super Anscochr ome D-200 Terr ain , weather, suns etphenomena

Mercury 9Hasselblad 70 80 Ultraspeed Anscochrome, Ter rain , weather, horizonFDC 289, D-200 definiti 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 order (SO-2 17)SO-217 Crew activity (for evaluation)

Terrain, weather

n i O-217V arth st r ip

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

SO-217

Gemini V80 SO-217

Ansco color rev ers al (D-50)

5, 18, 75, and 25

N A NAIGemini VI1

80

Terrain, weather, stereo-scopi c cover age, EVA (fordocumentation and analy-sis), earth-limb definitionEVA and maneuvering unit

(for evaluation)

Terrai n, 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 (ult ravi olet (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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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - Continued

Equipment Film size, mm Lens size. mm Film Tasktarget

~

l a u r e r

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

80

SO-368

SO-368Ektachrome 103DI 50 I

~~

Terra in. weather, AgeM SPSthru ste r plumes. Agenaprimary propulsion sy stem(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 from high altitude,Agena operationsTerrain. weather5-13 (uv astronom icalphotography)S 11 (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 (terrain). S-6 (weather).Agena operations

S-5 (terrai n), S-6 (weather)S- 11 (horizon airgl ow)S-29 (libration regions), S - 5 1(sodium cloud) - no datareturn

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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - ContinuedEquipment Film size, mm Lens size, mm Film Taskha rget1

Gemini XII - Concludedvlaurervlaurer sequencecamera

iasselblad

klaurer sequencecamera

relevision

3asselblad electric(EL)

1673 uv75

18

5

Spectroscopic 1-0SO-368

SO-368

SO-368Apollo 7

70

80

18 and 75

SO-121 ( 6 magazines)

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

Kodak E F (7 magazines)I I NAApollo 8

80

250 (mediumtelephoto)

50-368 2 magazines)

SO- 2 1 ( 1 magazine)

Kodak 3400 (3 magazines)

Kodak 2 4 8 5 ( 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 (camera mounted outside)

Simulated docking. space craf t-LM adapter (SLA), windowcoating, terrain, weatherS-5 (terrain), S-6 weather)Simulated 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 stripEarth (long distance), moon(long distance). lunarsurfaceLunar stereoscopic strip,lunar landmarks. earth(long distance), moon(long distance), solarcorona, lunar surface tar-gets, lunar surfac e (red-blursurface study)Spacecraft exterior atmos-phere, lunar surface inearthshine, t ransi ent lumi-nescent phenomena, gegen-schein, zodiacal lightLunar surface target s. moon(long d istance)Moon (long distance)Lunar terminator. image-motion-compensation ( I MC)training, moon (long dis-tance), lunar surface target:zero phase angle

aNot applicable.

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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - Continued

Equipment Film size. nini Lens size. nin i Film Task/target

Data-acquisitioncame ra (DAC)

Television

Hasselblad

Hasselblad SWA

DAC

Multispec tracamera (fourganged ELHasselblads)Television

16

N A ~

70

70

16

70

NA

200

7 5

18

_ _Apollo 9

8 0

38

75

18

8 0

- -

SO-368 (9 magazines)

SO-368

S O - 3 6 8

S O - 3 6 8

S O - 1 6 8 ( 2 magazines)NA

S O - 3 6 8

SO-368

SO- 168SO-368

S O - 3 6 8

S O - 3 6 8

SO- 168SO- 368. SO- 24 6 ( blac k-and-white IR). SO- 180 (colorIn). Ektachrome 3 4 0 0

NA

IMC training. eart h and moon(long distance)

Earth and iiioon (long distance).lunar surfac eSeparation and Saturn IVB(S- NB) inspection. lunarsurface. earth and moon( l o n g distance)Exhaust effects on commandmodule (CM) windowsCrew activitiesCrew 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 and C Mfrom LM during docking.terrainDrohue-impact damage. EVAfrom 1.M porch. docking.weatherInterior crew activitiesAscent propulsion systemburn to depletionS- N~/ SL A/L M inspection) .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 terra npllotugrallhy

~nte l ' l~ l rf CM and LM. EVAaNot applicable

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

Apollo 10Hasselblad EL

Hasselblad EL

DAC

Television

Hasselblad EL

DAC

aNot applicable.

70

70

16

N A ~

70

16

80

250

7518

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/S L A / L M (inspection); lunarsurface targets; undocking;LM (inspection); rendezvousEart h (long distance), lunartargets of opportunity, moon(long distance)RendezvousTD&E, S-IVB/SLA/LM (in spe c-tion), undocking, LM (ins pec-tion), rendezvous, lunarsurfaceIntravehicular transfer(commander), crew activ-ities in spacecraftTransposition and docking,spacecraft interior, undock-ing, lunar targets

Eart h from high altitude afte rtranslunar injection, trans-position and docking, earthand moon, undocking, LM(inspection), lunar targetsLunar surface through LM

windowEart h and moon (long distance),lunar targetsMoon (long distance), luna rtargets. landed-LM locationLunar mapping (strip. CM).lunar surface through LMwindowRendezvous. lunar targetsTD&E. undocking. LM (in spe ction). rendezvous. dockingCrew. spacecraft interior.entryDescent a s seen through LMwindow (60 00 feet to touch-down). EVA. ascent. CM atrendezvous

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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - Continued

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

~~

Zloseup ster eo-

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

250

5

18

51060

- _

- -

S O - 3 6 8

NA

NA

SO- 168

SO-368

3 4 0 0

S O - 3 6 8

3400

S O - 3 6 8

SO- 168SO- 168SO-368SO- 168

S O - 2 6 7

5 0 - 3 6 8

N A

Lunar surface details

Earth. moon, Spacecraftinterior, crewEVA, lunar surface. LM onsurfaceLunar sur face, LM. crewmenduring EVA, deployedexoeriments

TD&E. earth, moon, undock-ing. lunar targets. FraMauro, rendezvous anddockingVertical stereoscopic strip,moon (long distance). lunartargetsEarth and moon (long distance).lunar targ etsHigh-resolution oblique photog-raphy of Lalande, Descartes,and Fra MauroTD&E. undocking. rendezvousand docking. LM jettison,high-resolution obliquephotography (concurrentwith Hasselblad EL with5 0 0 - m m lens)EntryInterior crew activitiesL M descent. EVALunar su rfac e during EVA,Apollo lunar surf ace experi-ment s package. LM.crewmenLunar geological targets. sam -ple documentation.Surveyor IIILunar surface details

Transposition and docking.intravehicular transfer,spacecraft interior.lunar s urf ace . undocking.formation flying. docking.earth

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TABLE I. - PHOTOGRAPHIC EQUIPMENT AND APPLICATION - Concluded

--

~~

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

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

Multispectral cam-era (four gangedHasselblads)--

Hasselblad EL

Hasselblad DC

DACBattery -operatedDAC

Television

Lunar topographiccamera

7 0

70

1 616

NA

b5

-- Cre wmen during EVA, LM,lunar surface (Camerafailed during fi rs t EVA. )

Apollo 1380

2506 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 distanc e),servi ce module, spacecraftinteriorWeather, servi ce moduleLunar surface during flyby,servi ce moduleService moduleTransposition and dockingCrew and spacecraft interio r

Service module afte rseparationSpacecraft interior and intra-

Not use d because of earlymission termination

vehicular transfer

aNot applicable.bInches.

In the Gemini Pro gra m, equipment was requ ired 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 rep laced by a sequence came ra, 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 fo r close- range wide-angle photog-raphy req uir ed for EVA and crew station operations, an 1 8-millim eter lens requi red 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 experime nts begun in Project Mercury; however, there was also

ground strips) .

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The first motion picture ca me ra used in the Gemini Pro gr am (fig. 1)had a single-f r a me rate of 6 fr am es per second and a fixed shutt er speed 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 Pro gr am , procu reme nt of a mo re flexible and ac-cur ate sequence cam era was initiated. The sequence cam era incorporating fr am 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) wa s 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 cameraused 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 for space-flight us e (fig. 3), wasthe pri ma ry ca me ra used fo r the synoptic-weather and synopti c-terrain photographyin the Gemini Prog ra m. Photography obtained with this ca me ra contributed significantlto the program, as reported in reference s 7 o 13. A magazine for the 70-millimetercamera is shown in fi gur e 4. On the Gemini M o XI1 missions, a 70-millimeterscientific camera and a low-light, ultraviolet lens to meet specific experiment require -ment s wer e introduced. Valuable photographic re su lt s we re obtained (ref. 5); however,the camera did not provide the required reliability and was later abandoned. A thi rdstill came ra, the 70-millimeter Hasselblad super-wide-angle c am er a with 38- millimetelens (fig. 5), w as introduced fo r the Gemini M mission to fulf ill the wide-angle photo-graphic re quir emen ts of EVA and al so to provide wid er angle ground-covera ge 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 Pr og ra m wa s obtained with th is

.

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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 summar y of later Gemini photography.ground-support equipment is discussed later. Representative still photographs takenduring the Gemini miss ion s in support of the photographic requir ements for engineeringdocumentation, experi ments, and vehicle inspection a r e shown in figures 6 to 1 7 .

The required.

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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.

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Figure 12. - Gemini IX crew station,showing Astronaut Thomas P.Stafford in the left-seat positionand the 16-millimeter camer amounted in the window.

(a) Fi rs t view.

-7

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

ing the Gemini Prog ram .

Figure 13.- Gemini IX target dockingadapter.

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Figure 15. - Vehicle inspection during Gemini EVA.

T

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

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

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L - 4

(b) Second view

.

Figure 17 . - Concluded.

A spotmeter (fig. 18) was fir st in-troduced to the manned space-flight inven-tory on the Gemini V mission for thepurpos e of me asurin g light values in sit ua-tions in which light prediction was difficult,fo r example, inside the spa cec raf t and onareas of specific interest on a target vehi-cle. One example of the usefulness of thespotmeter was on the Gemini IXmissiondur ing 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 expo sur e 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 Prog ram , with externalexposure scale.and expansion of photographic equipment us ed for the Gemini Prog ram .Pr og ra m requir ed photographic equipment of sufficient quality to upgrade the availab llunar maps and to map ar e a s of the moon as an aid in landing-site selection.

The ApolloAlso,

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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 we re requ iredf or lunar geology. Continuous photography of the lunar module (LM) descent and as centwas re qui red to aid in LM landing-site location analy sis. Vehicle-inspection photog-raphy was requi red during the LM engineering m issio ns to determ ine that all vehiclessuffe red no damag e during separat ion, docking, or rendezvous and that the landing gearon the LM deployed properly.To meet the requi remen ts 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 cam er a wereintroduced; and various lense s wer e added (table I). Also, a change was made to themodified Hasselblad elect ric (EL) ca me ra (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 t o the cam era manufacturer which resulted inincre ased product control and quality. Camer a subcontr actors wer e also brought intodir ect involvement and handpicked the optics and assem bled specia l shu tte rs for theNASA cameras. A specia l version of the Hasselblad 500 EL cam era 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 grammetr ic 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 sur -fa ce geo logical and e ngineering photography, (2) an 80-millimeter lens for orbital

fFigure 2 0 . - Reseau plate on70-millimeter data camera.

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

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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 environment. 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-millim eter 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-millimeter lens mounted to cam -er a, 80-millimeter lens at left, and100-millimeter lens at right.

Figure 2 3 . - The 250-millimeter lensuse d 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 mresulted in the 16-millimeter data acquisi-tion ca me ra (DAC). The sequence modeswere changed to 1, 6, and 12 fra mes per sec-ond, and a 24-frame-per-second cinematicmode was added. Shutter speeds wer echanged 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-millimet er 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,mult ispec tral photography.

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

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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 .comm and module, showing condition fr om the lunar module. Note theof L M th ru ste rs and skin.

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Figure 3 5 . - Lunar module, showingsunglint fr om sur fac es, whichcomplicates space photography.

Figure 3 7 . - Use of photographicequipment during E V Aoperations.

24

Figure 36. - Handrail evaluation duringorbital E V A .

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

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(a) First view. (b) Second view

c ) Third view.Figure 39. - Interior crew station plioto-gra phs , showing handling and docu-Inen a ion of equip ii ii inside t li ecoiiiniaiid iiiodule and gener al viewsof crewiiiaii iiiside lunar iiiodule.

Figure 40. - Egress of conixiianderfroin L M .

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Figure 4 1 . - Egress of LM pilotfr om LM.

Figure 4 3 . - Lunar module footpad.

Figure 4 2 . - Astronaut sett ing u p solar-wind expe rime nt. 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).

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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 proved to be a substant ia1 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 accomplis h. The Apollo 16- mill imct cr cam 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 AN G L E MIRRORS E B 3 3 1 0 0 0 5 11 8 - m m - L f N SS f 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 lS l T lO N C O N l R O LSEB 1 3 1 0 0 0 3 1 M A G A ZI N E SF8 3 3 1 0 0 1 2 5 S E B 331 1

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 N TA 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 p art s.

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Requirements for high-resolutionphotography of proposed landing sit es weredefined ea rl y in the Apollo lunar-landingprogram. Thes e requirements wer e ful-filled for the f ir st t hre e landing sit es 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 sitesproposed for later lunar-landing missions;consequently, the lunar topographic cam -er a (LTC) (fig. 26) was introduced on theApollo 13 mis sio 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 st r ipphotography. The ca me ra w a s designed formounting 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 me ra , 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 cam era in the short timerequired and within the budgetary restric-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 detailed

description of this equipment, and a photograph of the LTC sy st em and the commandmodule hatch mounting is shown in figure 27.The sp otme ter was upgraded by sem i-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 Pr og ra m 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 omet er 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 lightingenvironm ents encountered in orbit withnearby spacecraft and natural satellites,because the lighting conditions in space areve ry d iffe rent (b ecause 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 predictab le situations 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 me te r has a1 sensitive ar 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 operat ion is the ground- support equipment

required 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 sto rage at a centralstorage a n d cont rol point, data ana lys is test ing, calibrating, applying decal s, cleaning,and fina l packaging in a clean room. Equipment test ing 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 cam era sy ste ms, and on laboratorysetups when the te st requir ement s ar e not as extensive. All tes ts and calibrations a r econducted in accordance with established and controlled procedures.

Major test ing and calibration of the 16-mi llim eter DAC are per for med on two s y s -tem test consoles (figs. 55 and 56). The svst 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 standard 115-V a c power input.The console measur es all para met ers(shutter speeds, shutter jitter , fra me rat es,telemetry pulse outputs, currents, voltages,run time, etc. ) and provides a visual dis-play to the opera tor. Thus, the console

Figure 55. - Data acquisition camerasystem te st console.

IF 8

--

I

7-

Fig ure 56. - Data acquisition ca mer acalibration console.

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provides an insight into the camera for all functions except actual photography.Photographic quality is veri fied by testing of the lens and complete photographicsystem, using standard resolution targets.The calibration console (fig. 56) is designed to provide extremely ac cur ate dataabout the operation of the 16-millimete r camera. The data needed for lunar surf acephotographic correl ation required accur acies 100 tim es bet ter than that for which the

camera w a s designed. This calibration console provides this accuracy by specialmeasuring and recording techniques, whereby the actual fr am e ra te s are meas ured onef r ame a t a tim e 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 s er ie s is reco rded af ter flight. An extrapolation ofthe two sets of data yields the probable performa nce during flight to an accu racy of0.03 percent. Since the development of this console, othe r u se 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 test console (fig. 57) before acceptance by MSC. The test console consi st s of a power supply, light source, oscillo-scope, ammeter, voltmeter, appropriate connecting cables, and switching circuitry.

After a mechanical tes t of the cam er asystem, the camera is connected to theconsole for electrical continuity tests,diode checks, and motor operating-currentmeas urem ents. All shutter speeds aremeas ured, using the light sour ce and os-cilloscope. Resolution tes t photography atall aper tu res 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 parameters as theshutter speeds, f ra me spacing, forward-motion-compensation (FMC) ra te s, datarecording, and electronic-circuit pulsesa r e checked to verify prope r operation andperformance within the specification re-quirements. For example, the ca me ra testset, mounted i n the central part of the con-sole (fig. 59), is used to monitor the op-erating cu rre nts and to provide ele ctricaloutputs, 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-consoleequipment. The shutter- speed and fr am e-spacing tests a r e performed, using unex-posed film and a light so urc estroboscope for the shutter-speed test s.

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Figure 58. - Ground-support and cali-bration equipment for the LTC.Camera is shown on the test stand.

The spotmete r checkout and calibr a-tion facility is shown in figure 60.facility is used primaril y for the calibra-tion of the flight automatic s pot met er, butcan be used to calibr ate and check out anytype of photometric device. Calibration ofall flight automatic spotmeters must beaccomplished every 6 months and is per-form ed on the flight-assigned spot mete r.By comparison of a light source of knownillumination with the spotmeter reading,an accu rate calibration can be accom-plished. This calibration is the onlymethod of ensuring t h a t the spotmeterreading is accu rate. The flight automaticspotmeter is calibrated to an accura cy ofone-fifth of an f-stop.calibration, a prescribed voltage is placedon the standard lamp. and the cur ren t ismonitored to e nsure that the lamp is draw-ing the pres crib ed curre nt. The diffusinggla ss i s then placed a distance corresp ond-ing to the de sired foot- lambert readingfro m the standard lamp, and readings a r erecorded.

This

To perform the

: ii

Figure 59. - Test set used to measurefunctional pa ra me te rs of LTC.

--*- '

LI I

1 .

Figure ti@. - Spotlnctc>rp-ound-supportand calibration equipment setup.32

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Resolution TestingThe ground-support equipment is intended pr ima ril y to check the mechanical andOptical per form -lect ronic per for man ces 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 more cri tic al photographicapplications, the tes ts a r e suppleniented by exacting calibration s of distention, spe ctr alresponse, and whatever s pecial characteristics are pertinent to the application. In theApollo Program, much of this work is done in cooperation with U . S. Geological Surveyand the NASA Manned Spacecraf t Center Mapping Sciences Labora tory personnel. whohave es tabl ished photomet ric and photograiiiiiietric calib ration 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 establish ed requirements.discussed previously. ) (Preflight or ground-support equipment has been

Integration of Mission Requirements and Equipment CapabilityPhotographic-requirement inputs ar e firs t assembled in the mission requirementsdocument (MRD), usua lly in the for m of de tailed test objectives.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 lis t containing the types and amountsof photographic equipment allocated . It then becomes the tas k of the as signed 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 req uire ment sin the MRD. An important fi rs t step 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 for the Apollo 1 2 missionare 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 so me extent in a preliminaryThese task s a re then reviewed and analyzed for any obvious in-graphic requireme nts.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 requ ire ments for dis cuss ions of any apparent 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 me ra setting. film usage, and spac ecr aft -attitude requirem ents are known. step-by-step crew procedur es a r e written for each

tas k. Pa st photographic and television procedure s documents describ ing the sa me o rsimilar tasks are used as guidel ines. By determining the number of fr ames of eachfilm type required, a preliminary analysis of the film budget is made.personnel a r e then consulted to determi ne that adequate stowage i s available for thefilm magazines.ability of the selected film type and any spec ial film proces sing r equ ired .a cre w briefing on all 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 duration of the inflight task, landmark tar gets , sun angles. spacecr aft atti-tudes, and effects on other cre w activitie s must be consid ered 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 simu lations of the lunar su rfa ce activiti es. Much of t he 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 anddeterm ine the most efficient way of accomplishing the tas ks. Ca me ra settin gs and otherprocedu ral details must be complete by the ti me c rew training pr og res ses 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 determin ed by the data u se r s and oth er personnelsupporting the photographic t asks. The require d came ra se ttings 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 ngi nee rs. Ca me ra set tin gs a r e required earlyin the procedures-development cycle. necess itatin g an early est ablish ment 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. Diagr ams 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 forexperi menta l and operational equipment, and il lust ra tion of the standard procedure fordocumentation of geological sa mp les.

Included in the appendix is an example of t he 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. Cam era decals indicating surf ace-and orbital-photography camern s etting s and 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 f o 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 fi nal rev iew be fore publication of the final photographic proc edur es. Thefina l copy of t he 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 proper integrat ion of the objectives and associ ated p roc edure s into the flightplan. On early Gemini and Apollo miss ions . the photography was mostly limited tooperational photography. On later missions. the scientific objectives and associatedphotographic operations became more extensive.generally con sis ts of covera ge of the nominal m ission events. the major task of integra-tion into the flight plan is making the photographic pro cedur es compatible with the cr ewprocedures 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 cons idered opera ioiia 1 pholography andare accomplished on every lunar mission. On Gemini miss ions , the photographic pro-cedu res wer e placed in a section of the flight plan sep ara te from the time- line section.On Apollo miss ions , the procedu res a r e condensed into the caiiiera conliguration codeas defined in the photographic and television procedures 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 tasks i f real-time reprograming should be required.

Because the operational photography

Contingency photography fo r a mission anomaly o r 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 th e sa me manner(Reference 14 contains a discuss ion on how the basics is the operatio nal photography.flight plan and trajecto ry are determined. ) When the traje ctory p aram eter s 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 inco rpor ated into the Apollo 12mission. Television procedure s and associated time lines are treated very similarly tothe photographic procedures and time lines, and a r e included in the photographic andtelevision procedures document.

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Ope ra t i n a I C o n s d e r at i n sMany operational considerations or constraints ar e of conc ern to th e photographic

engineer and the astronaut in obtaining space-f light photography. Th es e con str ain tsgenerally fall within the following categories.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 abse nce of a light-diffusing atmo sphe re, thes e adve rs e conditions mustbe over come. Photography taken ins ide the vehicle ha s areas of overexpo sure andunderexposure, with sun shafting causing bright illumination and underex posu re causingshadow areas. The crewman generally expo ses the photographs a t an ave rag e settingthat usually does not yield good photography because of the e xt re me 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 mi ssio ns and have adefinite effect on photography. The cre wma n, on many occasion s, does not have thetime to analyze the photographic situation and se t hi s equipment accordingly. In an ef-fo rt to sav e time , photography is generally accom plished with precomputed nominalexp osu re 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 consideration s.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 requires the expenditure of spac ecra ft propellant, 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 greater variety of lenses andfilm types could overcome som e of the lighting const rai nts a t the expe nse of gr ea te rweight, volume. and crew time. A review of figires 6 to 1 7 and 28 to 50. showingGemini and Apollo photography, w i l l i l lustrate some of thes e 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 mar ily , 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 present capability of support operations to generate the data required to pointa given spacecraft line of sight at 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 a w angles and mission time to point windows andbracket-mounted c am er as 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 computer complex (RTCC) pro grams. Suchprograms were conceived and developed to fulfill photographic s well asgeneral, the progr ams can point a fixed line of sight at any cel est ial o r ter rest ria l pointand compute the required 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 signa l 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 track, and elevation angle at t ime ofclose st approach; and to compute sunrise-sunset and moonrise-moonset tim es for theprograms are simulated during the premission training to ensure that they ar e cor rec tand that the comp uters that a r e time share d with other u se rs will be available whenrequired.

operational pacecraft-pointing requi remen ts, such as navigational sightings. In

spacecraft, along with terminator rise and set tim es. 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 procedures , 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 mis sions.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 and

definitions. 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 mat er ia l 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 migratio n of silicon base lubr icant s. Lubricantmigrating from a motor gear box to the motor brus hes caused a high resistance path.Also, when this lubricant migrated fro m its desired area, the area was left with insuffi-cient lubrication. The lubri cant migration was aggravat ed when the equipment remainedon 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 conside red for future program applications wherelong duration and vacuum operation may be a requirement. However, care ful analys is

is requi red to ensur e that the lubrication pro ces s i s compatible with other ma ter ial sused in the mechanism. In short, the requirement for a careful materi als compatibil-ity analys is in the operational environment cannot be overemphasized.Testing requi remen ts in support of space pro gra ms al so have contributed to so meof the problems encountered. Attention mus t be given to the number of equipment tes thours 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 remen ts 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 andmak es every attempt to limit testing to minimum requi remen ts.compounded fur ther by the requi rement that photographic equipment be compatib le witha vacuum and an oxygen atmo sph ere , a requi remen t which resul ted in the us e of speci allubricants and motor brushes that are not necessarily compatible with extended ambientatmos phere operations.le ms of exceeding equipment shelf life; in situat ions 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 ements hasbeen a problem throughout the space- fligh t pr og ra ms because of the insufficient time todevelop the requi red 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 requirem ents fo r the next. Also, because of othercommitments, some of the photographic inves tig ato rs a r e not available for ea rly defini-tion on a total program basis.additions of ite ms like lenses and film type can be read ily 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 se lect film for specific operations and with se-lection of proper exposure param ete rs.the maximum extent possible the number of different films required, 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, certa in basic 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 time recording on film avai l-able.corporation of t his capability in all future photographic s yst ems 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 p roced ureshave inc rea sed correspondingly. Methods have been established for translat ing missionobjectives into specific hardware requireme nts and flight procedures. These methodsappear adequate for pr esen t pro grams but need to be reviewed for future progr ams.A more advanced photographic s ystem for future progra ms should incorporatecerta in fea tur es 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 su ch 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 ireme nts; consequently, the photographic sys tems must rema inflexible 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 record ing on film, automatic recording of ap ertur e and shutte rspeed, and a tie-in with the vehicle navigational syst em so that vehicle attitude can bereadily retrie ved,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 incre ased emp hasis on Earth Resources support by space-flight photog-raphy, the futur e need exi sts for high resolution and photogrammetric cam era sys tem swith lar ge film formats. Also, fro m an economic consideration, th ese syste ms 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 , 1 9 7 2924 -23 26-00-72

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REFERENCES1. Anon. : Mercury P ro je ct Summary, Including Result s of the Fourth MannedOr bi 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 Sta tes Manned Orb ita l Space Fligh t, May 24,1962. NASA SP-6, 1962.4. Anon. : Result s of th e Thir d United Stat es Manned Orbital 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 Resul ts.NASA SP-121, 1966.7. Anon. : Earth Photographs from Gemini Ill, IV, and V . NASA SP-129, 1967.8. Anon. : Ea rt h Photographs f ro m Gemini VI through XI. NASA SP-171, 1968.9. Lowman, Paul D . , Jr . : The Eart h Fr om Orbit . National Geographic, vol. 130,no. 5, Nov. 1966, pp. 644-671.

10. Lowman, Pa ul D. , Jr . : Photography fr om Space eological Application.Annals of New Y o r k Academy of Science, vol. 140, ar ti cl e 1, Dec. 1966,pp. 99-106.11. Lowman, Pau l D. , Jr . ; McDivitt, Ja mes A. ; and White, Edward H . , 11: Terra inPhotography on the Gemini IV Mission: Prelim inary Report.NASA TN D-3982, 1967.12. Lowman, Pau l D . , Jr . : Geologic Orb ita l Photography: Experi ence fr om theGemini Pr og ra m. NASA TM X-63244, 1968.13. Lowman, Pa ul D . , Jr . : Geologic Appli cations 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 E TH O D US E D FO R Q U I C KINTERPRETATION AND INS TRU CT ION TO THE CREW

The equipment to be used for each photographic t ask 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 used in the coded fo rm a r e defined in the following table.

CodeAAACM

LMEVBBBDACELDCTVcscLMCcccDDDCEXHCEXCINBWBW 164HBW

InterpretationLocation from which photographs are takenCommand module

1- eft-hand (LH) ide window2- H rendezvous window3 atch window4- ight-hand (RH) rendezvous window5 H side windowLunar moduleExtravehicular

Camer a usedData acquisition cam eraElectric HasselbladData ca me ra (lunar surface Hasselblad)Television c ameraCloseup stereo camer aLunar multispectral cam era (4EL Hasselblads)Lens used: 5, 10, 18, 60, 75, 80, 250, 500 mm

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CodeIRBWMBW

=,=SPOTIVLMIRBRKTULCPOLZ47B FIL29+ FIL87C FIL58 FILHANDSEXTALCCONT

M

N

0P

InterpretationInf rar ed black and white, SO-246Medium-speed black and white, 3401Data recording aidsSpotmeterIntervalometerRight -angle m ir ro rDAC mounting bracket, EL ca me ra adapter, EL cam er a bracketUtility light clampPolarizing filterPhotar 47B filt er (blue)Photar 29 filter (red) + 0. 5 neutral density filt erPhot ar 87C filter (black)Wrattan 58 filt er (green)Camera handle and triggerSextant adapterAutomatic light control- nterior (TV)Remote control cable

asse mbly (500-mm lens) o r LMC mounting

Lens aper ture setting xamples:f2.8- ocal length, 2. 8S potmeter readingCC- etting on cue card

Shutter speed- xamples:125 /125 second2 sec- secondsFocus distance (feet)For EL and DC: number of fr am esFor DAC: fr am e rat e, magazine, percentag e, and tim e (minutes)

A coded example is shown as follows, followed by the inte rpre tati on of the codedform

CM4/DAC/18/CEX RKT, SPOT (S, 2 5 0 , ~ ) 2 fps, . 5 mag (4 min)

Photographs w i l l be taken from th e CM right-hand rend ezvo us window, using the DACwith an 18-millimeter lens and SO-368 film.the following cam era settings: f-stop fro m spo tm ete r reading, shut ter speed 1/250 sec-ond, focus at infinity, 12 fra mes /se c, 0. 5 magazine or 4 minutes to be used.The c am er a will be bracket mounted with

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PHOTOGR APHIC PROCEDURE WRITEUP USED TO F I N A L I Z EO B J E C T I V E A N D FO R C RE W M AN T R A I N I N G

EXAMPLE: LAND ING AND EXPLORAT IO N S ITES )

D e s c r i p t i o nDuring descent and ascent, the lunar surfac e w i l l be photographed to reco rd LMmovement and sur fac e disturbanc es and to aid in determining the landed LM location.Sextant photography of L ansberg will be accomplished on revolution 26.Following an orbit al plane change after LM jettison, ste reo str ip photographs willbe taken of candidate exploration sit es during two se pa ra te revolutions, using the ELand an 80-millimete r lens. During one stere ostri p and two landmark revolutions, theDAC w i l l simultaneously photograp