Gemini 10 Press Kit - heroicrelics Mirror

P RELEASE NO: 66-179NAI IONAL ACRONAUTICS AND SPACE ADMINISTRATION Wf) ?-11 ,,,WASHINGTON, D C 20546 lELS wcj i-f,9?',FOR RELEASE: FRIDAY A.M.July 15, 1966PROJECT: GEMINI io(To be launched no earlierthan July 18, 1966)

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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WO 2-4155NEWS WASHINGTON,D .C. 20546 TELS. WO 3-6925RELEASE NO: 66-179FOR RELEASE:FRIDAY *OM*July 15, 1966GEMINI 10LAUNCHES SETFOR JULY 18The National Aeronautics and Space Administration willlaunch the Gemini 10 spacecraft and its Agena Target Vehicleno earlier than July 18 from Cape Kennedy, Fla.The mission is one of the most complex manned space flightsto date.The primary mission objective is successful rendezvousand docking of the Gemini 10 spacecraft with the Agena 10 TargetVehicle.Operational goals, subject to time and propellant ex-pended in rendezvous, include rendezvous with the Agena which waslaunched March 16 for Gemini 8, two periods of extravehicularactivity by the pilot and conduct of16 experiments.Command pilot for the three-day Gemini 10 flight is JohnW. Young. Pilot is Michael Collins. Backup command pilot isAlan I;.Bean, and backup pilot is Clifton C. Williams, Jr.Young was pilot on Gemini 3, the first manned mission inthe Gemini program.Collins will make his first space flighton Gemini 10.space.Bean and Williams have not yet made a flight in-more- . 7/9/66

-2-Launch of the Agena is scheduled for 4:40 p.m.EDT withthe Gemini to lift off at 6:20 p.m. EDT. The late afternoonlaunch time is determined by orbital characteristics of thepassive Gemini 8 target vehicle,The Agena 10 w ill be launched into a 185-mile circular orbitby an Atlas Standard Launch Vehicle developing 390,000 poundsof thrust.Gemini 10 will be inserted into an initial 100-by-168 m ile orbit after a boosted flight atop a 430,000-pound-thrust GeminiLaunch Vehicle,Based on perfect timing of both launches, the initial ren-dezvous is scheduled in the fourth revolution, about five hoursafter liftoff, of the Gemini 10.Computation of maneuvers forrendezvous will be done in the spacecraft and will be comparedwith calculations on the ground.After almost an hour of formation flying with the Agena 10,the command pilot will execute the first docking maneuver, Duringthis docking exercise, an electric charge monitor test will beconducted to study the amount of charge that is exchanged betweenthe Gemini and Agena as the TDA probe contacts the Agena.A bending mode check to study the amount of bending stressbetween the docked vehicles will begin over hawaii approximatelysix hours after the Gemini launch.-more-

- 3-About seven hours and 40 minutes into the flight, the crewwill use the Agena primary propulsion system to conduct a seriesof translations (changes of position in orbit).The purpose ofthe translations is to position the spacecraft for a later ren-dezvous with Agena 8.The number, magnitude and direction ofthese translations will be determined by Gemini 10 flight con-trollers after launch of the spacecraft.The determination willbe based on the Agena 8 orbit, Agena 10 liftoff time and orbit,spacecraft launch time and success of the initial rendezvous.Even with a nominal fourth-revolution rendezvous and successfuldocking, these first dual rendezvous translations couldbe conducted to place the docked spacecraft in a circular orbitas low as 138 miles or in an elliptical orbit with an apogee ashigh as 460 miles.The former is a "catch-up" orbit in which the spacecrafttravels faster than the 246-mile-high Agena 8 and overtakes itfrom behind. The latter is a "dwell" orbit with the Agena 8overtaking the slowed-down spacecraft.Necessary height and phase adjustment and plane changetranslations done between 19 and 29 hours into the flight willposition Gemini 10 about eight miles below the passive target.Then,it gradually will overtake the target for the dual rendezvousterminal phase initiation at 47 hours 10 minutes ofelapsed time.-more-

-4-Activities planned between rendezvous maneuvers includetwo more dockings of Gdmini 10 with Agena 10. At 19 hours and26 minutes over the United States, Command Pilot Young will undockin darkness and move the spacecraft three feet back to conductan ion wake measurement experiment (S-26).He then will translate to 60 feet behind the target beforemoving in at half-a-foot per second to re-dock. Pilot Collinswill undock about 30 minutes before daylight, repeat the S-26experiment and the 60-foot translation, then will re-dock some20 minutes after sunrise.About 22 hours and 20 minutes into the mission, the crewwill pcwer-down Agena 10 and separate from it at two feet persecond. The Agena 10 will remain dormant in a co-elliptic orbitnine miles below Agena 8 until ground controllers reactivateit later in the mission.Thirty-five minutes later Collins will open his hatch andstand exposed to space for 55 minutes. During this period ofstand-up extravehicular activity he will carry out five differentphotographic experiments.-more-

-5-He will be connected to the spacecraft oxygen supply byshort hoses and to the cockpit by a nylon tether. Communicationsand biomedical instrumentation will be maintained overa short umbilical extension.For his second extravehicular activity, about 48 hours intothe mission, and lasting 55 minutes, Collins will operate froma 50-foot line using a hand-held maneuvering unit (HHMU). Duringthis EVA he will evaluate the extravehicular life support system(ELSS) and the nitorgen gas-fed maneuvering unit. He also willconduct two micrometeoroid experiments.EVA pilot pickup may be attempted. The command pilotwould then translate the spacecraft toward the extravehicularastronaut, allowing the EVA pilot to return to the spacecraftby pulling himself along the umbilical.An hour after he has returned to the cabin and the spacecrafthas moved away from the Agena 8, Collins once more willopen the hatch to jettison some EVA equipment that includes theumbilical, the maneuvering unit and the ELSS chest pack, theEVA visor and the standup EVA hoses and tether.-more-

-6-A retrograde height adjust translation will lower thespacecraft's orbit in preparation for reentry.Retrofire w illoccur at 69 hours 44 minutes between the Canton and Hawaiitracking stations.Splashduwn should take place about 33 min-utes later in the 44-1 landing zone about 300 miles east ofFlorida.(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS)"-more-

PREFLIGHT ACTIVITIES AND INTEGRATED COUNTDOWNGemini flights are developed by the NASA Manned Spacecraft Center (MSC),Houston, Tex., under the direction of the NASA Headquarters Office of MannedSpace Flight in Washington, D. C. The NASA John F. Kennedy Space Center(KSC), Fla., has the overall responsibility for preflight testing, checkoutand launching of the Gemini and Atlas/&ena vehicles for the Gemini missions.After launch, control of the flight is the responsibility of the MissionControl Center, MSC.Gemini 10 Timetable at Kennedy Space Center:Gemini launch vehicle (GLV) arrived May 18 (first stage) and May 21(second stage) ,GLV erected at bunch Complex 19 on June 7.Gemini 10 spacecraft arrived May 13 for receiving inspection, ordnanceinstalhtion, and assembly checks at Merritt Island,Atlas standard launch vehicle (ASLV) arrived June 1Q erected on LaunchComplex 14 on June 15.Gemini Agena target vehicle (GATV) arrived May 15, the target dockingadapter preceding it on May 4.QATV, docking adapter, and spacecraft underwent "timber tower" tests atKSC Radio Frequency Site June4 ,Docking conrpatability checks conducted June 4-7.Spacecraft and launch vehicle premate tests conducted June 14-16 at Complex 19with electrical mating June 20.Mechanical mating check July 5, sirmuLfaneous countdown dry run July U..Gemini LO countdown is a combination of countdowns referenced to theorbiting passive Agena 8 and associated with the Gemini 10 and Agena 10 launchvehicles, the spacecraf't and the target vehicle, the crew, Houston MissionControl and the worldwide tracking network, the Eastern Test Range, and theRadio-Command Guidance System.Liftoff for the target vehicle is scheduled for the 95-minute mark inthe simultaneous count. The Gemini spacecraf't will be launched approximately100 minutes and 30 secdnds Later, depending on the exact location andperformance of the orbiting Agena. A built-in hold is scheduled at T-3minutes to adjust the Gemini liftoff time to coincide with Agena lo's firstpass over the Cape. After the launch sequence adJustments are computed, thecount will resume,

TimeF-3 daysF-1 dayT-720 minutesT-615 minutesT-390 minutesT-300 minutesLAUNCH VEHICLE COUNTDOWNGeminiStart pre-countStart mid-countGLV propellant loadingComplete propellantloadingBack-up flight crewreports to the 100-footlevel of the White Roomto participate in finalflight preparation.Begin terminal countdown,Pilots' ready room, 100-foot level of White Roomand crew quarters mannedand made ready for primecrew.At las-AgenaCountdownBegin terminal countT-255 minutesT-240 minutesT-235 minutesT-195 minutesT-185 minutesT- 135 minutes"-325 minutesT- 120 minutesT- 119 minutesT-115 minutesT-100 minutesT-95 minutesT-86 minutesT-70 minutesT-55 minutesT-20 minutesT-3 min.,l sec.T-04 secondsT-0 secondsTS2 minutes 36 secondsTS-5 : 36T+5 : 56T+6:09Medical examinationEatCrew leaves quartersCrew arrives at readyroom on Pad 16Purging of suit beginsCrew leaves ready roomFlight crew to Complex 19Crew arrives at 100-foot1 eve 1Crew enters spacecraftClose spacecraft hatchesWhite Room evacuationBegin erector loweringSpacecraft OAMS staticfiringBu i 1 t - in ho IdGLV ignitionLift offBooster engine cutoff (BECO)Second stage engine cutoff(SE CO)Spacecraf t-launch vehicleseparationInsertion into orbitStart tower removalLift offInsertion into orbit-more-

-9-REENTRY(Elapsed Time from Gemini Lif t-Of f )- Time69 : 4469 : 457 0 : 03 : 0470:05: 1270:05: 1970: 10:0670: 11:4970: 13 : 237 0 : 17 : 48RetrofireJettison retrograde section400,000 feet altitudeCommunications b 1 ac kou tInitiate guidanceBlackout endedDrogue chute deployed (50,000 feet)Main chute fully deployed ( 11,000 ft.)Spacecraft landing-more-

-10-MISSION DESCRIPTIONInformation presented in this section is based on anormal mission. Several alternatives exist through whichflight objectives can be achieved. The complexity of themission increases the possibility of modifications ordeletions to the flight plan even as the flight progresses.Many maneuvers included in the flight plan will beused only as necessary to place the vehicles involved in theproper positions. Components of these maneuvers will bedetermined during the mission. Therefore, velocity incrementsand orbital values are not available for this preflightdescription in many cases.(All orbital parameters are given in statute miles.To convert to nautical miles, multiply by .87; to kilometers,multiply by 1.61.)LAUNCHLaunch Times -- Atlas-Agena: 4:40 pm, EDT, Launch Complex 14.Gemini 10: 6:20 pm, EDT, Launch Complex 19.Launch Window -- Agena launch window lasts about 20 minutes.Gemini 10 window opens about 100 minutes and 30 secondsafter Agena liftoff. The window opens at the M=4 pane --the opportunity to achieve rendezvous in the fourthrevolution. This pane lasts approximately 35 seconds.Opportunity to rendezvous in later revolutions, throughM=20 (the 20th revolution) exists for about 30 minutes.However, only the 35 second M=4 pane will be used for thefirst launch attempt. A decision on use of the extendedwindow and whether to recycle 48 hours will be made whenand if the originally scheduled launch is postponed.Azimuth -- Atlas-Agena will be launched along an 84.4 degreeazimuth east of north into a near-circular orbit of185 miles with an inclination of 28.87 de rees. Gemini10 launch azimuth will be biased from 96. % to about98.7 degrees so that a small amount of launch vehicleyaw steering will place the spacecraft in the Agena 10target plane at the beginning of rendezvous terminalphase, thus eliminating necessity of a plane change.INITIAL RENDEZVOUSOrbits -- Agena 10 at near-circular 185 miles. Gemini 10initially in elliptical 100-168 miles. Gemini trailsAgena 10 by 1160 miles.-more -

-11-Incremental Velocity Adjustment Routine (WAR) -- Spacecraftthrusters used at insertion to correct in-plane velocityerrors of 3 to 200 feet per second.Phase Adjustment (NC1) -- Near spacecraft second apogee, 2:18GET, a posigrade horizontal burn of 54.7 fps raisesperigee to 134 miles and reduces catch-up rate to 4.4degrees per orblt. Spacecraft trails by 440 miles.(Over Tananarive )Coelliptical Maneuver (NSR) -- Near third apogee, 3:48 GET,a Posiarade burn, mainly horizontal with the spacecraftpitchez up about-4 degrees, will add a velocity of51.2 fps and circularize the orbit to 168 miles. Geminitrails by 126 miles, is catching up at 2.3 degrees erorbit, should have radar lock-on. (Over Tananarive PTerminal Phase Initiation (TPI) -- Near the end of the thirdrevolution, 4:36 GET or about three minutes beforedarkness, a posigrade burn with the spacecraft pitchedup along the line of sight to the target puts thespacecraft on an intercept tra ectory with Agena 10,which it trails by 38 miles. Over Hawall)Intermediate Corrections -- During terminal phase the targetwill travel 130 degrees. Two spacecraft trajectorycorrections may be made. They are at 12 and 24minutes after TPI, 82 and 34 degrees of orbital travelfrom the target, respectively.Terminal Phase Final (TPF) -- Velocity matching maneuver ofabout 45 fps excluding any additional requirements dueto semioptical techniques used for final approach,executed to complete rendezvous at 5:08 GET or aboutseven minutes from daylight. (Southeast of Ascension)FIRST DOCKINGAfter the velocity matching maneuver to complete rendezvous,the spacecraft will fly in station-keeping formationwith Agena 10 until the first docking is performed by thecommand pilot at 5:5O to 6:oo GET. Agena 10 will be positionedat a 90-degree yaw with the target docking adapter facingnorth; the spacecraft, also at a 90-degree yaw, will pointsouth. This configuration gives optlmum lighting conditionson the target. (West of Hawaii)-more -

-12-BENDING MODE CHZCKA t 6:OO GET the spacecraft, in docked configuration,w i l l be qiven a three second pitch-down thrust immediatelyi’o1loKed DY three seconds or’ pitch-up thrust. After twominutes of stabilization, the spacecraft will be given athree second yaw left thrust then a. three second yaw rightthrust. After ten seconds of stabillzation, the spacecraftw l l l swing the dccked unit back into the direction of flight,Agena 10 target docking adapter forward.DUAL RENDEZVOUS MANEWERSHelsht Adjust Translation -- A t 7:38 GET, an orbit adjustingmaneuver to be determined on establishment of relativepositions of Gemini 10 and Agena 8. Agena 10 primarypropulsion system w i l l be used.Phase Adjust Translation -- At 8:25 GET, a phase adjustingmaneuver or maneuvers to be determined. This and theprevious maneuver could result In a circular orbit aslow as 138 miles or an elliptical orbit about 185 by460 miles. Agena PPS will be used.Plane Change Translations -- A t 19:lO GET, a plane changemaneuver or maneuvers as necessary to bring the spacecraft/targetdocked configuration Into the Agena 8 plane.Agena 10 secondary propulsion system will be used.FIRST UNDOCKING, SECOND & THIRD DOCKINGSA t 19:25 GET the command pilot will undock from Agena 10and translate to three feet from the target docking adapterat one-half‘ foot per second. He w i l l conduct the ion wakemeasurement experiment (s-26), translate 60 feet from Agena10, then translate back toward the target at one-half footper second. He will dock at sunset over the west coast ofAfrica.From ZO:O5 to 20: 10 the pilot will undock, translatethree feet from the TDA, conduct the S-26 experiment, translateto 60 feet and back to dock at one-half fps. Dockingw i l l occur at 20:55 in daylight over the Pacific Ocean.FURTHER DUAL RENDEZVOUS MANEWERSHeight Adjust Translation -- At 21:22 GET, or 14th perigee,a maneuver based on updated ground values will refinethe docked unit’s apogee to eight miles below theAgena 8 orbit. (Over Canary Islands)-more -

-13-Coelliptical Maneuver -- A t 22:08 GET, 15th spacecraftapogee, a ground updated maneuver wl.11 circularizeGemini 10's orbit eight miles below the Agena 8orbit. This is the final of the docked configurationburns. Following a posigrade OAMS translation toseparate the spacecraft from Agena 10, the pilot willcommand shutdown of Agena 10 systems. The targetvehicle w i l l remain in its 238-circular orbit untilreactivated by the ground.STANDUP EVANear the Canary Islands at 22:55 GET, the pilot willopen the right-hand spacecraft hatch and stand erect. Theoxygen inlet on his suit will be connected to the spacecraftenvironmental control system (ECS) by an 18-inch extension,his suit outlet by a 24-inch extension hose. A similarcommunications and bio-instrumentation electrical extensioninterconnects those systems; a nylon tether restrains thepilot in the cabin.After sunset at 23:O2 GET, the pilot begins the ultravioletastronomical camera experiment (S-l3), which continuesthrough 36 minutes, 14 seconds of darkness. At sunrisehe transfers the 70 mm Maurer camera and bracket tothe command pilot, receives the MSC-8 Maurer camera andextension rod, and photographs the slate holding colorpatches of red, yellow, blue and gray. Assembly of the colorpatch photography experiment and the photography togethertake about nine minutes. He hands the slate to the commandpilot, jettisons the extension rod, and conducts the synopticterrain and synoptic weather experiments (S-5 and -6) usingthe 70 mm Maurer camera and the remaining film in themagazine .Ingress and hatch closing at 24:lO GET, terminate thestandup EVA west of the Canton tracking station.AS NEEDED DUAL RENDEZVOUS MANEUVERSTo minimize dispersions in position, velocity, and timeof arrival at dual rendezvous TPI, a series of maneuvers basedon updated values from ground tracking stations is allowedin the flight plan. Under nominal conditions, the values ofthese maneuvers are zero in each case. True values from theground updates w i l l be applied and the maneuvers made ifrequired.-more -

-14-The maneuvers scheduled are:Phase adjustmentHeight adjustmentPhase adjustmentCorrective combinationCo -elliptical28:45 GET40:15 GET41:OO GET45:OO GET45:30 GETDUAL RENDEZVOUSTerminal Phase Initiation (TPI) -- Certain ground rules andconstraints have been established for dual rendezvous TPI.They Include:Spacecraft on-board radar not available for rendezvous;Visual acquisition of target;Target must be continuously illuminated by the Sun (sincetarget has no acquisitlon lights);Sun should be overhead at TPI, and five to ten minutesfrom setting at TPP; thus establishing a requirement for an80-degree terminal phase travel angle.A t i)7:lO GET, terminal phase will be Initiated by atranslatlon, posigrade and pitched up, of a magnitude tobe computed by the crew using the spacecraft reticle boresightedon the target. If the target has not been visuallyacquired at the time 01’ TPI, updated ground values will beapplied to determine the maneuvel . Mid-course correctionsalso will be computed f’rom the optical tracking technique.The pilot, using the Gemini sextant, w i l l determine time ofarrival 2.3 miles from the target, then will calculate thebraking maneuver necessary to reduce the closing rate to30 fps. A t 47:31 GET, the spacecraft shculd be in aformation-flying pcsltion bo feet from Agena 8.-more -

-15-UMBILICAL-EVAThe pilot will begin umbilical-EVA by opening the spacecrafthatch at 48:08 GET, over the Indian Ocean west ofCarnarvon some five minutes before sunrise. He will standIn the hatch and, with help from the command pilot, feedthe umbilical out of the hatch. At sunrise he will move fromthe cabin and move along the handrail to the nitrogen fittingon the external adapter section surface. Inserting the quickdisconnectfitting on the nitrogen hose Into the spacecraftfitting and opening the nitrogen valve to activate flow ofpropellant to the HHMU, he will move back to the cabin area,collect the micrometeoroid experiment (S-12) and hand it tothe command pilot.He will take the EVA motion picture camera from thecabin, Install in on the spacecraft adapter Just behind thepilot's hatch, and turn It on at one frame per second. Thenhe will fire the HHMU to check Its flow,Ten minutes into the extravehicular activity, the pilottranslates to the Agena 8 to attach a new S-10 micrometeoroidcollection package and return the old S-10 package to thecommand pilot. From 30 to 40 minutes into the EVA, thepllot uses the hand-held maneuvering unit to translate to 30feet in front of the spacecraft, stop his translation rates,then move along the line of sight to the Agena.Following the HHMU evaluation, the pilot will drift atnulled rates until the command pilot translates the spacecraftto him for the EVA pilot pickup maneuver. The final10 minutes of EVA will be used for evaluation of theumbilical dynamics, Before ingress, the pilot will turn offthe nitrogen valve on the spacecraft adapter. He will bleedthe HHMU of remaining propellant by holding on to theadapter handrails and firing the maneuvering unit in shortbursts. He will unplug the nitrogen umbilical, return tothe hatch, retrieve the EVA camera, and close the hatch.EVA will end at sunset over the Atlantic southeast of theUnited States.Following a four fps retrograde separation from Agena 8,the pilot will reopen the hatch and jettison a bundle ofEVA equipnrent,RETROFIRERetrofire will occur at 69:U GET between Canton andHawaii, with splashdown in the W est Atlantic 44-1 landingarea some 300 miles east of Florida at 70 hours 17 minutesground elapsed time.-more-

-1 6-AGENA MANEUVERS FOLLOWING SPLASHDOWNAgena 10 will be maneuvered into a parking orbit ofabout 250 miles after Gemini 10 splashes down. The targetvehicle will be in such an orbit that it can be used as arendezvous target for the later missions.ORBITS - REVOLUTIONSThe spacecraft's course is measured in revolutionsabout the Earth. A revolution is completed each the thespacecraft passes over 80 degrees west longitude, or atGemini altitude about once every 96 minutes.Orbits are referenced to space and in Gemini take about90 minutes.The longer time for revolutions is caused by the Earth'srotation. As the spacecraft circles the Earth, the Earthmoves some 22.5 degrees in the same direction. Although thespacecraft completes an orbit in about 90 minutes it takesanother six minutes for the spacecraft to reach 80 degreeswest longitude and complete a revolution.Gemini completes 16 orbits per day, but in 24 hourscrosses the 80th meridian of longitude 15 times -- hence 15revolutions per day.-more -

EXPERIMENTSSixteen experiments are scheduled for Gemini 10. Eight have been flownon previous flights. The experiments are divided into three categories:scientific, seven experiments; technological, eight experiments; and medid,one experiment.S- 1 Zodiacal Light PhotographySCIENTIFICPurpose - To obtain photographs of the zodiacal light atsunset, and to obtain photographs of the airglow covering the entire horizonduring the night.Equipment - Modified 35mm Widelux camera, Model F VI/Field of view 50 degrees.Lens opening is f/l. Focal length 2Qmn. Weight 3.5 pounds. Film -Eastman Tri-X35m, ASA 400, B & W, 18 exposures.Procedure - The pilot will mount the camera on the right hand window. Thecomnand pilot will orient the spacecraft attitude with the reticle, using celestialreferences. The pilot will then perform photography and record the times. Whennot in use, the camera is stowed in the left hand aft food box.Experimenter - Dr. E. P. Ney, University of Minnesota.Note: Also flown on Gemini 5, 8, 9.S-10 Micrometeorite CrateringPurpose - To collect craters of micrometeoroid impacts on different types ofmaterials and return them for Laboramry analysis.Equipment - Micrometeorite impact package is mounted on the target dockingadapter of the Agena before liftoff. The rectangular package is hinged to foldopen and expose eight plates, but will not be opened for this experiment.Procedure - The package will be launched onboard the Agena in the closedposition. It will be retrieved by another EVA pilot on a later rendezvous flightand analyred for meteoroid impact and cratering.Experimenter - Dr.Albany, New York.Curtis Hemenway and Royce Coon, Dudley Observatory,Note: Also flown on Gemini 8 and 9. Not fully activated on Gemini 8, butthe package is expected to be recovered during the umbilical EVAon this flight.S-12 Micrometeorite CollectionPurpose - (1) To collect ultra-small meteoroids in near Earth space tostudy the nature and frequency of hyperballistic impacts under in-flight conditions,(2) to expose microbiological specimens to the space enviroment todetermine their ability to survive the vacuum, extreme temperatures, andradiation, and (3) to search for any organisms capable of living on micrometeoroidsin space.-more-

-18-Equipment - Aluminum collection box, 11 inches long by 5.5 inches wideby 1.25 inches deep, weighing 7 pounds, 6 ounces. The device has two collectioncompartments and an internal electric motor and thermally insulated batteries.The collection compartment materials are aluminum-shadowed 200 Angstrom thicknitrocellulose and formvar mounted on 200-mesh copper screening. They are thesame collection materials used by the experimenters in previous rocket, balloonand aircraft sampling experiments.Procedure - The experiment will be mounted in the retro adapter directlybehind the pilot's hatch. The hinged lid can be opened and closed electricallyfrom inside the spacecraft. It is planned to open the experiment only duringthe first eight-hour sleep period of the crew when the spacecraft is in driftingflight in order to avoid contamination by the OAMS system. One of the compartmentswill be sterilized to determine the presence or absence of microorganismsin the micrometeorites collected. When returned to the laboratory,cultures designed for non-terrestrial organisms will be prepared to determineif any types of life are present in the sample. A set of representative Earthmicroorganisms such as bacteria, molds, and spores will be placed in the nonsterilecompartment. They will be quantitively assayed after the flightexposure to deterinine the fractions which survive. During the first portion ofEVA, the pilot will lock the collection box and return it to the spacecraftcabin.Experimenter: Dr. C. Hemenway, Dudley Observatory, Albany, N. Y.Note: Also flown on Gemini 9.S-6 SvnoDtic Weather PhotonraDhvPurpose - To make use of man's ability to photograph cloud systemsselectively -- in color and in greater detail than can be obtained from thecurrent meteorological satellites.Equipment - A 70mm Maurer camera with 8Omm Zeiss F2.8 lens; two magazinesof color film with 65 exposures each.Procedure - Any system which the pilot recognizes as being significantshould be photographed. Such areas would include squall line clouds, thunderstormactivity not associated with squall lines, frontal clouds and views offronts, jetstream cirrus clouds, tropical and extratropical cyclones, waveclouds and broad banking of clouds in the trade winds or other regions.Experimenter: K.M. Nagler, U. S. Weather Bureau.Note: Also flown on Gemini 4, 5, 6, 7.5-5 Synoptic Terrain PhotographyPurpose - The purpose of this experiment is to get high quality, smallscale photographs of selected parts of the earth's surface for use in researchin geology, geophysics, geography, oceanography, and other fields.-more-

-19-Procedure - The experiment will consist of taking pictures of certainareas and features along the flight path with a 70 mm camera, hand-held ormounted, using panchromatic, infrared or color film. Precise attitude controlis not required, but moderately high camera depression angles (angle betweenthe horizontal and the camera axis), preferably between 45 degrees and 90degrees, are desired.Equipment - Camera will be the 7Omm Maurer with 8 hlens.focal length standardExperimenter - Dr. Paul D. Lowman, NASA Goddard.Note: Also flown on Gemini 4, 5, 6, 7.S- 13 UV Astronomical CameraPurpose - Primarily to devise and test the techniques for ultravioletphotography and spectroscopy under vacuum conditions. To investigate the distributionof light intensity in the ultraviolet portions of stellar spectra downto a limit of 200 QA. Also to explore the ultraviolet spectra of 0 and B starsand some of the planets.Equipment - 7Omm Maurer camera with 73;mn f3.3 UV Mauer lens.Procedure - The spacecraft is oriented toward the star field to bephotographed. The cabin will be depressurized and the hatch opened. The camerawill be positioned manually and guided by the pilot. A defraction grating willbe used to obtain spectrograms of the desired stars and planets.Experimenter - Dr. Karl Henize, Dearborn Observatory.S-26 Ion Wake MeasurementL_Purpose - To investigate the ionosphere wake of an orbiting spacecraft;i.e. to measure charged particle densities and temperatures within the wakerelative to those of the ambient plasma. To evaluate the possibility of usingthis ionosphere wake as a guidance mechanism to facilitate rendezvous. Additionaldata generated in performance of the experiment will include measurementof the electrical potential difference between the vehicle and surroundingmedium.Equipment - Using a five-element retarding potential analyzer with asimple electronic switching arrangement, measurements will be made of positiveion density, electron density, i o n temperature or energy distributionfunction and vehicle potential with respect to the surrounding ambient. Thethree sensors and preamplifiers are connected to an electronics package consistingof a power conditioner, signal generator and data conditioner. Akeycomponent is the master clock used to generate the carrier in the phasecoherent system and to sequence the modes and biases applied to the sensorelectrodes.-more-

-20-Procedure - The analyzers are mounted on the outside but flush withthe front furface of the docking cone of the Agena target docking adapter.The instrument system will be activated by ground command at a time sufficientlyin advance of the actual rendezvous and docking to insure a suitable sample ismade of the ambient plasma characteristics. Continuous sampling of ion densityand electron density and energy during the rendezvous maneuver would provideprofiles through the wake behind Gemini 10. The actual traverse of the detectorswould be determined by analysis of the rendezvous operation after the flight.In addition to making measurements during the rendezvous maneuver, it isdesireable to have the Gemini spacecraft maneuver laterally with respect tothe Agena axis and "sweep" the wake across the detectors and to map it in atransverse manner. This maneuver is repeated with several separations betweenthe spacecraft at distances of a few feet.MEDICALM-5 Bioassav of Bodv FluidsPurpose - To collect body fluids before, during and immediately afterflight for analysis of hormones, electrolytes, proteins, amino acids and enzymeswhich might result from space flight.Procedure - Urine will be collected in a special bag for each elimination.A specified amount of tritiated water will be added automatically. The waterhas a tracer amount of radio-active tritium. By comparing the amount of tritiumin the sample with the known amount of tritium placed in it, biochemists canmeasure the total volume. Twenty-four 75 cc capacity sample bags will becarried. A sample will be drawn for each elimination. The remaining urinewill be transferred into the urine dump system of the spacecraft.Experimenter - Dr.L. F. Dietlein, MSC.Note: Also flown on Gemini 7, 8, 9.TECHNOLOGICALPurpose - To determine the feasibility and operational value of starocculting measurements in the development of a simple, accurate and selfcontainedorbital navlga-tional capability.Equipment - As much of the existing Gemini onboard equipment as ispossible will. be used for the recording of photometric sensor output signalintensity and time. A photoelectric sensor also is necessary for performanceof the navigational- studies. The photcelectric sensor consists of atelescope, eyepiece, reticle, partially silvered mirror, iris, chopper,optical filters, photomultiplier, pre-amplifier and associated electronics.The instrument is hand-held to the astronaut's eye for viewing out thespacecraft window.-more-

-21-Procedure - As the astronaut views the horizon, he looks for brightstars about to be occulted. He then points the telescope at one and centersthe star within a reticle circle. A portion of the radiation is then divertedto a photomultiplier. With a hand-held switch, the astronaut initiates acalibration mode in which the intensity of thc> star is measured automatically.He then tracks the star within the reticles as the star passes into the atmosphereand behind the edge oE the earth. 'rhci tracking period for each star isapproximately 100 seconds.Experimenter - Capt. 11. Kozuma, U. S. Air ForceNote: Also flown on Gemini 7.D-10 Ion Sensing Attitude ControlPurpose - A navigation system which can sense vehicle attitude (yaw,pitch, roll) by utilizing the flow variations of the space environment on aspecially*designed system-E uipment - Two experimental packages or booms (one for yaw, one forpitch ocated in the adapter section of the vehicle. The unit weighs 10pounds, require 10 watts and are approximately 5x6~13 inches in size. Thereare seven computated data points and the packages operate at an angle of plusor minus 15 degrees. -Procedure - The deployment of the two booms, followed by the firing ofthe flap-releasing - pyrotechnics, _ _is accomplished by one of the astronauts viaa set of switches in the cabin. An additional switch, also in the cabin,applies and removes the main power input to each unit. Both yaw and pitchoperations are simultaneous and the boom deployment, followed by flap release,are one-time operations.Experimenter - Capt. E. Vallerie, U. S. Air ForceMSC-3 Tri-Axis MagnetometerPurpose - To monitor the direction and amplitude of the Earth's magneticfield with respect to an orbiting spacecraft.Equipent - An adapter mounted tri-axis f luxgate magnetometer.Procedure - The astronaut will operate the experiment as the spacecraftpasses through the South Atlantic Geomagnetic Anomaly. The magnitude of thethree directions of the Earth's magnetic field will be measured with respectto the spacecraft.Experimenter - W. D. Womack, MSCNote: Also flown on Gemini 4, 7

-22-MSC-6 Beta SpectrometerPurpose - Prior to the Apollo missions it will be necessary to predict,as accurately as possible, the radiation doses to which the astronauts willbe subjected so that the degree of hazard can be assessed for each missionand preventive measures taken. The Beta Spectrometer experiments will provideaccurate data on the electron source term. This source term data will be aninput to computer calculations for dose due to secondary x-ray emission.Equipment - The spectrometer must be mounted in the adapter equipmentsection. The mounting is such that the axis of the electron cone is normalto the plane of the outward face of the bremsstrahlung spectrometer detector.The electron acceptance cone must have an unobstructed view of the environmentexternal to the spacecraft. The spectrometer will be wired to power from thespacecraft power supply.Procedures - A bremsstrahlung spectrometer will be carried on the BetaSpectrometer. The bremsstrahlung will measure x-rays produced by electronsimpinging on the spacecraft. The bremsstrahlung readings will be comparedwith the results of electron computer calculations to verify or adjust thecomputer code.Experimenter - J. Marbach, MSCMSC- 7 Bremsstrahlung SpectrometerPurpose - When a spacecraft passes through a region of high free electronconcentration an interaction takes place between the vehicle structure andthe electrons, producing a continuous x-ray spectrum. This experiment isdesigned to measure the bremsstrahlung flux as a function of energy immediatelybehind the vehicle when the vehicle passes through the South Atlantic anomaly.Equipment - The bremsstrahlung spectrometer will consist of an x-raydetection system. It will be mounted on the inner wall of the pressurizedcabin. The only modifications required will be those allowing for mounting,power and telemetry connections.Procedure - After the spectrometer is mounted and checked out, the onlyexperimental procedure will be turning the spectrometer on and off at thecorrect time.Experimenter - R.Lindsey, MSC.MSC-8 Color Patch PhotographyPurpose - What effect the environment of space will have upon the colorphotography taken in cislunar space and on the lunar surface during the Apollomission is not known. If optimum photography is to be obtained during anApollo mission, the influence of the UV energy transmitted by the Apollo cameralens must be known. This experiment will show that.-more-

-23-Equipment - Equipment will consist of the 7Omm Maurer still camera with8Omm f2.8 standard lens and back, color film similar to that which will beused used during an Apollo mission and a slate 4% x 4% x k inches in dimensionsupporting four color patches.Procedure - Prior to launch, a slate holding four National Bureau ofStandards color patches will be photographed under controlled lighting conditionswith the camera loaded with film similar to that which will be usedduring a Apollo landing mission. After insertion into orbit the pilot willphotograph the slate from outside the spacecraft and oriented to receive themaximum solar illumination.Experimenter - J. R.Brinkman, MSC.MSC- 12 Landmark Contrast PleasurementPurpose - To acquire reference data for Apollo guidance and navigationsystem design. Principally, to measure visual contrast of land-sea boundariesand other types of terrain to be used as navigation landmarks.Equipment - Same as that used on D-5 plus 16mm movie camera and the additionof two optical filters which fit over the objective lens of the experimentphotometer. Filters are each two inches in diameter and about t inch thick.Procedure - The photometer will be mounted to the right-hand window as inthe star occultation experiment. Several minutes before the landmark is expectedto appear over the horizon, the observer turns on the power supply. The spacecraftis then turned so that the photometer points normally toward the expectedlandmark direction, and then rotated to put the sun at the observer's back,thus shading the window from direct sunlight.Experimenter - C. E.Manry, MSCNote: Also flown on Gemini 7MSC-:,Lunar W Spectral ReflectancePurpose - To determine the ultraviolet spectral reflectance of the lunarsurface between 2,000 and 3,200 angstrom.Equipment - The 7Omm Maurer still camera and W lens will be used forthis experiment. An objective grating attachment for the canera will be usedfor spectrograms, and interference filters will be used for side band photography*Procedure - Several spectrograms will be made of the solar radiationreflected-from the lunar surface. The spectrograph is similar to a camera inoperation. Thus the procedure is similar to photographing the moon. Exposuretimes will vary from one to 50 seconds. The spectrograph will be swivelmounted so that the pilot can guide the spectrograph during the longer exposures.The command pilot will keep the spacecraft oriented toward the moon.Experimenter - R. C. Stokes, MSC.

-24-CREW PROVISIONS AND TRAININGCREW TRAINING BACKGROUNDIn addition to the extensive general training received prior to flightassignment, the following preparations have or will be accomplished prior tolaunch:1. Launch abort training in the Gemini Mission Simulator and the DynamicCrew Procedures Simulator.2. Egress and recovery activities using a crew procedures developmenttrainer, spacecraft boilerplate mdel and actual recovery equipment and personnel.Pad emergency egress training using elevator and slide wire, and breathingapparatus.3. Celestial pattern recognition in the University of North Carolina’sMorehead Planetarium at Chapel Hill.4. Zero gravity training in KC-135 aircraft to practice EVA. Stowage anddonning of EVA equipment is done in aircrafe and crew procedures trainer.Additional EVA training is performed in 20-foot chamber at vacuumconditions.5. Suit, seat and harness fittings.6. Training sessions totaling approximately 15 hours per crew member onthe Gemini translation and docking simulator.7. Detailed Agena and Gemini systems briefing; detailed experiment briefings;flight plans and mission rules reviews.8. Participation in mock-up reviews, systems review, subsystem tests, andspacecraft acceptance review.9. Ejection seat training.During final preparation for flight, the crew particpates in network launchabort simulations, joint combined systems test, and the final simulated flighttests. At T-2 days, the major flight crew medical examinations will be administeredto confirm readiness for flight and obtain data for comparison withpost flight medical examination results.GEMINI 10 SUITSThe pressure suit worn by the command pilot will be similar to suits wornon Gemini 4, 5, 6, 8, and 9. The pilot will wear a suit with special thermalprotective cover layers for EVA activities.-more-

-25-COMMAND PIUT SUITThe Gemini command pilot's suit has five layers and weighs 23 pounds.The layers are, starting inside the =it:1. White cotton constant wear undergarment with pockets around the waistto hold biomedical instrumentation equiprment2. Blue nylon comfort layer3. Black neoprene-coated nylon pressure garment4. Restraint layer of nylon link net to restrain pressure garment andmaintain its shape5. White HI-1 nylon outer layerPILOT SUITThe pressure suit worn by the Gemini 10 pilot weighs 33 pounds and isidentical to the Gemini 4 and Gemini 8 pilot suit with the followingexceptions:1. No extravehicular thermal over-gloves will be worn. Thermalprotection for the hands is now integrated in a basic suit glove.2. The material is now a layer-up of neoprene-coated nylon, the samematerial as the pressure retention layer.3* The inner visor is a polycarbonate oaterial which provides impactand micrometeoroid protection.The Gemini extravehicular suit has seven layers: 1-4 and 7 are identicalto the command pilot's suit.5. Thermal protective layer of seven layers of aluminized mylar withspacers between each layer.6. Micrometeoroid protective layer .For extravehicular activity, the pilot will wear a detachable overvisorwhich has attach points on both sides of the helmet and can be swiveled intoposition over the face-plate. The overvisor is gold-coated and providesprotection for the eyes from solar glare.When the cabin is depressurized, the suits automatically pressurize to3.7 pounds per square inch to provide pressure and breathing oxygen for bothcrew members.EXTRAVMICULAR LIFE SUPFORT SYS!L'E24 (ELSS)It is a 42-pound rectangular box which is worn on the chest. It provideselectrical, mechanical and life support connections between the EVA astronautand the spacecraft. System is 18 inches high, 10 inches wide and six inchesdeep,, It contains ejector pump for circulation, a heat exchanger for cooling-more-

-26-air, a 30 minute emergency oxygen supply. Controls and a warning system forthe emergency oxygen supply are mounted on the top of the unit, Used Incombination with the M, the ELSS functions as a suit pressurization andair supply system during EVA.HAND-HELD MANEwERlNG UNIT (m)This unit is similar to the unit used by Ed White on Gemini 4 andscheduled for use by Dave Scott on Gemini 8. A minor modification ha8 beenadded since the Gemini 8 mission as well as a different fuel and fuel sourcelocation. A handle has been added providing a forward and reverse. The unitis used to provide the extravehicular astronaut with positive control of hisattitude and to propel him from point to point inthe zero gravity environmentof free spce. Nitrogen fuel bottles are now located in the adapter section.The fuel is fed to the EIIIMU throw the umbilical. MaJor coaponents of thegun, In addition to the two handles, include two sprlng loaded poppet valves,foldable tubes, two one-pound nozzles, and one two-pound nozzle. It weighsabout three and a half pounds and is stored in the cabin during Launch. Theunit is I2 inches long by inches, and 15 inches retracted. Tractor andbraking thrust ranges up to two pounds, and the total delta velocity of thegun is 84 feet per second,The umbilical tether for Gemini 10 EVA is a "Siamese umbilical" manufacturedby McDonnell Aircraft Corp. It includes two fluid tranemlssion hosee,one for oxygen and one for the nitrogen BIiMu fuel. The nitrogen hose, 3/80inch inside diameter, is about 60 feet long; the oxygen hose, 1/4-inch insidediameter, is 54 feet; the 1,OOO-pound test nylon tether which governs the distanceaway from the spacecraft the EVA astronaut can mve, is 50 feet long.When snubbed into the restraint eye at the nose of the spacecraft, theumbilical tether will penult mvement to about 40 feet from the spacecraft.Electrical power, codcations and bio-instrumentation hardlines also arecontained in the umbilical. The hoses are protected from temperature extremesby a wrapping of aluminized myylar. Hoses, hardlines and tether are encased ina sleeve of white nylon. Outside diameter of the sleeve-covered unit Is 2 Inches.MEDICAL CHECKSAt least one medical check a day wlll be =de by each crew meniber.Perforned over a convenient ground station, a check will consist of oraltemperature and food and water intake evaluation.Solid Wastes -- Plastic bag with adhesive lip to provide secure attachmentto the body. Contains germicide which prevents formation of bacteria and gas.Adhesive lip also uoed to form seal for bag aPter u0e and bag Is etowed inempty food container box and brought back for analysis.Urine -0 Voided into fitted receptacle connected by hose to either acollection device or overboard dump.

-27-WATER MEASURING SYSTEMA mechanical measuring system has been added to water gun. It consistsof a neoprene bellows housed in a small metal cylinder mounted at base of gun.The bellows holds one-half ounce of water. When plunger of gun is depressed,a spring pushes water out of bellows and through gun. A counter in right sideof gun registers number of times bellows is activated. Each crewman willrecord how much he drinks by noting numbers at beginning and end of each useof gun.Number of Meals -- Nine per astronaut for mission.Type -- Bite-sized and rehydratable. Water is placed in rehydratableswiththe water gn. Bite-sized items need no rehydration.Storage -- Meals individually wrapped in aluminum foil and polyethelene,polyamide laminate. All meals are stored in the right aft food box over thepilot's right shoulder.-more-

GEMINI 10 FOOD MENU(THREE-DAY MENU CYCLE)DAY 1: Meal C(R) Beef pot roast(R) Potato salad(B) Cinnamon toast(R) Chocolate pudding(B) Brownies(R) TeaCalories11914356307241- 32898DAY 3: Meal B(R) Shrimp cocktail(R) Beef and gravy(R) Corn(B) Toasted bread cubes(B) Fruitcake (Pineapple)(R) Orange grapefruit drinkCalor i e s7160105161253- 83881DAY 2: Meal A(R) Applesauce(R) Sugar coated flakes(B) Bacon squares (double)(B) Cinnamon toast(R) Cocoa(R) Orange drinkDAY 2: Meal B(R) Pea Soup(R) Tuna salad(B) Cinnamon toast(B) Fruitcake (date)(R) Pineapple grapef ruitdrinkDAY 2: Meal C(R) Beef and vegetables(R) Meat and spaghetti(B) Cheese sandwiches(R) Apricot pudding(B) Gingerbread cubes(R) Grapefruit drink13913918056190- 837872202145626 2- 838359870158300183- 83892DAY 3: Meal A(R) Peaches98(B) Strawberry cereal cubes 171(R) Sausage patties (2) 223(B) Cinnamon toast 56(R) Orange drink a3(R) Grapefruit drink83714-DAY 3: Meal C(R) Potato soup(R) Chicken salad(B) Beef sandwiches(R) Butterscotch pudding(R) TeaSUPPLEMENTARY FOOD: Meal A(R) Fruit cocktail(R) Toasted oat cereal(B) Bacon squares (double)(R) Ham and applesauce(B) Cinnamon toast(R) Orange drink(R) Pineapple grapefruit drinkSUPPLEMENTARY FOOD: Meal B(R) Shrimp cocktail(R) Chicken and gravy(B) Toasted bread cubes(B) Fruitcake (Pineapple)(R) Orange grapefruit drink(B) Coconut cubes22023726831132106887911801275683- 837 071199216125383- 175883(R) Hehydratable(E) Bite-size-more-

-29-Still CamerasCAMERASOne 70 mm Hasselblad wide-angle camera using a 38 mmlens and haze filter. Capable of time exposures andspeeds up to l/5OO second using f4.5 to f22.0 aperturesettings, The field of view is 63' X 63O, theresolution Is 125 lines per mm; and the camera can befocused from one foot to infinity. Magnification isapproximately 1.5 times. Used during EVA,Two Maurer 70 mm cameras using 80 mm lens with a fieldof view of 37O X 370 can be focused from one foot toinfinity. Aperture settings are from f2.8 to f22 andthe resolution is 200 lines per mm. Experiment lenssuch as the W lens will be used with these cameras.Sequence CamemTwo 16 mm Maurer Sequence cameras using 18 and 75 mmlenses and 5, 18 and 75 mm lenses are available. The5 mm lens will be used for EYA photography. Fieldsof view of the 5, 18 and 75 mm lenses are 118O X 78O,400 X 30° and 80 X 50 respectively. Time exposuresand single exposures can be taken as well as adjustingthe frame rate at either 1 or 6 frames per second.Resolution is 40 lines per mm and the shutter speedsare 1/50, 1/100, 1/200, and 1/250 seconds. Ninemagazines of Kodak S.O. 207 color film approximately80 feet each in length will be carried during themission.-more -

-30-MANNED SPACE F'LIGIET TRACKING NEXWRKGEMINI 10 MISSION FtEQ-NASA operates the Manned Space Flight !Backing Network by us,% its ownfacilities and those of the Department of Defense for mission informationand control.For Gemini 10, the network will provide flight controllers:(1) Radar tracking, command control, voice and telemetry data areavailable fYom launch through Gemini spacecraf't splashdown in recovery area.Except for voice communications, the network provides the same functions forthe Agena Target Vehicle as 10% as electrical power is available.(2) Verification of the proper operation of the systems onboard theGemini and Agena target.The RTCC at the Manned Spacecraft Center, Houston, will be the primarycomputer center utilized in the control of the entire mission. The RTCCreceives, stores, processes, sends, and drives displays of the necessarymission critical information required by the flight controUers at the MissionControl Center (MCC-Houston)During the launch (powered flight) phase, the RTCC receives launch trajectorydata from the Air Force Eastern Test Range (AFGLII) radars via the Cape KennedyCDC-3600 Real Time Computing Facility (RTCF) and from the Bermuda trackingstation.During all phases of the mission, the RTCC receives trajectory andtelemetry data from the various sites and stores and processes this informtionfor use by flight controllers in the command and control of the mission. Thistelemetered information consists of bio-medical, environmental, electrical,command maneuvering and other spacecraft and target vehicle systems prameters.This information is displayed at the various flight controllers consoles in theMCC where necessary decisions are made for the conduct of the mission. Theflight controllers use the displayed information to assist them in the determinationand generation of required voice and comPaand updates to be sent to thespacecraft and tazget vehicle.TRACKINGThe Gemini 10 mission will require separate tracking of five space vehicles:the Gemini spacecraft, the Gemini 8 and Gemini 10 Agena Target Vehicles (Am),the Gemini Launch Vehicle (GLV-a modified Titan 11), and as required, the AtlasBooster called SLV-3. The Agena Target Vehicle wiU carry one C-bend and oneS-band beacon, while the spacecraft carries two C-band beacons. Skin tracking(radar signal bounce) off the spacecraft, Agena target vehicles, and GeminiLaunch vehicle throughout orbital lifetime is a mission requirement. The MSFNand various facilities of the North American Air Defense CommRnd (NORAD) will beused for this mission. However, NORAD will not track during the rendezvous phase.-more-

-31-For Gemini 10, various combinations of spacecraft tracking assignmentswill be carried out according to individual station capability. Some siteshave radar systems capable of providing space position information on boththe Gemini and one7ena vehicle simultaneously through their Verlort (S-band)and m-16 or m-6 C-band) radars. Most of the data transmission links,however, have only a single system capability; therefore, transmission schedulingpriority will be established by the Flight Director or Flight Dynamics Officeraccording to the mission requirements,During the first revolution of the Agena 10 (prior to Gemini spacecraftliftoff, as a general rule, the C-band radars will track the Gemini spacecraftwhile the S-band radars will track the Agena 10 Target Vehicle, The siteswith dual-tracking capability will track both vehicles simultaneously.!!!racking of the Agena 8 will be done by selected C-band stations just Wiorto the mission and during the mission as assigned by the MCC-H.-more-

-32-XXxxxsX X S* X2cxxx X X x Flight ControlTeam MannedSpacecraft Acqui-XX XX x sition Aid Systemx xxx x Skin Track-more-

-33 -Goddard Space Flight Center Computer SupportNASA's Goddard Space Flight Center, Greenbelt, Md e, real time computingsupport for Gemini 10 includes the processing of real time tracking informationobtained from the spacecraft, target vehicle, and GLV beginning with missionsimulations through Gemini spacecraft recovery and Agena lifetime.Goddard's computer also will certipj the worldwide network's readinessto support Gemini 10 through a system-by-system, station-by-station, computerprogrammedcheckout method called CADF'ISS (Computation and Data Flow IntegratedSubsystem), Checkout of network facilities also will be performed by Goddardduring postlaunch periods when the spacecraft are not electronically "visible"by some stations and continue until the vehicles are again within acquisitionrange.Gemini SpacecraftThe spacecraft has two C-band tracking beacons. The model ACF beacon(spacecraft) will be installed in the reentry module and the DPN-66 modelbeacon in the adapter section.The ACT beacon wiU be prime for launch, insertion, and reentry phase,using the DPN-66 as a backup for these periods.Gemini 10 Agena Target VehicleThe Agena target vehicle will contain one C-band and one S-band beacon.The C-band beacon will be a modified DPN-64The C-band beacon will be primefor Agena Target Vehicle before the Gemini launch. "he Gemini spacecraf'twill be the prime target for C-band tracking following launch.Gemini 8 Agena Target VehicleSince the main batteries and propulsion systems on the Agena 8 weredepleted shortly after terminstion of the Gemini 8 mission, beacon trackingor maneuvering of the Agena 8 Target Vehicle will not be possible. Duringthis inactive period, the NORAD facilities have provided most of the trackinginformation necessary for mission planning purposes. During the mission,skin tracking of the Agena 8 will be accomplished by selected stations.-more-

-34-Acquisition SystemsAll the sites in the network will receive real time acquisition messages(pointing data) f'rom the Real Time Computing Center at NrC, Houston. Thisinformation will be used to position the telemetry and radar antennas at theproper azimuth for acquisition of the RF signals from the spacecraft at thetime they appear over the horizon. Most sites are also equipped with anacquisition aid system which permits llslaVIngl' the radar antennas to thetelemetry antennas or vice versa. Since the telemetry antennas have a mmhbroader beamwidth than the radar antennas, they may acquire the spacecraft RFsignal first, making it possible to point the radar antennas in the generalvicinity of the spacecraft to insure a rapid radar acquisition.Mission Message RequirementsLow speed telemetry data (onslte teletype summaries) from flight controllermanned stations will be sent to the Houston Mission Control Center,Bermuda and Corpus Christi transmit Gemini spacecraft or Agena targetvehicle FCM telemetry via high-speed digital data to Houston Mission ControlCenter in computer format. MCC-K/TEL 111, Grand Ehhama Island, Grand TurkIsland, and Antigua will remote Gemini spacecraft and Agena wide-band data tothe Houston Mission Control Center in the same manner.Spcecraf't Command SystemThe prime ground system in effecting rendezvous is the Digital CommandSystem (DCS) located at key stations throwhout the worldwide network.Command control af the mission from launch through recovery will as always beprovided by the Flight Director at Houston Mission Control Center, Maximumcommand coverage is required throughout the mission.Grand Canary Island; Carnarvon, Australia; Hawaii, and the two ships,USNS Coastal Sentry and USNS Rose Knot; are DCS equipped and manned by flightcontrollers who will initiate all uplink data command transmissions.Following astronaut recovery, further commands will be req='red for theAgena target vehicle. Network Digital Command System support will be continuedthroughout the Agena target vehicle battery lifetime.Cape Kennedy, Grand Bahama, Grand Turk, Antigua and Bermudasites will not be manned by flight controllers. All uplink data commandtransmissions through these sites will be remoted in real time from HoustonControl Center.-more-

-35-In addition to real time commands and onboard clock update commands,the following digital instructions may be sent:a. Gemini spacecraf't b. Agena Target Vehicle1. Preretro with maneuver 1. Maneuver2. Preretro without maneuver 2. Ephemeris3. Orbital navigation 3. Engine burn time4. Maneuver5. Rendezvous6 . Accelerometer error correctionsSpacecraft CommunicationsAll MSFN stations having both HI' and UAF spacecraft communications canbe controlled either by the station or by remote (tone) keying Prom HoustonMission Control Center and from Goddard.The following sites are not scheduled to have a capsule communicator(Cap Corn) and will be remoted to Houston Mission Control Center:Cape Kennedy, Grand Bahama Island; Tananarive, Malagasy Republic;Kano, Migeria; Bermuda; Grand Turk Island; Pt. Arguello, Calif.; AntiguaIsland; Ascension Island; Canton Island; USNS Range Tracker, and the voicerelay aircraft .Spacecraft Systems SupportThe Gemini spacecraft communications systems (antennas, beacons, voicecommunications, telemetry transmitters, recovery light, and digital commandsystem) allow radar tracking of the spa ccraf't, two-way voice communicationsbetween the ground and the spacecraft and from astronaut to astronaut; groundcommand of the spacecraft; TM systems data transmission, and postlanding andrecovery data transmission. The sole link between the ground and the Geminispacecraft is provided by these systems.The Agena target vehicle communications systems (antennas, beacons,telemetry transmitters, and digital command system) allow radar trackingof the vehicle *om both the ground and the Gemini spacecraft. Ground stationand Gemini spacecraft command to the Agena also are accomplished through thissystem .-more-

Agena Target Vehicle OnboardSystems auplprted by NetworkStationsTelemetry (Real Time)Telemetry (Dump)L-Band TransponderS-Band TransponderC-Band TransponderCommand ReceiverGemini Spacecraft OnboardSystems supported by NetworkStationsReentry Module UHF (Voice)Transmit -R e cei veReentry Module HF (Voice)Transmit -ReceiveReentry Module Telemetry(Real Time)Reentry Module Telemetry(rnP)Reentry Module Telemetry(Backup)Adapter Package L-BendRadar (Telemetry Readouts)(Range Safety)Comnmnd ReceiverReentry Madule C-BandTransponder(Command Control)Adapter Package C-BendTrans ponderAdapter Package AcquisitionAid BeaconAdapter Package DigitalCommand SystemReentry Module UHF RecoveryBeaconGround CommunicationsThe NASA Communications Network (NASCOM) used for Gemini 9 w ill be usedfor Gemini 10. Shore stations for USNS Rose Knot and USNS Coastal SentryShip support will be based upon the mission-designated ship positions andpredicted HE' radio propagation conditions.-more-

-37-Network ResponsibilityManned Spacecraft Center (MSC). The direction and mission control of theNetwork immediately preceding and during a mission simulation or an actualmission is responsibility of the MSC.Goddard Space Flight Center. The NASA Office of Tracking and DataAcquisition has centralized the responsibility for the planning, implementation,and technical operations of Goddard Space Flight Center. Technical operationis defined as the operation, maintenance, modification, and augmentation oftracking and data acquisition facilities to function as an instrumentationnetwork in response to mission requirements. About 370 persons directlysupport the network at Goddard; contractor personnel bring the total networklevel to some 1700.Department of Supply, Australia. The Department of Supply, Commonwealth ofAustralia, is responsible for the maintenance and operation of the NASA stationat Carnarvon, Australia. Contractual arrangements and agreements define thiscooperative effortDepartment of Defense (KID). The DOD Is responsible for the maintenanceand operational control of those DOD assets and facilities required to supportProject Gemini. These include network stations at the Eastern Test Range,Western Test Range, White Sands Missile Range, the Air Proving Ground Center,and the tracking and telemetry ships.-more-

-38-ABORT AND RECOVERYCrew SafetyEvery Gemini system affecting crew safety has a backup feature. TheMalfunction Detection System aboard the launch vehicle warns the crew of amalfunction in time for escape.There are three mod.es of escape:WDE IWDE I1Ejection seats, and personal parachutes, used at groundlevel and during first 50 seconds of powered flight, orduring descent after reentry.Retrorockets salvo fired afier engine shutdown is commanded.MODE I11Normal separation from launch vehicle, using OAMS thrusters,then making normal reentry, using computer.Except for Mode I, spacecraft separates from Gemini hunch Vehicle, turnsblunt-end forward, then completes reentry and landing with crew aboard.Survival PackageSurvival gear, mounted on each ejection seat and attached to the astronaut'sparachute harnesses by nylon line, weighs 23 pounds.Each astronaut has:3.5 pounds of drinking waterMacheteOne-man life raft, 54 by 3 feet, with CO2anchor, dye markers, nylon sun bonnet.bottle for Inflation, seaSurvival light (strobe), with flashlight, signal mirror, compass,sewing kit, 14 feet of nylon line, cotton balls and striker, halazone tablets,a whistle, and batteries for power.Surpival radio, with homing beacon and voice transmission and reception.SunglassesDesalter kit, with enough br-bckettes to desalt eight pints of seawater.Medical kit, containing stimulant, pain, motion sickness and antibiotictablets and aspirin, plus injectors for pain and motion sickness.-more-

-39-PLANNED AND CONTINGENCY LANDING AREASThere are two types of landing areas for Gemini 10, planned--whererecovery forces are pre-positioned to recover spacecraf't and crew withina short time-and contingency, requiring special search and rescue techniquesand a longer recovery period.Planned Landina AreasPRLMARYSECONDARYLAUNCH SITELAUNCH ABORTWest Atlantic (44-1) where the USS GuadaLcanallanding platform helicopter ship is pre-positioned.East Atlantic, West Pacific and Mid-Pacific areaswhere destroyers are deployed.Off-the-pad abort or abort during early phase offlight, includes an area about 41 miles seaward fromCape Kennedy, three miles toward Banana River fromComplex 19.Abort during puwered flight, extending f'rom 41 milesat sea f'rom Cape Kennedy to west coast of AA.ica,Contingency Landing AreasAll the areas beneath the spacecraft's ground track except those designatedPlanned Landing Areas are Contingency Landing Areas, requiring aircraft andpararescue support for recovery within a period of 18 hours f'rom splashdown.Recovery forces are provided by the military services under the ope?rationalcontrol of the Department of Defense Manager for Manned Space Flight SupportOperations.-more-

-40-GEMINI SPACECRAFTThe Gemini spacecraft is conical, 18 feet, 5 inches long, 10 feetin diameter at its base and 39 inches in diameter at the top. Its twomajor sections are the reentry module and the adapter section.Reentry ModuleThe reentry module is 11 feet high and 7% feet in diameter at itsbase. It has three main sections: (1) rendezvous and recovery (R&R),(2) reentry control (RCS), and (3) cabin.Rendezvous and recovery section is the forward (small) end of thespacecraft, containing drogue, pilot and main parachutes and radar.Reentry control section is between R&R and cabin sections andcontains fuel and oxidizer tanks, valves, tubing and two rings of eightattitude control thrusters each for control during reentry. A parachuteadapter assembly is included for main parachute attachment.Cabin section between RCS and adapter section, houses the crew,seated side-by-side, their instruments and controls. Above each seat isa hatch. Crew compartment is pressurized titanium hull. Equipment notrequiring pressurized environment is located between pressure hull andouter beryllium shell which is corrugated and shingled to provide aerodynamicand heat protection. Dish-shaped heat shield forms the large endof cabin section.Adapter SectionThe adapter is 7% feet high and 10 feet in diameter at its base,containing retrograde and equipment sections.Retrograde section contains four solid retrograde rockets and partof the radiator for the cooling system.Equipment section contains fuel cells for electrical power, fuelfor the orbit attitude and maneuver system (OAMS), primary oxygen forthe environmental control system (ECS), cryogenic oxygen and hydrogenfor fuel cell system. It also serves as a radiator for the coolingsystem, also contained in the equipment section.NOTE: The equipment section is jettisoned immediately before retrorocketsare fired for reentry. The retrograde section is jettisonedafter retros are fired.-more-

-41-ELECTRICAL FOWER SYSTEMGemini 10 will carry two fie1 cells for the primary power supply duringLaunch and orbit. The cells consist of three stacks of 32 individual cells.Oxygen ._ hydrogen react to produce electrical energy.. .- andFour 45 amphour batteries will also be carried in the sprcecrart toinsure a continuous power supply during reentry and landing. They wlll alsobe used during prelaunch and launch, In conjunction with the fuel cells.Three L5 amp-hour squib batteries WlU be used in the reentry section forall squlb-actuated pryotechnic separating during the mission.Useable --poundsOAMS PROPELtANTA fifth Fopellant tank has been added to the spacecraft to increaseavailable propellant. Also, the auxiliary (Volkswagon) tank will hold 23.6pounds of oxidizer.Purpose -- To measure range, range rate, and bearing angle to Agena socrew can determine maneuvers necessary for rendezvous.Operation -- Transponder on Agena receives radar bprlses and returnsthem to spacecraft at a specific frequency and pulse xidth. Radar acceptsonly signals processed by transponder.Location -0 small end of spacecraft on forward face of rendezvous andrecovery section.-Size -- less than two cubic feetWeight -- less than 70 poundsPower Requirement -- less than 80 watts

Auxiliary Tape Memory (ATM) -- The Auxiliary Tape Memory is a 15-trackmagnetic - tape recorder which stores 835,000 bits on each track resultingin a total storage of 12,500,000 bits. Data parity, clocking, and computerprocessing bits are recorded in triplicate. The ATM provides tripleredundant storage for approximately 1,170,000 bits that can be used forexternal storage of computer programs. The present computer has providedonboard computer program capbility for launch, rendezvous, and reentryand has 156,000 bits of program storage.The ATM is a hermetically-sealed unit which contains a mechanicaltransport assembly mounted on vibration isolators, an an electronic assemblycontaining the power supply, control logic, record logic, and playbacklogic.The tape transport is a flangeless reel, peripheral drive unit whichcontains 525 feet of one-inch wide magnetic tape. The magnetic tape isdriven by an endless, seamless 3f4-inch wide mylar belt called the peripheraldrive belt. The peripheral drive belt is in turn driven by twodrive capstans which are coupled by smaller endless, seamless mylar belts.By not exposing the magnetic tape to drive stresses, its useful life isextended.The unit weighs 26 pounds, contains 700 cubic inches, and usesapproximately 18 watts. The ATM is built by Raymond Engineering Laboratories,Middletown, Conn., under contract to the International BusinessMachines, Electronics Systems Division, Owego, N. Y., for the primeGemini contractor, McDonnell Aircraft Corp.-more-

-43 -GEMINI LAUNCH VEHICLEThe Gemini Launch Vehicle (GLV 10) isa modified U. S. Air ForceTitan I1 intercontinental ballistic missile consisting of two stages,identical to the launch vehicles used in previous Gemini flights.FIRST STAGESECOND STAGEHEIGHT 63 feet 27 feetDIAMETER 10 feet 10 feetTHRUST 430,000 pounds 100,000 pounds(two engines)(one engine)FUELOX I D I ZE R50-50 blend of monomethyl hydrazine andunsymmetrical-dimethyl hydrazineNitrogen tetroxide.propellants are hypergolic, ignitespontaneously upon contact with oxidizer).Overall height of launch vehicle and spacecraft is 109 feet.weight is about 340,000 pounds.CombinedModifications to Titan I1 for use as the Gemini Launch Vehicle include:(NOTE: GLV-10 same as GLV 1 through 9)1. Malfunction detection system added to detect and transmit boosterperformance information to the crew.2. Back-up flight control system added to provide a secondarysystem if primary system fails.3. Radio guidance substituted for inertial guidance.4. Retro and vernier rockets deleted.5. New second stage equipment truss added.6. New second stage forward oxidizer skirt assembly added.7. Trajectory tracking requirements simplified.8. Electrical hydraulic and instrument systems modified.Gemini Launch Vehicle program management for NASA is under ttedirection of the Space Systems Division of the Air Force System Ccrr,ms.rld.-more-

-44-AGENA TARGET VEHICJ~EThe Agena target vehicle for Gemini 10 is a modification of the U. S.Air Force Agena D upper stage, similar to the space vehicles which helpedpropel Ranger and Mariner spacecraft to the Moon and planets.It acts as a separate stage of the AtlasIAgena launch vehicle,placing itself into orbit with its main propulsion, and can be maneuveredeither by ground control or the Gemini 10 crew, using two propulsionsystems.Height (Liftoff) 36.3 feet Including shroudLength (Orbit) 26 feet Minus shroud and -JdapterDiameter5 feetWeight 7,000 pounds In orbit, FueledThrust16,000 pounds Primary Propulsion System (PPS)400 pounds Secondary Propulsion System (SPS)Unit I132 pounds Secondary Propulsion System (SPS)Unit IFuelUDMH(Unsymmetrical Dimethyl Hydrazine)Ox id i L e rIRFNA (inhibited Ked Fuming Nitric Acid) inprimary propulsion system; MON (Mixed Oxides ofNitrogen) in secondary propulsion system.Combust ion IRFNA and UDMH are hypergolic, ignite on contactPrimary and secondary propulsion systems are restartable. Main engineplaces Agena into orbit and is used for large orbit changes. Secondarysystem, two 200-pound-thrustY af t-f iring engines, are for small velocitychanges. Two 16-pound-thrust, aft-firing thrusters are for ullage orientationand vernier adjustments. Attitude control (roll, pitch, yaw) isaccomplished by six nitrogen jets mounted on Agena aft end.Modifications to Agena for use as Gemini rendezvous target vehicle include:1. Dockingadapter and equipment to permit mechanical connection withGemini during fl ight.2. Radar transponder compatible with Gemini radar.3. Displays and instrumentation, plus aapisicn lights for visuallylocating and inspecting Agena before docking.4. Secondary propulsion system for small orbital changes.5. Auxiliary equipment rack for special rendezvous equipment andtelemetry.6. Command control equipment to allow control by Gemini 10 crew orground controllers.-more-

-45-7. Multi-restart engines to provide in-orbit maneuver capabilityAgena program management for NASA is under the direction of the SpaceSystems Division of the Air Force Systems Command.STATIC CHARGE DEVICEThree protruding flexible copper fingers are installed on the Agenadocking cone to make first contact with the spacecraft. Any charge willbe carried to a ground in the Agena and dissipated at a controlled rate.An electrostatic charge monitoring device is also installed in the targetdocking adapter to measure the potential or difference in charge betweenthe two vehicles.-more-

-46-ATLAS LAUNCH VEHICLEThe Atlas Standard Launch Vehicle is a refinement of the modifiedU. S. Air Force Atlas intercontinental ballistic missile, similar to thelaunch vehicle which placed Project Mercury astronauts into orbit.Atlas is a 1% stage vehicle, igniting all three main engines on thepad, then dropping off the two outboard booster engines at staging, allowingthe single sustainer engine to continue thrusting at altitude, aided bytwo small vernier engines.HeightDiameterWeightThrust77 Feet16 Feet10 Feet5 Feet, 10 inches260,000 pounds390,000 pounds57 , 000 poundsBalanceMinus Agena PayloadLower Booster SectionTank SectionsTapered Upper EndFully fueled, minus Agenapay loadTotal at liftoffTwo booster (outer) engineOne Sustainer (center) engineTwo small vernier engines fortrajectory and final velocitycontrolFuelRP-1, a hydrocarbon resembling keroseneOx id iz er Liquid oxygen at-297 degrees F.Combu s t ionUnlike Titan's hypergolic, spontaneous ignition,Atlas combustion is achieved by forcing propellantsto chambers under pressure, burning them in hasgenerators which drive propellant pump turbines.Modifications to the Atlas Standard Launch Vehicle for the Gemini 10mission include:1. Special autopilot system for rendezvous mission.2. Improved propellant utilization system to assure simultaneousdepletion of both fuel oxidizers.3. Increased thickness of Atlas structure for support of AgenaUpper stage.4. Simplified pneumatic system.5. Retrorockets moved from exterior equipment pods to upper interstageadapter section.6. Uprated MA-5 propulsion system (used on later Mercury flights).7. Modular telemetry kit tailored for each mission.Atlas Standard Launch Vehicle program management for NASA in underthe direction of the Space Systems Division of the Air Force SystemsCommand.-more-

-I+*[ -- CRFW BIOGRAPHIESNAME: John Watts YoungBIR!l!iiPLACE AND DATE:EDUCATION:MARITAL STATUS:San FLpancisco, Calif., Sept. 24, 1930.Bachelor of Science degree in aeronautical engineering fromGeorgia Institute of Technology, 1952.Married to the former Barbara V. White of Savannah, Ga,CHILDREN: Sandy, Apr. 30, 1957; John, Jan. 17, 1959.PROFESSIONAL SOCIETIES: Member, American Institute of Aeronautics andAstronautics; associate member, Society ofFxperlmental Test Pilots .EXPERIENCE: Upon graduation from Georgia Tech, Young entered the UnitedStates Navy and is now Commander in that service.*om 1959 to 1962 he served as a test pilot, and later programmanager of the F4H weapons system project, doing test andevaluation flights and writing technical reports.He served as maintenance officer for all-weather FighterSquadron 143 at the Naval Air Station, Miramar, Calif.In 1962, Young set world time-to-climb records in the 3,000meter and 25,000 meter altitudes in the F4B navy fighter.He was the pilot for the first manned Gemini flight in March1965 and backup pilot for Gemini 6.He has logged more than 3,400 hours flying time, includingmore than 2,900 hours in jet aircraft.CURREMT ASSIGI"T: Young was among the group of nine astronauts selectedby NASA in September 1962. In addition to participation in the overallastronaut training program he has had specialized duties including monitoringdevelopment of the environmental control system, pressure suits, survivaland associated pilot equipment, such as spacecraft ejection seats and couches.-more-

-4a-NAME:Michael CollinsBIRTHPLACE AND DATE: Rome, Italy, Oct. 31, 1930EDUCATION:Bachelor of Science degree from the United States MilitaryAcademy, West Point, New York.MARITAL STATUS: Married to the former Patricia M. Finnegan of Boston,Mass.CHILDREN: Kathleen, May 6, 1959; Ann S., Oct. 31, 1961; Michael L.,Feb. 23, 1963.PROFESSIONAL ORGANIZATIONS:Member, Society of Experimental Test Pilots.EXPERIENCE:Collins, an Air Force Major, chose an Air Force careerfollowing graduation from West Point.He served as an experimental flight test officer at theAir Force Flight Test Center, Edwards AFB, Calif. In thatcapacity he tested performance and stability and control characteristicsof Air Force aircraft, primarily jet fighters.He has logged more than 3,500 hours flying time, includingmore than 3,000 hours in jet aircraft.CURRENT ASSIGNMENT: Collins was one of the third group of astronautsselected by NASA in October 1963. In addition to participating in theastronaut training program, he concentrates on pressure suits. He wasalso named as pilot of the backup crew on Gemini 7.-more-

-49-NAME: Alan Lavern BeanBIRTHPLACE AND DATE: Wheeler, Tex., Mar. 15, 1932.EDUCATION: Bachelor of Science degree in Aeronautical Engineering,University of Texas.MARITAL STATUS: Married to the former Sue Ragsdale of Dallas, Tex.CHILDREN: Clay A,, Dec. 18, 1955; Amy Sue, Jan. 21, 1963.EXPERIENCE: Bean, a Navy ROTC student at Texas, was commissioned upongraduation and received his flight training. He is now aNaval Lieutenant Commander.He attended the School of Aviation Safety at the Universityof Southern California.Bean was assigned to Attack Squadron 44, Jacksonville, Fla.,Naval Air Station for four years. He then attended the NavyTest Pilot School at Patuxent River, Md.He served at Patuxent as project officer on various aircraftfor Navy preliminary evaluation, initial trials and finalboard of inspection and survey trials.Bean was later assigned with Attack Squadron 172 at CecilField, Fla., as a A-4 light jet attack pilot.He has logged more than 2,600 hours flying time, includingmore than 2,200 hours in jet aircraft. Bean has flown 24aircraft, including jet propelled, and helicopter models.CURRENT ASSIGNMENT: Bean was chosen as an astronaut in the group namedby NASA in October 1963. In addition to participating in the astronauttraining program. he has specific responsibility in the recovery systemsareas.-more-

-50-NAME: Clifton C urtis Williams, Jr.BIRTHPLACE AlpD IlATE: Mobile, Ala,, Sept. 26, 1932.EDUCATION:Bachelor of Science degree in mechanical engineering FromAuburn University.MITAL S!l!A!RB: Married to the former Jane E. Laslsche of Mew Bern, N. C.PROFESSIOIQAL ORGANIZATIONS: Member of Sigma chi; Pi Tau Sigma, nationalmechanical honorary; Tau Beta Pi, nationalengineering society; and associate member ofthe Society of Ekperimental Test Pilots.FXPEEIIENCE: Williams, a Major in the United States Marine Corps, is agraduate of the Navy Test Pilot School at Fatuxent River, Md.,and attended the Marine Corps School at Quantico, Va.He served three years as a test pilot in the CarrierSuitability Branch of the Flight Test Division at PatwentRiver. This work included Land based and shipboard tests ofthe F8E, TF&, F8E (attack), A4E and automatic carrier landingsystem.Williams has logged more than 2,400 hours Plying time,including more than 1,900 hours in jet aircraft,CURRENT ASSIGNMENT: Williams was one of the third group of astronauts chosenby NASA in October 1963. In addition to participation in the overall astronauttraining pro~am, he has specific responsibilities in the fields of rangeoperations and crew safety and monitoringbooster tanks performed on theGemini 9 flight from the Mission Control Center.-more-

-51-Gemini 1, A ~K. 8, 1964PREVIOUS GEMINI FLIGHTSUnmanned orbital flight, using first production spacecraft, totest Gemini launch vehicle performance and ability of launch vehicleand spacecraft to withstand launch environment. Spacecraft and secondstage launch vehicle orbited for about four days. No recovery attempted.Gemini 2, Jan. 19, 1965Unmanned ballistic flight to qualify spacecraft reentry heat protectionand spacecraft systems. Delayed three times by adverse weather,including hurricanes Cleo and Dora. December launch attempt terminatedafter malfunction detection system shut engines down because of hydrauliccomponent failure. Spacecraft recovered after ballistic reentry overAtlantic Ocean.Gemini 3, Mar. 23, 1965First manned flight, with Astronauts Virgil I. Grissom and John W.Young as crew. Orbited Earth three times in four hours, 53 minutes.Landed about 50 miles short of planned landing area in Atlantic becausespacecraft did not provide expected lift during reentry. First mannedspacecraft to maneuver out of plane, alter its own orbit. Grissom, whomade suborbital Mercury flight, is first man to fly into space twice.Gemini 4, June 3-7, 1965Second manned Gemini flight completed 62 revolutions and landed inprimary Atlantic recovery area after9 hours, 56 minutes of flight.Astronaut James A. McDivitt was command pilot. Astronaut Edward H. White I1was pilot, accomplished 21 minutes of Extravehicular Activity (EVA) usinga hand-held maneuvering unit for first time in space. Near-rendezvouswith GLV second stage was not accomplished after use of pre-planned amountof fuel for the maneuver. Malfunction in Inertial Guidance Systemrequired crew to perform zero-lif t reentry.Gemini 5, Aug. 21-29, 1965Astronauts L. Gordon Cooper and Charles (Pete) Conrad, Jr., circledthe Earth 120 times in seven days, 22 hours and 56 minutes. Cooper wasfirst to make two orbital space flights. Failure of oxygen heatingsystem in fuel cell supply system threatened mission during first day offlight, but careful use of electrical power, and excellent operationalmanagement of fuel cells by both crew and ground personnel, permittedcrew to complete flight successfully. Spacecraft landed about 100 milesfrom primary Atlantic recovery vessel because of erroneous base-lineinformation programmed into onboard computer, although computer itselfperformed as planned. Plan to rendezvous with a transponder-bearing pod 'carried aloft by Gemini 5 was cancelled because of problem with fuel celloxygen supply.-more-

-52-Gemini 7, Dec. 4-18, l$$Holds current world rccord for mnne3. space flight as Command FilotFrank Fbrman and Pilot James Love11 completed 206 revolutions of the earthin 13 days, 18 hours, wid 35 minutes. Cn the 12th day of their flicht,Gemini 7 served as target for the Gemini 6 spacecraft on the first successfulrendezvous in space, In proving mn's ability to operate in spce for aperiod up to two weeks, the crew of Gemini 7 carried out m fimbitious list of20 experiments including all medical experiments in the G+-.rnini I?agram, a testof laser communications from space and visual acuity. The Gemini 7 experiencedcontinuous difficulty with the delta p light on the fuel cell system. HDwcver,the system performed for the entire mission. The only other problem encounteredwas the temporary malfunction of a yaw thruster on the spacecraft.Gemini 7 landed in the i&Lantic on Dec. 18, making a controlled reentry whichbrought it within 10 miles of the recovery carrier.Gemini 6. Dee. 15-16, 1965The first spacecraft to rendezvous with another spacecraft in orbit.Command Pilot Walter Schirra and Pilot Thorns Stafford flew their spacecraftfrom a 100-by-167 mile orbit into a 185-mik circular orbit, rendezvousingwith Gemini 7 over the Pacific Ocean at 5 hours, 47 minutes af'ter liftoff.It demonstrated one of the major objectives of the program, and also pavedthe way for Apollo Lunar Orbit Rendezvous in the accomplishment of the firstmanned landing on the Moon.Gemini 6 was launched on its historic rendezvous mission on the thirdattempt. On the first try, Oct. 25, the Agena Target Vehicle was destroyedby a hard start of its primary propulsion system. On Dec. 12, the GeminiLaunch Vehicle failed to liftoff when an electrical plug connecting therocket with the pad electrical system dropped out prematurely.Gemini 8, March 16, 1966Astronaut Neil Armstrong, Command Pilot, and David Scott, Pilot, completedthe first rendezvous and docking with an Agena spacecraft launched into orbitapproximately 100 minutes earlier. The planned three-day flight was terminatednear the end of theseam revolution after an electrical short circuit in tbeGemini spacecraft caused continuous firing of a roll thruster. The crewundocked from the Agena and activated the reentry reaction control system toregain control of the spacecrart. The crew made a guided reentry and landedin the Pacific Ocean 500 miles east of the island of Okinawa, and only approximatelyfive miles from the aiming point. C, recovery aircraft was on thescene before splashdown to parachute a recovery team to the spacecraft. Thecrew and spacecraft were picked up by a Navy destroyer approximately threehours after splashdown .-more-

-53-Gemini 9, June 3-6, 1$6Three separate rendezvous with the fiuqented Target Docking Adapter and atwo-hour and 10-minute extravehicular activity were the primary accomplishmentsof the seventh manned Gemini flight. Col. Thomas P. Stafford, a veteran of thefirst US rendezvous mission in Gemini 6, was command pilot for the three-dayflight. Eugene Cernan was pilot and performed the EVA. The flight, originallyscheduled for Majj 17, was postponed two weeks when the Atlas booster which waslaunching the Rgena Target Vehicle developed an electrical short circuit whichcaused its engines to gimbal hard over and abort the flight. The ATDA wassubstituted for the Agena and was launched on June 1. Gemini 9 did not launchon June lwhen a malfunction in the computer transmitting data to the spacecraficaused an automatic hold at T-3 minutes. Gemini 9 was launched two days later,and although the shroud had failed to separate from the ATDA which preventedany docking exercises, an initial third orbit rendezvous was achieved, followedby an equi-period rendezvous, and a lunar abort or rendezvous from above onthe following day. The ?3VA was postponed one day because of crew fatigue.Cernan spent more than one orbit outside the spacecraft before visor foggingin his helmet forced termination of the EVA before the Astronaut ManeuveringUnit experiment could be performed. Gemini 9 made the most accurate landingto date in the program, splashing down approximately three and one half milesf’rom the recovery carrier in the West Atlantic after 4-4 revolutions of theEarth .I-more-

-54-U.S. MANNED SPACE FLIGHTSMANNED HOURSMISSION SPACECRAFT HRS. REVS. IN MISSIONHRS, MIN,II4I 41 9341-5155556131922372305ll49TOTAL MANNED HRS.CUMULATIVE94600195522238152026611026Gemini 6 (Schirra8 Stafford) I 25 51 24 15IGemini 8 (Armstrdng& Scott I 10 42 06 6.6IGemini 9 (Staffo;d& Cernan) I 72 20 56 445121144422441483252-more-

-55-PROJECT OFFICIALSDr. George E. MuellerJohn A. EdwardsWilliam C. SchneiderDr. Robert R. GilruthAssociate Administrator, Officeof Manned Space Flight, NASAHeadquarters; Acting Director,Gemini ProgramActing Deputy Mrector, GeminiProgram, Office of Manned SpaceFlight, NASA HeadquartersGemini 10 Mission Director, DeputyDirector, Mission Operations,Office of Manned Space Flight,MASA HeadquartersDirector, NASA Menned SpacecraftCenter, Houston, TexasCharles W.MathewsGemini Program Manager, MannedSpacecraft Center, HoustonChristopher C. KraftAssistant Director for FlightOperations, WMed SpacecraftCenter, HoustonDr. Kurt H.DebusDirector, John F. Kennedy SpaceCenter, MASA, Kennedy Space Center,FloridaG. Merritt PrestonLt. Gene Leighton I. DavisMaJ. Gen. V. G. HustonCol. Robert €?. HullCol. Otto C. Ledford-more-Deputy Mission Director for LaunchOperations, John F. Kennedy SpaceCenter, NASA, Kennedy Space Center,FloridaUSAF, National Range Division,Command and DOD Manager of MannedSpace Flight Support OperationsUSliF, Deputy DOD Manager of MannedSpace Flight Support Operations;Commander of Air Force Eastern TestRangeUSAF, Director, Directorate, GeminiLaunch Vehicles, Space SystemsDivision, Air Force Systems CommandUSAF, Commander 6555th Aerospace 'Test Wing, Space Systems Division atAir Force Eastern Test Range

-56-Col. John G. AlbertLt. c01. L. E. Allen, Jr.R. Adm. William C. AbhauR. Adm. William P. MackR. Adm. Henry S. PersonsUSAF, Chief, Gemini Launch Division,6555th Aerospace Test Wing, SpaceSystems Division at Air Force EasternTest RangeUSAF, Chief, Atlas Division, 6555thAerospace Test Wing, Space SystemsDivision at Air Force Eastern TestRangeUSN, Commander Task Force 140Primary Recovery AreaUSN, Commander Task Force 140.3Onboard prime recovery carrierUSN, Commander Task Force 130Pacific Recovery Area-more-

-57-AIResearch ?4anufacturing Co.;Loa Angelea, Calif.IB4 Federal Syetem DIvi61onElectronic System CenterOwego, N. Y .Wneral Electric CO.West Lynn, MassThe Eagle Pitcher Co.Joplin, Mo.Northrop Corp.Newbury Park, Calif.Rocketdyne MvlSiOn,Ikth American Aviation, InC.Canoga Park, Calif.Thiokol Chemical Corp.ELMon, Md.Weber Aircraft Corp.Burbmk, calif.Westiqghouse Electric Corp.Baltimore, Md.Ehvironmentsl Control SystemOnboard ComputerFuel CellsBatteriesWachut esOAMS, RCSRetrorocket SystemEjection SeatsRendezvous Radar SystemAtlas contractors include:Rocketdyne Div., North AmericanAviation, Inc., Canoga Pask, Calif .General Electric Co.Syracuse, N. Y.Airframe and SystemsIntegrationPropulsion SyatemsGuidance-more-

-58-Titan I1 contractors include:Martin CO., Baltimore Div.,Baltimore, Md .Aerojet-General Corp.Sacramento, Calif.General Electrlc Co.Syracuse, N. Y.Burroughs Corp.Paoli, Pa.Aerospace Corp,El Segundo, Calif.Airf’rame and SystemIntegrationPropulsion SystemRadio Command GuidanceSystemGround Guidance ComputerSystems Engineering andTechnical DirectionAgena D contractors include:Lockheed Missiles andSpace Co,Sunnyvale, Calif ,Bell Aerosystems Co.Niagara Falls, N. Y.McDonnell Aircraft Corp.St, Louis, Mo.Airframe and SystemsIntegrationPropulsion SystemsTarget Docking AdapterFood contractors:u. s. Army LaboratoriesMatick, Mass.Whirlpool Corp.St . Joseph, Mich .Swift and Coo, ChicagoPillsbury Co . , MinneapolisFood Fornulation ConceptProcurement, Processing,PackagingPrincipal Food ContractorsSult contractor:The David R. Clark Co.Worcester, Mass-more-

-59-ABBREVIATIONS AND SYMBOLS FREQUENTLY USEDAMUASCOCGLVTCECSETREVAELS SFLTGAATVGATVG ENGLVGN2GTIMUI RFNALc (14)LD (14)Astronaut Maneuvering UnitAuxiliary Sustainer Cut OffChief Gemini Launch Vehicle Test,~nductorEnvironmental Control SystemEastern Test RangeExtravehicular ActivityExtravehicular Life Support SystcinFlight Director (Houston)Gemini Atlas Agena target vehicleGemini Agena target vehicleGeneral informationGemini launch vehicleGaseous NitrogenGemini TitanInertial measuring unitInhibited Red Fuming Nitric AcidLaunch Conductor - Complex 14Launch Director - Complex 14LDLIMD(l.9)Launch Director - Complex 19Launch Mission Director-more-

-60-LN2LO2LTCMCCMDOAMSPCMs /cSPCFTS LDSLVS TCS ROTDAUDMHLiquid NitrogenLiquid OxygenLockheed Test ConductorMission Control Center (Defined withthe word Houston or Cape)Mission Director (Houston)Orbit Attitude Maneuvering SystemPulse Code Modulation(Gemini) spacecraftChief Spacecraft test conductorS imultaneous Launch DemonstrationStandard (Atlas) launch vehicleSLV test conductorSuperintendent of range operationsTarget docking adapterUnsymmetrical Dimethlhydrazine-more-

-61-Approximate Times of Major EventsIn Nominal Gemini 10 MissionGETHoursEvent- GETHours00 - Launch 13 -Event02 -Synoptic terrain photos (S-5) ---16 -05 - Rendezvous with Agena 10 18 --17 -End sleep periodFirst dock, bending mode check 19 - Dual rendezvous plate change- Undock- Ion wake experiment (S-26)20 -Dock- Undock-Ion wake Experiment (S-26)Dual rendezvous height ad just. (pps)_ Dock08 Eat period 21 --Dual rendezvous height adjust.Dual rend. height adjust. (PPS) -End eat period09 Begin sleep period- -Ion wake experiment-10 -- --22 - Undock, dual rendezvous co-elliptical11 - 24 -End stand-up EVA- -Begin eat period12 - 25 --23 -Begin stand-up EVA (S-13)-.. Color patch photography- Synoptic weather (S-6) and terrain photos- End eat period- Landmark contrast experiment.(MSC-12)Synoptic terrain photo (S05) as possible

- GETHours26 -32 -Event- GETEventHours39 End sleep period, begin eat periodStar occultation nav (D-5) -Synoptic weather photo (S-6) 40 - End eat periodLandmark contrast (i.ISC- 12)Dual rendezvous height adjust.--41 - Dual rend. catch-up adjustStar occultation nav (D-5)Landmark contrast (MSC-12)Synoptic weather Star occultation nav (D-5)(S 6)-Synoptic weather (S-6) 42 -Star occultation nav (D-5) -Begin eat period 43 -Synoptic weather (S-6) -End eat periodBegin sleep period44 ---45 -Begin eat period-46 -End eat period-48 -i)u&rendezvousUmbilical EVAEvaluate extravehicular life supportsystem, hand-held maneuvering unit,retrieve S-12, S-10 experimentsEnd umbilical EVAOpen hatch, jettison equipment51 -- Begin eat period

-63--GETHoursEvent52 End eat period- Zodiacal light photo (S-1)53 Ion sensing attitude cont (D-10)--54 -Begin sleep period---55 -GETHours65 ---66 -Event-67 - Begin eat period--End eat period68 --63 -End eat period-Ion sensing attitude cont. (D-10)-more-

NOTE:Clip the time scalesat left and slidethem along the scalesshowing the approximateground elapsedtime of a nominalmission. Place thelocal time of liftoffopposite the 00 onthe GET scale and youwill be able to readoff the approximatelocal times of majorevents .10L-end-