NASA UAP D018 Gemini 4 Experiment Debriefing 1967

NATIONAL AERONAUTICS ADMINISTRATlo-1 AND SPACE ROUTING SLIP MAIL CODE NAME Action Approval Call Me Concurrence file Information Investigate and Advise ____ .l ,Nmote and Forward Note and R_e_hl_rn___ _ __jL ,P;;,,-;R;:e::q::-u•=s�I::::.::_ • _ ___ _ Per Teleph one Conversation I R..e,.c,ommendation _ _ _ _J__: See·Me Signature Circulate and De I s roy (fL J 1 'I, h'.C.9-- � TEL. NO (· or ,ode) & EXT. NASA FORM 26 APR 69 PREVIOUS EDITIONS MAY BE USED • Mission Operation Report No. M-913-65-04 MEMORANDUM June 1, 1965 To A/Administrator From M/Associate Administrator for Manned Space Flight Subject: Gemini Flight Number Four (GT-4) Additional Flight Activities Subsequent to the preparation of the GT-4 Mission Operation Report several new procedures and items of equipment have progressed to a stage of flight readiness. Consequently, three significant additional flight activities are now possible and have been included in the mission. These activities are: extra vehicular activities (EVA); extra vehicular propulsion; and demonstration of rendezvous with the booster second stage. Additional details of these flight plan activities are provided in the attached supplement to the basic report. Enclosure: MOR No. 913-65-04 Change 1 FOR INTERNAL USE ONLY ADDITIONAL the booster second stage. Additional details of these flight plan activities are provided in the attached supplement to the basic report. Enclosure: MOR No. 913-65-04 Change 1 FOR INTERNAL USE ONLY ADDITIONAL GT-4 FLIGHT PLAN ACTIVITIES M-913-65-04 Three additional special engineering and operational objectives are now planned for the first four orbits of the GT-4 Mission: 1. Demonstration of extravehicular activities (EVA) using a 25 foot umbilical. flight repair, and inspection of orbiting objects. Potential future application includes crew transfer, in­ 2. Demonstration of extravehicular maneuvering using a simple, one­ This device could be used with or without man propulsion unit. a spacecraft tether on future missions. 3. Demonstration of rendezvous with the booster second stage. This activity wil I provide valuable early information and maneuvering procedures necessary to rendezvous with a target vehicle. lights identical to those designed for the Gemini/Agena Vehicle have been insta I led on the booster second stage for th is test. Flashing The first orbit will be occupied with operational checks of the The The Flight Plan sequence involves post-launch separation from the launch vehicle, then maneuvering to stop the spacecraft separation velocity. The first two orbits wil I be flown with the spacecraft at distances less than one quarter of a mile from the launch vehicle. Nighttime separation from the launch vehicle, then maneuvering to stop the spacecraft separation velocity. The first two orbits wil I be flown with the spacecraft at distances less than one quarter of a mile from the launch vehicle. Nighttime separation will be sufficient to prevent the flashing lights from disturbing the pilot's visual dark adaptation. spacecraft guidance, maneuvering, and environmental control systems. pilots will utilize the second orbit to prepare for the extravehicular activity. This procedure involves unstowing and assembling a 25-foot umbilical, the emergency oxygen pack, a maneuvering unit, and the cameras. Over Hawaii, at daybreak, near the end of the second orbit, the cabin will be depressurized and Jim McDivitt will maneuver to within close proximity of the booster. At this point, the right hatch will be opened and Ed White will climb out and hold on the right forward portion of the spacecraft unti I McDivitt gives him a release command. Upon command, White wi II push off slowly and reorient himself with the hand-held maneuvering unit to face the booster. A 35-mm still camera (Zeiss-Contarex) mounted on the maneuvering unit will be used to photo­ graph the booster and spacecraft with various earth/sky backgrounds. After testing his ability to maneuver in a zero gravity environment, White will maneuver back toward the spacecraft and ingress. ing unit will be used to photo­ graph the booster and spacecraft with various earth/sky backgrounds. After testing his ability to maneuver in a zero gravity environment, White will maneuver back toward the spacecraft and ingress. from the spacecraft will be approximately 10 minutes. He will be inside with the cabin repressurized by the time the spacecraft posses over Ascension Island on the start of the third orbit. The total time separated Shortly ofter passing Ascension, McDivitt wil I maneuver ahead of the booster with 5 feet per second separation velocity. spacecraft in a higher altitude and longer period orbit than the booster, it will rise above and fall behind the booster. One orbit later, the spacecraft Because this maneuver places the 6/1/65 Page 1 M-913-65-04 will trail 16 miles behind the booster. At this point, a spacecraft retardation maneuver of 13 feet per second will initiate the visual rendezvous sequence. The spacecraft will approach the booster from behind and below. Because of unknown variation in the atmospheric density and drag of the slowly tumbling booster, the exact approach trajectory cannot be predicted. The flight crew will measure elevation angles of the booster and wil I initiate rendezvous maneuvers when the booster is approximately 45 degrees elevation angle a bove the spacecraft. By observing the movement of the booster with respect to flight crew will measure elevation angles of the booster and wil I initiate rendezvous maneuvers when the booster is approximately 45 degrees elevation angle a bove the spacecraft. By observing the movement of the booster with respect to the star background and with respect to the spacecraft inertia l platform display , the crew can determine the proper lateral maneuver to null the lateral component of velocity thereby resulting in a spacecraft velocity vector which is directly toward the booster. After removing the lateral velocity difference, the pilot will apply a series of breaking maneuvers with the forward firing thrusters to reduce the closing velocity. The flight crew will measure with onboard instruments the total maneuvering velocity required for the rendezvous procedure. The spacecraft should be back in close proximity of the launch vehicle over the Northeast coast of South America at the beginning of the fifth orbit. After the rendezvous operation is complete, the spacecraft will again separate from the booster - spacecraft on an orbit with a predicted lifetime of four days. this time using a maneuver which will place the Gemini The EVA suit is the new G4C suit which replaces the G3C suit used so successfully by the GT-3 flight crew. The G4C suit has the following new features: a. Helmet - incorporation of triple lens shield (visors) for visual, thermal, impact, and micrometeorite protection. b. by the GT-3 flight crew. The G4C suit has the following new features: a. Helmet - incorporation of triple lens shield (visors) for visual, thermal, impact, and micrometeorite protection. b. Torso - 1. Change to Nomex (HT-1) 11 Linknet11 in restraint layer for increased 2. 3. structure I strength. Incorporation of strain relief zipper in sealing closure. Incorporation of redesigned ventilation inlet and outlet fittings with automatic locking and redundant sealing features. 4. Replace Nomex (HT-1) coverlayer with integrated thermal and mi crometeori ty cover layer. c. Gloves - Incorporate new design with increased mobility, abrasion resistance and thermal protection. d. Bio-connector - Self-alighment, pin protective design. 6/1/65 Page 2 M-913-65-04 FIG. Figure 1 depicts the principal physical differences between the old G3C suit and the new EVA G4C suit. Figure 2 shows that with one visor down on the new G4C helmet, there is practi ca I ly no attenutation of Ii ght entering, whereas Figure 3 shows that with two of the visors down there is a noticeable difference in the amount of light that enters the astronaut's eyes. With the third visor down, there would be a similar decrease in the amount of I ight al lowed to enter down there is a noticeable difference in the amount of light that enters the astronaut's eyes. With the third visor down, there would be a similar decrease in the amount of I ight al lowed to enter the helmet. It should The multivarious layers of materials used in the EVA G4C suits are delineated in Figure 4. be noted that the old G3C suit consisted only of the pressure and restraint layers of Figure 4 with the HT -1 nylon outer protective layer. The EVA spacesuit has received the following qualifi­ cation tests: G-4C OVER VISOR SPACE HELMET 6/1/65 Page 3 • M-913-65-04 G-4C OVERVISOR SPACE HELMET FIG. 3 G-4C EXTRAVEHICULAR SUIT THERMAL AND MICROMETEOROID LAYERS PRESSURE AND RESTRAINT LAYERS HH NYLON OUITR ~6~~ T~~~~~} ~~~;:) USE: WEAR AND SOLAR REFLECTANCE COTTON CONSTANT "[AR ~Ng~~;:r~~m OXFORD NYLOt-i COf.JORT LAY.R 11 oz,vo 2 swu ____ PRCSSURE LAYER NEOPRE~E COATEO NYLON 11-1·2ozvo21 r - - - -- RESTRAINT lAVlR UM( NH DACRON Al.;Q HflO~ u-J 4 oz vo 21 FIG. 4 7 LAYERS ALUMIN IZEO MYLAR SEPARATED BY 7 LAYCAS UNWO ·2ozvo21 r - - - -- RESTRAINT lAVlR UM( NH DACRON Al.;Q HflO~ u-J 4 oz vo 21 FIG. 4 7 LAYERS ALUMIN IZEO MYLAR SEPARATED BY 7 LAYCAS UNWOVEN DACRON SPACERS HH NYLON INNER MICROr,,'tn OROID STOPPER LAYERS !EACH 6. 8 OZ/YD2 WH IT[ I US E: WEAR ANO MICR0~,1£TEO ROI D PRO TE CT ION 6/1/65 Page 4 M-913-65-04 a. Leakage b. Proof pressure c. 02 compatibility d. Ejection envelope e. Cold temperature f. Rapid decompression g. Life cycling h. Visor testing Should the 25-foot long tether fail in some manner, the pilot will be carrying a chestpack that has been compatibility qualified with the G4C suit and con­ sists principally of an emergency oxygen bottle with automatic valving. It should be emphasized that both the primary and backup flight crews have undergone 40 minutes cabin depressurization with the hatches open at a simulated altitude of 150,000 feet in the chambers at McDonnell, St. Louis during which time they practiced opening and closing the hatches, taking pictures, and other actions that will take place during EVA. The extravehicular maneuvering will be accomplished using a zero g Integral Propulsion (ZIP) Unit as shown in Figure 5. This device is handheld taking pictures, and other actions that will take place during EVA. The extravehicular maneuvering will be accomplished using a zero g Integral Propulsion (ZIP) Unit as shown in Figure 5. This device is handheld and accomplishes propulsion by jetting oxygen out through a single forward firing It nozzle and two aft firing nozzles as selected and aimed by the operator. includes a camera mounted for convenient extravehicular photography. FIG. 5 6/1/65 Page 5 Mission Operation Report No. M-913-65-04 MEMORANDUM May 24, 1965 To A/Administrator From M/Associate Administrator for Manned Space Flight Subject: Gemini Flight Number Four (GT-4) GT-4, the fourth in a series of twelve planned Gemini flights is scheduled to be launched from Complex 19 at the John F. Kennedy Space Center on or after 3 June 1965. This wi 11 be the second manned Gemini mission and the longest ever attempted by a two-man crew. The purpose of the mission is to further demonstrate manned space flight for a period of four days. The nominal launch time is 10 a.m. EDT (1400 GMT). The space vehicle is to be launched on an azimuth of 72 degrees and the spacecraft wi 11 be inserted into an initial orbit of 87-161 N.M. at an orbital inclination of 32.5 0 GMT). The space vehicle is to be launched on an azimuth of 72 degrees and the spacecraft wi 11 be inserted into an initial orbit of 87-161 N.M. at an orbital inclination of 32.5 degrees. The 62 revolution mission will have a duration of approximately 97 hours and 50 minutes. The primary and backup flight crews are of the "new generation, 11 being members of the second group of astronauts. command pilot and Edward H. White, II will be the pilot. Because the duration of the flight is one of the most significant aspects of their mission, the post- flight activities will involve expanded medical evaluation as compared with previous missions, including at least 24 hours aboard the recovery aircraft carrier, the USS WASP. James A. McDivitt will be the After conducting various orbital maneuvers and the thirteen experiments during the four-day mission, the spacecraft wi 11 reenter and touchdown approximately 400 miles southwest of Bermuda for a water landing and carrier retrieval. Enclosure MOR Noo M-913-65-04 FOR INTERNAL USE ONLY Report No. M-913-65-04 MISSION OPERATION REPORT GEMINI FLIGHT NUMBER FOUR (GT-4) OFFICE OF MANNED SPACE FLIGHT FOR INTERNAL USE ONLY FOREWORD MISSION OPERATION REPORTS are published expressly for the use of NASA General Management as required by the Administra­ tor in NASA Instruction (GT-4) OFFICE OF MANNED SPACE FLIGHT FOR INTERNAL USE ONLY FOREWORD MISSION OPERATION REPORTS are published expressly for the use of NASA General Management as required by the Administra­ tor in NASA Instruction 6-2-10 dated August 15, 1963 . The pur­ pose of these reports is to provide NASA General Management with timely, complete and definitive information on flight mission plans and results from launchings with Scout class or larger vehicles. Initial reports are to be prepared and issued for each flight project just prior to launch. Following launch, updating reports for each mission will be issued to keep General Management currently in­ formed as provided in NASA Instruction 6-2-10. Distribution of these reports has been specifically directed by Gen­ eral Management and they are not available for additiona l or general distribution . The Office of Pub I ic Affairs pub I ishes a comprehensive series of pre-launch and post-launch reports on NASA flight missions which are available for general distribution. Pub I ishec and Distributed by OFFICE OF PROGRAM REPORTS OFFICE OF PROGRAMMING NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D. C. 20546 Rtndczvous guidance & recovery system ____ _, Separation point Oxidizer tank •Equipment bay Stage 11 engine thrust chamber 10 Ft Oxidizer tank Stage I engine g1mbal point M-913-65-04 GENERAL 11 Ft 8 Ft 27 recovery system ____ _, Separation point Oxidizer tank •Equipment bay Stage 11 engine thrust chamber 10 Ft Oxidizer tank Stage I engine g1mbal point M-913-65-04 GENERAL 11 Ft 8 Ft 27 Ft Gemini Flight Number Four (GT-4) is the second manned orbital flight in the Gemini Program and the fourth flight in a series of twelve planned to develop long-duration and rendezvous capability, docking techniques, extra-vehicular activities, and controlled reentry. The first three Gemini flights demonstrated: orbital insertion capability; spacecraft structural integrity; and spacecraft systems performance and crew accommodation qualities, respectively. This GT-4 mission is intended to further demonstrate manned space flight for a period of four days, the longest ever flown by two astronauts. The space vehicle is depicted in Figure 1. MISSION OBJECTIVES 108 Ft PRIMARY • • Demonstrate and evaluate the performance of the Gemini spacecraft systems for a period exceeding four days. Evaluate the effects of prolonged exposure to the space environment on the two-man flight crew in preparation for missions of longer duration. SECONDARY • • • Demonstrate OAMS capability to perform retro fire backup. Demonstrate the capability of the spacecraft and flight crew to make significant in-plane and out-of-plane maneuvers. Conduct further evaluation of spacecraft systems as outlined below: 1 . Structure and thermo I protection 2. Environmental Control Systems (ECS) 3. Crew stations 4. Guidance and Control System 5. Orbital Attitude and significant in-plane and out-of-plane maneuvers. Conduct further evaluation of spacecraft systems as outlined below: 1 . Structure and thermo I protection 2. Environmental Control Systems (ECS) 3. Crew stations 4. Guidance and Control System 5. Orbital Attitude and Maneuver System (OAMS) • Execute the fol I owing experiments: • D-1, Basic Object Photography • D-6, Surface Photography • D-8, Radiation in Spacecraft • D-9, Simple Navigation • M-3, In-Flight Exercises • M-4, In-Flight Phonocardiogram • M-6, Bone Demineralization • MSC-1, Electrostatic Charge •Equipment bay contains: • Batteries· • Malfunction detection system IMOSI units • Range safety command control system • Programmer • Three-axis reference system !TARSI • Radio guidance system IRGSI • Autopilot • Instrumentation and telemetry system FIG. 5/24/65 Page 1 M-913-65-04 • MSC-2, Proton Electron Spectrometer • MSC-3, Tri-Axis Magnetometer • MSC-10, Two-Color Earth's Limb Photos S-5, Synoptic Terrain Photography • S-6, Synoptic Weather Photography • UNUSUAL TASKS OF THIS MISSION It One of the interesting tasks of this mission is the duration of the flight. will be the longest ever to be conducted by a two-man crew . Another highly interesting item is that control of the mission for the first time wil I be from the Mission mission is the duration of the flight. will be the longest ever to be conducted by a two-man crew . Another highly interesting item is that control of the mission for the first time wil I be from the Mission Control Center (MCC) Houston. Some elements of the Mission Control Center at Cape Kennedy and the GSFC computing facility will be standing by as a backup during the launch phase. The computing facilities at GSFC will also be used as a backup to MCC-Houston during the orbital phase. Flight controllers will man the MCC in three shifts to give complete round-the-clock coverage of the four­ day mission. Crew control of reentry will be ac~omplished by tracking the roll needle rather than nulling the down-range and cross-range needles as on GT-3. The experiments will, of course, contribute much information for the scientific and medical communities. The G4C suit which replaces the G3C suit used on GT-3 has the fol lowing new featu res: a triple overvisor, a redundant pressure closure seal (zipper), and thermal and meteoroid protection integrated in the outer cover layer. Abort procedures to be utilized by the astronauts in the unlikely event it becomes necessary for them to terminate. a mission before orbital insertion are different from those used in the Mercury program . In that program, the fireball that would have been created had a astronauts in the unlikely event it becomes necessary for them to terminate. a mission before orbital insertion are different from those used in the Mercury program . In that program, the fireball that would have been created had a conflagration occurred on the pad, would have been large enough to engulf an ejecting astronaut, so it was necessary to add an escape rocket to I ift the entire spacecraft free of the area. The GLV, on the other hand, uses self-igniting fuels which, upon mixing, create a fi reba II sma II enough so that the astronauts can eject from the spacecraft in much the same man­ ner as is done in today's high performance jet aircraft. This is called the Mode I abort pro­ cedure. The three abort modes are more fully defined by the altitude and elapsed time-after­ launch parameters depicted on Figure 2. 15,000FT. _ _ __ __.___ _~--'<-+--~- -□~ OEIAYEO ABORT PROCEDURES MODE ID - SHUTDOWN, SE PARATE, TURN AROUND, MOOE ll - SALVO RETROS AFTER SHUTDOWN MOOE n (WA IT 5 SECS ) MOOE I - EJECT AfTEll SHUTDOWN RETROFIRE ' ~' MOOE I 50 SECONDS SEA LEVEL- - - - - - - - - - - ' ' - -- -L - - ' - - 5/24/65 FIG . 2 Page 2 LAUNCH VEHICLE DESCRIPTION M-931-65-04 The RETROFIRE ' ~' MOOE I 50 SECONDS SEA LEVEL- - - - - - - - - - - ' ' - -- -L - - ' - - 5/24/65 FIG . 2 Page 2 LAUNCH VEHICLE DESCRIPTION M-931-65-04 The Gemini Launch Vehicle (GLV) has been modified by man-roting an Air Force Titan II missile. The GLV has two stages, the first 71 feet long and the second 18 feet long; both stages have a diameter of 10 feet. The gross loaded weight of the two stages is 337,521 pounds and they both burn storable hypergolic (self-igniting upon mixture) propellants. First stage thrust is approximately 430,000 pounds at sea level. Second stage thrust is approximately 100,000 pounds. The various systems of the GLV have been detailed in previous Gemini MOR 1s and what follows is additional information concerning modifications made to GLV-4. The fuel dampener and oxidizer standpipe used to suppress longitudinal oscillations have been redesigned. Butt welding vice lapped joints have been utilized on the fuel tank conduits to eliminate minute cracks. Malfunction Detection System circuitry has been redesigned to provide separate indications of the subassembly thrust level and additional insulation has been applied to provide increased fire protection. Sixteen T/M readout points have been removed from the GLV because they are no longer required and one range safety circuit has been added to the destruct system interlocking AGE and the GLV motor driven switch control. This circuit will . Sixteen T/M readout points have been removed from the GLV because they are no longer required and one range safety circuit has been added to the destruct system interlocking AGE and the GLV motor driven switch control. This circuit will prevent switch cycling in the event that both set and reset signals are inadvertently applied during checkout. TABLE I PROJECT COST (In Millions) FY 62 FY 63 FY 64 FY 65 FY 66 FY 67 Total Spacecraft 30.3 205. 1 280.5 165.3 122.7 19. 1 823.0 Launch Vehicle 24.4 79. 1 122.7 115.4 88.6 8.5 438.7 Operational Support 0 1 4.9 15. 7 27.7 30.8 13.0 92.2 Total RD & 0 54.8 289. 1 418.9 308.4 242. 1 40.6 1353.9 This level of funding will provide for twelve Gemini Launch Vehicles, twelve space­ craft, seven Agena Target Vehicles, six Atlas booster missiles and the operational costs of flight testing and the associated Ground Support Equipment. SPACECRAFT The spacecraft is 18. 75 feet long and its two sections, a reentry module and an adapter section will weigh 7799 lbs. fully loaded with the astronauts onboard. The configuration will be the same as was flown on GT-3 except for the following: minor changes have been made to switch positions and nomenclature, three additional (total of six) adapter 5/24/65 Page 3 astronauts onboard. The configuration will be the same as was flown on GT-3 except for the following: minor changes have been made to switch positions and nomenclature, three additional (total of six) adapter 5/24/65 Page 3 M-913-65-04 batteries will be required, radial thrusting TCA's and burst diaphragms in the 11 811 package that were removed for GT-3 are both installed on GT-4, and will act through the Spacecraft Centers of Gravity. An HF antenna has been added to the adapter section for orbital use and the HF transciever there has been removed. The C-band phase shifter now has its own inverter, the recovery flashing light can now be turned off during dayIight hours, the HF antenna on the cabin section has been redesigned, and the adapter $-band transponder in the adapter section has been replaced with a C-band transponder which will have a different pulse spacing In the GT-4 mission S/C, urine wi 11 be dumped from the one in the spacecraft. directly overboard from the urine bellows through a shut-off and selector valve, a solenoid valve and a heated line. Redundancy is provided by the capability to dump urine through the launch cooling heat exchanger (water boiler}. The main chute disconnect cartridge has been changed from a 22-second time delay to a zero second delay and Redundancy is provided by the capability to dump urine through the launch cooling heat exchanger (water boiler}. The main chute disconnect cartridge has been changed from a 22-second time delay to a zero second delay and new long-life attitude thrusters have been installed. EXPERIMENTS The 13 experiments are depicted and described on the following pages: D-1 BASIC OBJECT PHOTOGRAPHY 1. D-1, Basic Object Photography In conducting this experiment, the as­ tronauts will employ elaborate photo­ optical equipment to investigate the technical problems associated with observing, evaluating, and photo­ graphing objects in space. These objects include the 2nd stage of the launch vehicle and natural celestial bodies such as the moon. Data from this experiment will be used to evaluate the astronauts' ability to view and track objects, and to maintain object-camera orientation by maneuvering the spacecraft. Equipment which wi 11 be used is illustrated in Figure 3. FIG. 3 5/24/65 Page 4 M-913-65-04 0-6 SURFACE PHOTOGRAPHY D-8 RADIATION IN SPACECRAFT (PORTABLE UNIT) FIG. 4 FIG. 5 2. D-6, Surface Photography This experiment wi 11 investigate the technical problems associated with an astronaut's ability to acquire, track, and photograph terrestrial objects from a space­ craft with more elaborate photo­ opti ca I equipment than that used previously. The astronaut will photograph This experiment wi 11 investigate the technical problems associated with an astronaut's ability to acquire, track, and photograph terrestrial objects from a space­ craft with more elaborate photo­ opti ca I equipment than that used previously. The astronaut will photograph selected series of objects during day-side and night-side intervals of the flight using specified Iens-fi Im combi­ nations. The resulting data wi 11 be used to eva Iuate the astronaut's ability to maintain object-camera orientation by maneuvering the spacecraft. Figure 4 shows the camera mount installed on the spacecraft window. 3. D-8, Radiation in Spacecraft Data from this experiment will be used to supplement external radi­ ation measurements in studying the dose levels within the space­ craft resulting from passes through regions of varying radiation intensity. Two tissue-equivalent, current-mode ionization chambers wi 11 be used to measure the variation of absorbed dose-rate inside the spacecraft. Five small packets containing radia­ tion detection and measurement devices will be placed at various locations in the cabin to as