Gemini 4 Experiment Debriefing, 1967

Action MAIL CODE NAME Approval Call Me Concurrence file Information Investigate and Advise NASA FORM 26 I • AND SPACE ROUTING SLIP ADMINISTRATlo-1 NATIONAL AERONAUTICS ____ .l ,Nmote and Forward Note and R_e_hl_rn___ _ _ __jL,P;;, -;R;:e::q::-u•=s¦I::::.::_____ Per Teleph one Conversation _ _ _ _J__:R..e,.c,ommendation See·Me Signature Circulate and De I s roy (fL 1 J 'I, h'.C.9-- § TEL. NO ( · or ,ode) & EXT. 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 M-913-65-04 ADDITIONAL GT-4 FLIGHT PLAN ACTIVITIES 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. Potential future application includes crew transfer, in­ flight repair, and inspection of orbiting objects. 2. Demonstration of extravehicular maneuvering using a simple, one­ man propulsion unit. This device could be used with or without 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. Flashing lights identical to those designed for the Gemini/Agena Vehicle have been insta I led on the booster second stage for th is test. 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 will be sufficient to prevent the flashing lights from disturbing the pilot's visual dark adaptation. The first orbit will be occupied with operational checks of the spacecraft guidance, maneuvering, and environmental control systems. The 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. The total time separated 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. Shortly ofter passing Ascension, McDivitt wil I maneuver ahead of the booster with 5 feet per second separation velocity. Because this maneuver places the 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 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 above 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 - this time using a maneuver which will place the Gemini spacecraft on an orbit with a predicted lifetime of four days. 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. Torso ­ 1. Change to Nomex (HT-1) 11 Linknet11 in restraint layer for increased structure I strength. 2. Incorporation of strain relief zipper in sealing closure. 3. 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 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 the helmet. The multivarious layers of materials used in the EVA G4C suits are delineated in Figure 4. It should 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: FIG. 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 HH NYLON OUITR ~6~~ T~~~~~} ~~~;:) USE: WEAR AND SOLAR REFLECTANCE 7 LAYERS ALUMINIZEO MYLAR SEPARATED BY 7 LAYCAS UNWOVEN DACRON SPACERS THERMAL AND MICROMETEOROID LAYERS HH NYLON INNER MICROr,,'tn OROID STOPPER LAYERS !EACH 6. 8 OZ/YD2 WH IT[ I USE: WEAR ANO MICR0~,1£TEO ROI D PRO TE CT ION PRESSURE AND RESTRAINT LAYERS r----­ 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 RESTRAINT lAVlR UM( NH DACRON Al.;Q HflO~ u-J 4 oz vo 21 FIG. 4 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 and accomplishes propulsion by jetting oxygen out through a single forward firing nozzle and two aft firing nozzles as selected and aimed by the operator. It 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 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. James A. McDivitt will be the 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. 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 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 additional 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 ____ _, 11 Ft 8 Ft Separation point Oxidizer tank •Equipment bay 27 Ft Stage 11 engine thrust chamber 108 Ft 10 Ft Oxidizer tank Stage I engine g1mbal point •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 M-913-65-04 GENERAL 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 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 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 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 One of the interesting tasks of this mission is the duration of the flight. It 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 features: 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 conflagration occurred on the pad, would have been large enough to ABORT PROCEDURES 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. FIG . 2 MOOE I - EJECT AfTEll SHUTDOWN MOOE ll - SALVO RETROS AFTER SHUTDOWN MODE ID - SHUTDOWN, SE PARATE, TURN AROUND, RETROFIRE -□~ OEIAYEO MOOE n (WA IT 5 SECS ) 15,000FT. _ _ ____.____~--'<-+--~- ' ~' MOOE I 50 SECONDS SEA LEVEL-----------''----L--'-- 5/24/65 Page 2 M-931-65-04 LAUNCH VEHICLE DESCRIPTION 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 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 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 from the one in the spacecraft. In the GT-4 mission S/C, urine wi 11 be dumped 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 new long-life attitude thrusters have been installed. EXPERIMENTS The 13 experiments are depicted and described on the following pages: 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. D-1 BASIC OBJECT PHOTOGRAPHY FIG. 3 5/24/65 Page 4 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 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 ascertain their suitability as convenient dosimeters of space radiation and measure total accumulated dose. Figure 5 shows some of the equipment to be used for this experiment. M-913-65-04 0-6 SURFACE PHOTOGRAPHY FIG. 4 D-8 RADIATION IN SPACECRAFT (PORTABLE UNIT) FIG. 5 5/24/65 Page 5 the manner in which this exercise wi 11 be performed. 5/24/65 Page 6 FIG. 7 4. D-9, Simple Navigation This experiment is designed to develop and test navigation pro­ cedures which employ a simple stadimetric device and a sextant to make sightings and measurements in space using the horizon and stars as references. Data from sightings wi 11 be used in compu­ tations to determine orbital parameters. These results wi 11 be compared with actual parameters to determine the accuracy of the procedures. The hand held sextant to be used is shown in Figure 6. 5. M-3, In-Flight Exerciser The purpose of this experiment is to assess the astronauts' capacity to perform physi ca I work under spacecraft conditions. Monitored exercise wil I be performed by the astronauts prior to the flight to establish control data. l·sotonic exercises employing a bungee cord and involving the arms and legs wi 11 be taken prior to and a.fter exercising. Pulse rate wil I be monitored continuously. The inflight data obtained wil I be compared with the control data to determine the· capacity for work in space. Figure 7 shows M-913-65-04 0-9 SIMPLE NAVIGATION HAND HELD SPACE SEXTANT MG5-8097 FIG. 6 M-3 IN-FLIGHT EXERCISER 6. M-4, In-Flight Phonocardiogram The purpose of this experiment is to measure the fatigue-stage of an astronaut's heart muscle during a long-duration flight. A microphone wi ll be applied to an astronaut's chest wal I at the cardiac apex. Heart sounds detected during the flight will be recorded on an on­ board biomedical recorder. The sound trace wi 11 be compared to the waveform obtained from a simultaneous infl ight electro­ cardiogram to determine the time interval between electrical activation of the heart muscle and the onset of ventricular systrole. Figure 8 illustrates the method of installation of the phono­ cardiogram transducer. 7. M-6, Bone Demineralization The purpose of this experiment is to establish the occurrence and degree of bone demi nera Ii­ zati on resulting from prolonged weightlessness during spaceflight. Spec ia I X-rays wi 11 be ta ken of an astronaut's heel bone and the terminal bone of the fifth digit of the right hand. Three pre­ flight and three postflight exposures wi 11 be taken of these two bones and compared to determine if any bone deminerali­ zation has occurred due to the space flight. Figure 9 i 11 ustrates the laboratory procedure which will be used for this experiment. M-913-65-04 M-4 IN-FLIGHT PHONOCARDIOGRAM PROTOTYPE PHONOCARDIOGRAM TRANSDUCER AND SIGNAL CONDITIONER FIG . 8 GEMINI EXPERIMENT NO. M·& BONE DEMINERALIZATION ESTABLISH DEGREE PURPOSE OF BONE DETERIORATION EQUIPMENT STANDARD X-RAY WEIGHT N/ A VOLUME N/ A PRE AND POST PROCEDURE FLIGHT x-RAY LOCATION N/ A i " ' MG4-1886 FIG. 9 5/24/65 Page 7 8. MSC-1, Electrostatic Charge Before rendezvous missions are attempted, an investigation must be made of the possibility of inadvertent ignition of pyrotechnics and other detri­ menta I effects due to discharge of electrostatic charge potentials during rendezvous. In this experiment, an electrostatic­ potential meter, which protrudes through the wa 11 of the space­ craft adapter assembly, wi 11 be used to detect and measure any accumulated electrostatic charge that may be created on the surface of the spacecraft by ionization from engine exhaust. This dota wi 11 be a no Iyzed to determine if the charge is adequate to create a rendezvous hazard. Fig­ ure 10 shows the detector instal lotion. 9. MSC-2, Proton Electron Spectrometer This experiment is designed to measure the quantity and energy of protons and electrons present immediately exterior to the orbiting spacecraft. This wil I be accomplished by means of a scintillating-crystal, charged­ particle analyzer mounted on the adapter assembly of the spacecraft. Data from this experiment wil I be used to correlate radiation measure­ ments made inside the space­ craft and to predict radiation levels on future space missions. The proton electron spectrometer instal lotion is shown in Figure 11 . MSC-1 ELECTROSTATIC CHARGE FIG. 10 M-913-65-04 MSC-2 PROTON ELECTRON SPECTROMETER FIG. 11 5/24/65 Page 8 M-913-65-04 10. MSC-3, Tri-Axis Magnetometer In this experiment, the direction and magnitude of the earth's magnetic field with respect to the spacecraft will be measured. A tri-axis fluxgate magneto­ meter, mounted in the adapter assembly of the spacecraft wi 11 be used. The equipment instal lo­ tion is shown in Figure 12. - 11. MSC-10, Two-Color Earth's Limb Photos The astronaut wil I obtain photo­ graphs of the earth's limb using a hand-held camera, black and white film, and a special filter mosaic which will allow each picture to be taken partly through a red filter and partly through a blue filter. After the flight, the negative will be subjected to careful measure­ ments, and the resulting data will be used in statistical analyses to evaluate the limb radiance. These studies will be used to determine if the sun-lit earth's limit can be reliably observed in the short­ visible or near-ultraviolet spectral region. The camera to be used for this experiment is shown in Figure 13. MSC-3 TRI-AXIS MAGNETOMETER MSC-10 TWO-COLOR EARTH'S LIMB PHOTOS MG5·8105 FIG. 13 FIG. 12 5/24/65 Page 9 12. S-5, Synoptic Terrain Photography The objective of this experi­ ment is to obtain high quality photographs of selected parts of the earth's surface. The spa1.,c:craft will be manually oriented from an orbit mode attitude to a moderately high camera depression angle attitude. After a series of photographs has been taken, the spacecraft will be reoriented to the orbit mode attitude. Four spacecraft orientation maneuvers will be required during which approxi­ mately 40 pictures will be taken over areas of the United States. Figure 14 shows one of the photos taken by Gordon Cooper which is similar to the terrain photographs planned . 13. S-6, Synoptic Weather Photography The objective of this experi­ ment is to learn more about the earth's weather systems by obtaining high quality photo­ graphs of selected cloud for­ mations. As in experiment S-5, the spacecraft will be oriented from an orbit mode attitude to a moderately high camera depression angle attitude. After a series of photographs has been taken, the spacecraft wi 11 be reoriented to the orbit mode attitude. Approximately 10 orientation maneuvers will be required during which approximately 40 pictures will be taken. The photograph shown in Figure 15 taken by Gordon Cooper is similar to those planned on this flight. 5/24/65 M-913-65-04 GEMINI DPEltllfNT NO. S.5 SYNOPTIC TERRAIN PHOTOGRAPHY ,.,. .:t PURPOSE OITAIN HIGH QUALITY PHOTOGIAPHS Of THI EARTH'SSUlfACf EQUIPMENT 70MM CAMERA AND fllM WEIGHT I LI. VOlUMI 0.036 CU. n. PROCEDURE POSITION sm1mn, TAIi PICTURES LOCATION PRISSURIZID CAIIN PMOTOGUIH Of THI HIIAlAUS IN THI NIDIA, IIIPAl, 11111 IOROII AHA, THIN IT ASTRONAUT l. GOIDON C00,11, JI., DUIING HIS 22-01111 IA-f IIISSION. MC4· 1768 FIG. 14 GOIN OPIIIIINT NO. S-6 SYNOPTIC WEATHER PHOTOGRAPHY PURPOSE OITAIN HIGH QUALITY aoue PHOTOGIAPHS EQUIPMENT 10 11 CAMDA Me ,u WEIGHT I LI. YOlUMl 0.036 cu. n. PROCEDURE POSITION SPACKWT Me TAIi PNOTOGIAPIIS lOCATION PIISSUIIZED WIN PIIOIOGUPH Of ClOUDS AND lffl IUIIIA 11S1 COAi!. WIST Of UNOOII. TWI 1Y ASIIOIIAUI l. IOIDOII COOPII, ll, DU- HIS 22-11 IA•t IIISSIOII. MC4· I767 FIG. 15 Page 10 M-913-65-04 ASTRONAUTS The Command Pilot for the GT-4 mission will be James A. McDivitt and the Pilot will be Edward H. White, II. The backup flight crew will consist of Frank Borman as Command Pilot and James A. Lovell, Jr., as Pilot. Their pictures and biographies follow: FIG. 16 FIG. 17 JAMES A. MCDIVITT Born in Chicago, Illinois on June 10, 1929. He graduated first in his class from the University of Michigan with a B. S. in aeronautical engineering. McDivitt is ma rried to the former Patricia A. Hass of Cleveland, Ohio and has three children. McDivitt joined the Air Force in 1951 and is an Air Force Major. He was awarded three Distinguished Flying Crosses, five Air Medals and the Choo Moo Medal from South Korea. He is a graduate of the United States Air Force Experimental Test Pilot School and the United States Air Force Aerospace Research pilot course. He served at Edwards Air Force Base, California, as an experimental test pilot. McDivitt has logged more than 3,000 hours flying time, including 2,500 hours in jet aircraft. McDivitt was selected as an astronaut by NASA in September 1962. In addition to participating in the overal I astronaut training program he has had additional specialized duties. These duties include monitoring the design and development of the guidance and navigation systems for the Gemini and Apollo spacecraft, as wel I as monitoring the overall Apollo Command and Service Modules. EDWARD H. WHITE II Born in San Antonio, Texas, on November 14, 1930. White received his B.S. from the United States Military Academy and his M.S. in aeronautical engineering from 5/24/65 Page 11 M-913-65-04 I ' the University of Michigan. He is married to the former Patricia E. Finegan of Washington, D.C. and has two children. White, an Air Force Major, received flight training in Florida and Texas, following his graduation from West Point. He attended the Air Force Test Pilot School at Edwards Air Force Base, California, in 1959. White was later assigned to Wright-Patterson Air Force Base, Ohio, as an experimental test pilot with the Aeronautical Systems Division. In this assignment he made flight tests for research and weapons systems development, wrote technical engineering reports, and made recommen­ dations for improvement in aircraft design and construction. He has logged more than 3,600 hours flying time, including more than 2,200 hours in jet aircraft. White was named as a member of the astronaut team selected by NASA in September 1962. FRANK BORMAN Born in Gary, Indiana on March 14, 1928. He re­ ceived his B.S. from the United States Military Academy and his M.S. in aeronautical engineering from the California Institute of Technology. He is married to the former Susan Bugbee of Tucson, Arizona and has two sons. Upon graduation from West Point, Borman, now an Air Force Major, chose an Air Force career and received his pilot training at Williams Air Force Base, California From 1951 to 1956 he served with fighter squadrons in the United States and in the Philippines and was an instructor of thermodynamics and fluid mechanics at the U.S. Military Academy, West Point. He was graduated from the USAF Aerospace Research Pilots School in 1960 and later served there as an instructor. In this capacity he prepared and delivered academic lectures and simulator briefings, and flight test brief­ ings on the theory and practice of spacecraft testing. Borman has logged more than 4,400 hours flying time, including more than 3,600 hours in jet aircraft. Borman was one of the nine astronauts named by NASA in September l 962. JAMES A. LOVELL, JR. Born in Cleveland, Ohio, on March 25, 1928. He received his B. S. from the United States Naval Academy. Lovell is married to the former Merilyn Gerlach of Milwaukee, Wisconsin and has three children. Love I I, a Navy Lieutenant Commander, received flight training following his graduation from Annapolis. He served in a number of Naval 5/24/65 Page 12 FIG. 18 FIG. 19 •• - M-913-65-04 aviator assignments including a three year tour as a test pilot at the Naval Air Test Center at Patuxent River, Maryland. His duties there included service as program manager for the F4H Weapon System Evaluation. Lovell was graduated from the Aviation Safety School of the University of Southern California. He served as flight instructor and safety officer with Fighter Squadron 101 at the Naval Air Station at Oceana, Virginia. Lovell has logged 3,000 hours flying time, including more than 2,000 hours in jet aircraft. Love II was selected as an astronaut by NASA in September 1962. In addition to participating in the overal I astronaut training program, he has been assigned special duties. These duties included monitoring design and development of recovery and crew life support systems. These include space suits, environmental control system and developing techniques for lunar and earth landings and recovery. The launch trajectory for the GT-4 mission wi 11 be similar to that flown by GT-3. ln­ sertion wi 11 be at the same altitude, 87 miles, but the first apogee of GT-4 will be 161 miles. The Gemini launch sequence is shown in Figure 20. FLIGHT PLAN In addition to the various orbi ta I maneuvers to be performed during the mis­ sion, as ca Iled out in Table II, other activities will be taking place as is shown below in Table 111, a summarization of the Flight Plan. The consumable items loaded onboard the spacecraft are shown in Table IV. TRAJECTORY 811Ul MODE 111: SHUTDOWN j •SEPARATE SIC 5:10 CHANGE -·-·- •RETRO &REBffllY A200.m ABORT MOOl SEflllNCE L 2:48 START 11:SHUTDOWN T RADIO GUIDANCE j.SALVO RETROS . 1:40 CHANG ABORT MOOE 1:19 MAX Q 2:34 BECO ~.ET11SON RETRO I 5.5G·s •=SEOllll:E TU 75,000' 1·­ ~ 42.000' IIElAYEO AQIE U:SfUTOOWN •WAIT 5SECONDS 25.000' •SALVO RETim •JETTISON RmO SECTIII 0:50 CHANGE ABORT····-···-· 15.000' •I.AIIN SBIIIIG MODE Q:23 START PITCH 2500' Q:20 STOP ROLL 012• l:EJECT 2000· ~l Q:10 START ROLL oas· :OO LIFT OFF-- ... - _______... 0 50 • RANG -NAUTICAL MIES ­ FIG. 20 • 5/24/65 Page 13 MANEUVER HP/HA TRANSLA­ ~v AFTER POINT OF DIRECTION TIONAL MANEUVERS APPLICATION OF THRUST THRUSTER PURPOSE Separation l0FPS 87/161 N.M. SECO+2­ FWD AFT S/ C-Booster Separation 1 ?FPS 91/161 N.M. 2d Apogee FWD FWD Adjust lifetime {for insertion dispersions. Evaluate thruster operation. 2A 12FPS Apogee of FWD Left Ad just Iifetime. Evaluate thruster operation . 30th Rev. +TSC #1 Approx. 15 min Left Right 5FPS Evaluate thruster operation. Determine visual after 2A characteristics of thruster plume . TSC #2 5FPS 5 min. after Down Evaluate thruster operation. Determine visual Up TSC #1 characteristics of thruster plume. TSC #3 5 min after 5FPS Down Evaluate thruster operation. Determine visual Up TSC #2 characteristics of thruster plume. 27FPS 94/ 134 N.M. Perigee AFT Adjust lifetime. Evaluate 3-axis fol lowing 2A 28 AFT application. 4FPS 3A Apogee of FWD FWD Adjust Iifetime. Evaluate thruster operation. 45th Rev . 6FPS 93/ 124 N.M. Perigee AFT FWD Adjust lifetime. Evaluate thruster operation. following 3B 1 l0FPS 62d Rev. 4 45/99 AFT AFT Achieve OAMS retrofire. Evaluate thruster (45/97)* {or 66th Rev. )* operation. s:: -b (,J I 0, I °' *FOR PACIFIC LANDING ~ +TRANSLATIONAL SYSTEM CHECK M-913-65-04 TABLE Ill IN-FLIGHT ACTIVITIES Time Revolution HRS:MIN No. 0:12 1 1:45 2 4:35 3-4 7:45 5-6 11:15 7-8 13:05 9 17:05 11 19:52 13-14 24:00 16 25:58 17-18 29:25 19 31 :20 20 31 :40 21 33:20 22 43:00 28 44:25 29 46:48 30 47:33 31 52:30 33-34 54:35 35 56:35 36-37 41 70:26 46 76:30 49 77:20 50 90:45 58 95:45 61 96-35 62 97:32 97:46 63 5/24/65 EVENT Insertion Check I ist D-9 Experiment Translation Maneuver D-6 Experiment MSC-1,2,3, and 10 Experiments M-3 Experiment MSC-2 and 3 Experiments D-8 Experiment D-9 Experiment D-1 Experiment M-3 Experiment S-5 Experiment HF Communication Tests D-9 Experiment S-6 Experiment MSC-2 & # Experiments D-8 Experiment D-8 Experiment S-6 Exoeriment S-6 Experiment S-5 Experiment S-6 Experiment M-3 Experiment MSC-1 Experiment Translation Maneuvers Translation Maneuvers Thruster Failure Check Power Down S/C S-5 Experiment S-6 Experiment M-3 Experiment D-9 Experiment MSC-2 & 3 Experiments S-6 Experiment D-9 Exoeriment Translation Maneuvers M-3 Experiment Apollo Yaw Orientation Power Down S/ C M-3 Experiment D-9 Exoeriment Power Down S/ C M-3 Experiment Pre Retro Checklist, TR-5 Minutes Checklist, TR-1 Minute Checklist Retrofire, Retro Jettison, Post-Retro Checklist Reentry, Drogue Chute Deploy, Pilot Chute Deploy, Main Chute Deploy, Two-Point Suspension, Touchdown, Post-Landing Checklist Page 15 Function CP p Dav Niaht X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X :.<. X X X X )( X X X X X X X X X X X X X X )( X X X X X X X X X X X X X X M-913-65-03 TABLE IV GT-4 CONSUMABLE LOADINGS ITEM QUANTITY REMARKS Batteries OAMS Propel I ants Odixizer Fuel Oxygen Primary Secondary Lithium Hydroxide Food Drinking Water Spacecraft Adapter RCS Propellants O xidizer Fuel 703 I bs. based on a 2400 A-h 246 lbs 164 lbs 52 lbs 13 lbs 97 lbs lb lbs 14 lbs 61 lbs 40. 4 lbs 3l.61bs Each battery has a 400 A-h capacity Egress bottle are also carried if ejection is required. LANDING SEQUENCE At the end of the mission, the parachute landing sequence shown in Figure 21 will be employed. One item that should be mentioned in this regard is that should the 84-foot main parachute fail to open, the crew can abandon the spacecraft by eject­ ing and using their personal parachutes to effect a safe water landing. The latter sequence would also be employed should the spacecraft come in overland instead of the intended water landing. FIG. 21 GEMINI PARACHUTE LANDING SEQUENCE 50,000 FEET - HIGH ALTITUDE DROGUE CHUTE DEPLOYED \ 21 , 000 FEET - Oft:N CABIN VfNT t VALVE 10, 600 FEET - PILOT PARA.CHUTE DEPLOYED 9,600 FEET - It A It SECTION SEPARAT ION 9,000 FEET - MAINCHUTE DEPLOYMENT !' 6,700 FEET - TWO-POINT SUSPENSION 1,500 FEET - CABIN WA.Tflt SEAL CLOSED 1_ SEA LEVEL - TOUCHDOWN ~~- JffilSONCHUTf ~ ­ 5/ 24/65 Page 16 M-913-65-03 MISSION MANAGEMENT RESPONSIBILITY The Gemini Program is managed by the Gemini Program Director who exercises his direction through the Project Manager at the Manned Spacecraft Center. The direc­ tion of a specific mission is accomplished by a Mission Director acting under the cognizance of the Associate Administrator for Manned Space Flight from the time a space vehicle is committed to flight test until the end of the Mission Period. TITLE Program Director (Acting) Deputy Program Director Program Manager Mission Director TRACKING & DATA ACQUISITION MSC GSFC ETR Staff Gemini Flight Ops Rep Requirements Coordinator Security Officer Meteorologica l. Group NAME Dr. G . E. Mueller Mr. W.C. Schneider Mr. C. W. Mathews Mr. C.C. Kraft PROGRAM MANAGEMENT NASA HEADQUARTERS Office of Manned Space Fliqht I PROJECT MANAGEMENT Manned Soacecraft Center I SPACECRAFT MSC McDonnell Aircraft Co. OPERATIONS ORGAN IZATION FOR MISS ION PERIOD ORGANIZATION NASA Headquarters NASA Headquarters MSC MSC LAUNCH VEHICLE MSC SSD Aerospace Corporation Martin Company Aerojet General DOD Mgr for MISSION DIRECTOR MS F Support ...___--.-_____,----- ----~ Operations Gemini Program Manager Deputy for Flight Operati ons DO D Recovery Director Atlas/ Agena Medical Publ ic Fl ight Crew 5/24/65 Launch Director Affa irs Director Director Director ---------------------------------- Page 17 Flight Crew Medical Monitor M-913-65-04 TRACKING AND DATA ACQUISITION The ground support network for GT-4 wi 11 be the Gemini Manned Space Flight Network (MSFN) illustrated in Figure 22 and tabulated in Table V. There will be, however, some mi nor modifications to the MSFN for the GT-4 mission. These changes for the GT-4 fl ight are prima rily in locating the range tracking ships in positions most advantageous fo r the orbits to be flown . TABLE V - NETWORK REQ UIREMENTS FOR GT-4 Network Ra dar G round Station Code C Band Merritt Island MILA X Cope Ken nedy/ CNV/ M iss ion Contro l MCC Patrick AFB PAFB X lr.:.""d Bahamas G BI X Grand Turk GTI X IAntiouo ANT X Ascension Island ASC X Valkario Fla. VA L Eleuthera Island ELU Bermuda BDA X Conarv Is land CYI X Kono N iae rio KNO Tananarive TAN Cornarvon CRO X Canton Is land CTN Hawaii HAW X Guovmos Mex. GYM Corous Christi TEX Rose Knot Victor RKV Coasta l Se ntrv CSQ Ranae Tracker RTK X Pt ArQuello, Cal CAL X White Sa nd~ NM WHS X Ea lin AFB EG L X M SC, Houston MCC ITe lemetry Airc raft (d) NOTES: Tracki ng Telemetry A/ G Mistrom Acq. aid G emini launch Spacec ra ft Commend vehi cl e voi ce or oth ers as I isted PCM FM/ FN Li nks R/T D/T RSDP * DCS Tone UHF HF received GE-Mod 111 - G X X Xa 3 X X X X X Xb Xo 3 Xb X Xe Xe 3 Xb X X Xe Xe 3 Xe X X Xe X X X 3 Xb X X Xe X 3 X X X X X 2 Xo 2 Xo X 3 X X X X X 2 Xa X 3 X X X X X 3 X X X X 3 X X X X X 3 X X X X X 3 X X X X X 2 Xo X X X X X X Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe Xe . Xe Xe Xe Xe Xe Xe Xe Xe X X X X Xe Xe Xe Xe Fli ght Controller Manned Sites X X X X X X X X X a - Record Only c - Remoted to ond from the MCC b - Remoted to MCC d - Three telemetry aircraft in pri mary recovery area * Remote Site Data Process (RSDP) The ground network support facilities include the MCC-Houston, Cape Kennedy (CNV), Air Force Eastern Test Range (AFETR) downrange stations, the MSFN, and Goddard Space Flight Center (GSFC). Real time tracking and the acqui­ sition of data for post flight evaluation will be provided by optical and photo­ graphic systems, MISTRAM, GE Mod Ill radar, C-band radar, and the Impact Predictor OP) 7094. The network as listed in Table V will monitor spacecraft and launch vehicle PCM telemetry. The flight controller-manned stations, as shown in Table V will display selected spacecraft data for real-time evaluation and transmit these data to the MCC via teletype. The MCC will use both the Digital Command System (DCS) for transmitting commands. All the remote sites that are flight controller-manned, except for GYM, will have the DCS command capability. Tone commands for use by the Range Safety Officer will be used for manual fuel cutoff (MFCO), auxiliary second stage cutoff (ASCO), and Destruct. 5/24/65 Page 18 -0 0 (0 (1) I / /_ I \ / / l TH I \ /J I \ P ,I C / I w I 0­ <.n I 0 .i,.. FIG. 22 M-913-65-04 BACKGROUND Project Gemini is the stepping stone between the comparatively simple one-man orbital flights of Project Mercury and the complexities involved in the multi-man lunar flights of Project Apollo. As such, Gemini's prime reason for being is to increase knowledge of man's capabilities in space and in developing operational techniques to support the Apollo Program. Thus, Gemini's objectives become: a. b. c. Long-duration flights - up to fourteen Rendezvous and maneuver in space Docking with a target vehicle days d. Extra-vehicular activities by the astronauts e. Control led reentry f. Operational training for al I flight personnel concerned To accomplish these objectives, a series of flights have been planned of which this GT-4 is the fourth. The first three demonstrated respectively: orbital insertion capability, spacecraft structural integrity, and crew accommodation qualities. The four-day manned flight will further demonstrate manned space flight capabilities for the support of future missions of even longer duration. The remaining eight Gemini flights, all of which will be manned by two astronauts, are tabulated in Table VI ' with type of missson and approximate date of flight: Mission No. GT-5 GTA-6 GT-7 GTA-8 GTA-9 GTA-10 GTA-11 GTA-12 TABLE VI Mission Objectives Seven-day flight with experiments* Radar rendezvous and docking 14-day Extra-vehicular activities Optical rendezvous and docking Simultaneous countdown and rendezvous Direct rendezvous Apollo-LEM rendezvous simulation Apollo-LEM abort simulation Date Latter 1965 Early 1966 Early 1966 Early 1966 Mid 1966 Mid 1966 Late 1966 Early 1967 *Includes rendezvous evaluation pod The planned end-of-the-mission touchdown point is in the Atlantic Ocean approxi­ mately 400 miles southwest of Bermuda as is shown in Figure 23. This is the primary landing area. The GT-4 mission employs a zone concept for recovery which estab­ lishes four recovery zones: East Atlantic, West Atlantic, West Pacific and Mid­ Pacific. Each zone consists of a circular area with a radius of 240 nautical miles in which various ships and planes will be stationed. An aircraft carrier will be sta­ tioned only in the primary landing area as ii lustrated in the recovery forces diagram 5/24/65 Page 20 00 M-913-65-04 GT-4 PRIMARY AND SECONDARY LANDING ZONES, RECOVERY SHIP SUPPORT AND CONTINGENCY RESCUE FORCES \);J DO 30" ~ 00 HICKAM 0 00 00 0 GUAM O" ~ PRIMARY l~ RECOVERYAREA 0 PAGO PAGO 8 " REEm;~ANEA CVS CARRI ER 30" 00 OESTROYER AO OILER 0 CO NTINGE NCY RESCUE FORC ES /)};; FIG. 23 of Figure 24. Other areas in the world along the ground tracks are called contingency landing areas. Because these contingency landing areas are world-wide, it has been necessary to pre-position certain aircraft with their associated crews, pararescuemen, and paramedics so that they will be able to reach the spacecraft in sufficient time to render aid to the downed astronauts. These contingency forces have been deployed to the bases shown in Figure 23 . It should be noted that there are numerous types of aircraft in the launch area and primary landing area for telemetry, weather reconnaissance, aerial photography, and recovery operations. In addition to these aircraft there are also several helicopters in the pri­ mary recovery area from the aircraft carrier that are carry­ ing swimmers. These swimmers deploy into the water and attach an auxiliary flotation collar to the spacecraft. Launc area recovery forces are de­ picted in Figure 25. RECOVERY AREA FORCES ARS AIRCRAF T PRIMARY RECOV ERY ZONE 200 MILES BY USS WASP AND ONE DESTROYE R AIRCRAFT 1 USAF SSB RELAY AIRCRAFT AT TOUCHDOWN POINT 3 WASP HELICOPTERS 1 WASP COMMAND (480 MILES N DIAM ETER ) LANDING FOOTPRINT (ELLIPSE - 40 MILES) ~ ARS AIRCRAFT FIG. 24 5/24/65 Page 21 M-913-65-04 LAUNCH AREA RECOVERY FORCES 2 MINE USA M 113 LARK USMC \ AMPHIBS LANDING FOOTPRINT ( 27 MILES LONG) TANKS FOUR HELICOPTERS TWO PHOTO JETS FIG. 25 5/24/65 Page 22 NASA ROUTING SLIP ,. 2. CODE NAME (if ,,,msary) ACTION APPROVAi. CONCURRENCE FILE INFORMATION INVESTIGATE ANO ADVISE 3. NOTE ANO FOIIWAR0 NOTE ANO RETURN l'ER REQUEST RECOMMENDATION 5. SEE ME SIGNATURE 6. REPlY fOR SIGNATURE OF, 7. REMARKS: ~ - Of4-· ~ ~ ~~~-­ &._. Q ~u' HL ~ J)k ~ - ~ ~ 1-~t I l · J>~~P1~,~s ~A-- 'J- ~ ~<L -~ f-i ~ o'\rv--J ~ J - ;-T;/::i, er_ lJ. 1/~ I 0ATE , u.s. GOY[RMN[NT PRINTING o,,ict ~ 196-& 0,-1571845­ NASA 'Form 26 (Rev. Jan. 1963) NASA ROUTING SLIP CODE NAME (if 11«mary) ~ ACTION APPROVAi. 1. - \6 ,-,----£ CONCURRENCE FILE 2. J • (- i/--e_ INFORMATION INVESTIGATE AND ADVISE 3. .. NOTE AND FORWARD NOTE AND RETURN "· PU REQUEST IIECOMMENDATION 5. SEE ME SIGNATURE 6. REPLY FOR SIGNATURE OF: 7. REMARKS , ~~1" CT'µ:;:­ I r#- ft{ J' c_ ©4;~"'1­ frGJ' ~ z.s-­ 4. l I . FROM: I CODE : I NAME: IDATE : ~0_ C U.S. GOVI RNM ! NT PRINTI NG Off' IC[ : 19H o,-67'84 5 NASA f orm 26 ( Rev. Jan. 1963) (/ EX l 3 ROUTING S L IP , - N A E INIT I AL N. G. FOSTER R. L. cox w . A . EATON G. C . HR A B AL R . A. MOK E F. B. NEWMAN ' 0. SM IS TAD B . BROCKER ~ M. M~ ~ FILE -=> E I A RKS ~ C,,vL() z; \..__ ---- fLc.. - C..y 0~ AFT~NO<#,J Se-w,o~ <Dr ~ f. 9\& b c.,cn: I N-"• ~fl­ l,'-\Jrc, Belt 11 )'.,; or· ~;omc.;U1j r.r~ .Ulce t! ,r,.t ,Lovt', from looking at t e ai!'.' 0 10vfedge on Now t he air ~l ow was discovered q1lit a number o· y ea s ago when it wa s stud ·cd .om t e ground the hard way and, uh uh, by etometer (?)' ,1.nd l,y ( tri11.nguJ.;.i. t • on) , by tryi ng to determine h ow high i t wa s it was many yea r n h r oJ"<• on· 1,a<l ::om,1 j< <'>L how ll lg}1 tr,c air 1.i:low really was, ancl .ir1 a rnorm:11. wv "Wj.ll .lrnl.i1:1d,· l1t)W in u. rrv-.1.l,L<·r- f ccr·ond.o Glenn and -<! , ,. c..-....it.. ~Cu.rp ·nL(·r- wac ·· lil • Lo <:Lr:r-m i 11C: in u mutter [" seconds how jgh it w:.J,,s . /\ncl tl1<: r1 lie: d:i.<t v.wu.y w:i.tl, :,0 y :r.1.rs of' hard wor·k. Aga.in the e W"l.ls :L dis,·ov _ry 111a<'l.c Lh<..:.rc: hut LJ1c pc,in t WIL~: t;hat in a few ~ - conds from th . :L ht vant 11~ poj_ri L ynu cnn d > tl jolJ. Nuw with tl'ic air glow t hen .Looki ng 'U/~(' 011 LL so L of ul1 , wt· 'll . . . a band we never mean by LK't.nd ·t red. l' 1.•f't't:tly tlc~ :i. 1'.ncrl arnl J.jkc.: i n th· slide or som thing like tlio.L. . it :;urn l,j IIK::; a Ji t;t;l • J'11z:1.y l,ut t:.l1i s j s U1c air glow band and this C rp ·11t r nnd. li_y r·ock. ·t pn.::;~i11r.; L11r-()t.1/'.h the 'L.i.r elow. TJb th·I s is t he air glow dg on tl11tL we 1t1~v, _h .ard ttl,rn1t Ut:Ls mot'ni.ng uli it was used i n er- com1 rtion vlit}, l:h _ u:,,xtu.n) X'P'l"imc.mL.; ancl ' O on. Now 1 just wanted to 1: i vc y 0 11 ::om(: idcu. ol.' wl 1c-rc; we- :;l.1t11d. in 'lid/~l1tnes s . N w ub, before ~tr.Jwv--~ C.-lc1 111 w-:tn l.n l1;rvc· ,'.onr· ,i!'I' 1rl , 1 tl1v thD1l1'.ht W' L(.; Lo have him irlt imaJtl some And NASA head- And. nil , ull , ,John Glenn w,1 :~ ; '. i v,·11 1i:; <I ,,v,'r .-L 111 1.1.,-1,w , i 11l.('r· l', ·1 ·,·11cc l'i .1 l.1·1 · ve1·y slrnilar to thls t ype that was L1 1t· (;;,,xt,u;r. IJl 1 he , I re: , 11!.; , did not have ve y much time Belt l l 2 l,o use it, but l,c did uh have a cha nc to obs e .,_ve the air glow -rith the naked eye and he ·aw it edge on and he alle it, uh . name for it a t the mome t and . a nd really t he first time you se e a thing l ike that you don ' t know whether it haze or l uminou s sort ; i t d.oes look hazy . Uni'or·l.;unal~ ly t 11 . pr·er;s and other people kept tha t t e rm •·l si:;t, ,•,)11:,;i••L.in1-~ 01 · dus t. p11:r:-tlc•J(\~_; :i 1ci s o <,n . ReH-l ly, wbat Glenn saw wn. air· p;l w- tlt:'.t' on :t Jumillou$ l 1t_y·,.,·. Thex·,· may be :i littl -· d st thee, l..,.~ may tinv " omctl 1i Tl/'. to -::.u.y ul>oul: l.t1a t , l,ut, the pr.cdominate feature is j t ·i.s a ~elf J wninout: 11-y r . Now, C:.1.r:-:per,Lcr has mar. time to observe i.t . lle took t h int rfC'r:- nee filt •re• hack up with h j m and uh , he was 1:,.bl to tim a ::; La pas'"'inf( t h row~li U1c air f~low a s the star was setting 1..1.nd lie n ote i I_; n.rni t u Tl ·cl :Lt V y c-nre rull y . throur;h the air /'.low the u1)pt:r LI ; low r· and when :it cl .i :;appe1u· :c . From that careful LimJ 11e; inJ'ut·ma.Li un ore wt1:~ utile to µ.i n ,town Uie exact time of' the air 1-'.low. Ro1w:li.ly •)() ldJ.u111eL(•1·. /\nd Lili s -i.o wl 1:iL took mnn,y many years to do 1·1 ·,,m Ll 1(' p:ni111 1d l,_y l.1 ·.ir1.rw.1 i.Ju.'\.:I,)11 ( ·:·) w-J1 i <" I, i :~ ver ·y v ' r.y d.iffic:u.lt cau se you 1t<·vc1 · l<.11ow l11 n, l,u Lnk(· ,·,tr · u1 · 1.11111. Ln1nsml s s.i on W<i.S o ic;c1·vation. Uh, we had h ped J. iglrt 1vl1:i<- il is very diffi ult to see IH'1J.r- I.I1c :;1111 , c111 c trtl, yrn1 ,·itn ~;(' (' i t, c,1uy 1.ri 1('TI the s un :is , oh, some -- C l:r:lt ll v/1 • some: L:i.rnr: sec :.;.3tronauts might l.1c aolc t o sec t hti.t . UJ i, Coope was able to see the . light , and uh , White and McDivitt s aw the .. . light, ve ry wel l. Uh, the let 's see there ' s another point here ; well, w '11 go ba k t o t hat in a moment. The cason I 1,htnk have tt otl1e.r dcsji.'.ns I~ show what r:Fm be done . If we lw.vr: Urne Lu ehow whuL 1·1n1 be don<· lly r~xLem.l.int'. vi s 1..ia1 obscr vt"i.tions we ,,.,:111 do so. UJ1 , :,om 01 · Ll1 ·s • n. w r :_:u]ts , 11t1 that McDivitt and White we re able tu r or ar v ry . nLc r 'S Ung. Ul1 f irst of all, t hey saw a structure in the air gl ow a nd this is the fi rst time this i s eport ed. In one inst ance a uh, . i s seen some structure i n the ~i r elow that they 're looking edge on turns (whlte) .... This has never been obscrv d b fore . It is ver y hurd to observe t his with a rocket; you clan 't know when to fire the rocket to do t hat . They, they observed that. They obcer-vcd. unothcr intc.;rcct:Lnp, tli·ine; . They observed mcteo oi ng into Lh • 1:,.1r.th ' :: -'Li..mu:..;phcrr: dnwn ·1ic1ow Lb . 111 . I t .i :; the .first time a mcteo 1::: rcJ,ortccl f"r.um uh , uJ1 , npac l1y l.l!l ,rnL onui1L. And it. wa a very pecu­ 1.iar .xperjcnc:c l"or· i..11 rn I itru sure: b r·.-1use they saw the things below them go ng own .I.nto t.hc ca1 ·t;h ' n utmo::;pltcr(: . Th_y saw when they were over /\u t alia) they cuw u.J1 ave /1.ustru.lin they sn.w (southern) lights uh, Lli·i.,.. 1tg :I. n ir.; L11e l'it·:::I; time J tli inl< Ll1·i s i s reported by astronauts . . u lo L Ile l. l:c r Lllan I c 1L1ld. m1 uh . and l.l11..':;,• :i 1· , : : wl, l,1 · r1i1-'.l 1L l.i1n,· pl1L't1,,1m·1111. 'rh 1·c ut·c some inte e ting twilight pl 1c11<>n11'11u. I.I rd, i :~ d •i IT.i 1·1l.l L P ll i.H•rv,' 1· 1·um oc·kc t s or satel ites and they (Jh tllcy fow1d sunrises more Belt ll l;. spectacular than sunsets. I will try to explain that in a moment if I can. Uh, going to go back a moment t o what Cooper J uh, what Schirra uh, saw during a twilight right after sunset. He observed) uh, the planet Mars and he observed at twilight, the sun had just set, a very specta.­ cular array of colas, he describes them very carefully in the report, in the blue.: book, his 1iJ.ue book, and sumrna.rys blue book too. Uh, he d.escr-ibcd a ro.th r :Lnt est:lng blue hand that ' "' three blue bands; you r-an o.11 0chi c a. ' s hlues. Uh, . . . and he's able is true to d.o qu • t w 11, \./ ith bl1t ~s . He observe a da k blue, light blue, and a dark blu /\nd t le worc.l "light" i1-i 1:1. d ··_ fi ult word. When one says lj gh L on d.o sn ' l: know whether on m nns the lue was a lighter hue or 'j_t W:l:; brig! It J: • nut1 j t J it 1:ipp '1:1. ~ to be 1:1. iigr1t blue J and. one has to use these wo tls or what t hey stand. Anyway, we uh, from what these obse vations v re is (reportedly) on to a tape and is . (debriefing) and afterwards we are all very consistent. We had an order to try to construct this thing. The first time a ound it needed a little correction wr1en lkhirra saw 1.t; th s cond t me around he was somewhat, he was quit plca"ell w:i. Llt H . We di<ln ' t quit - know wl at this thing (band) was u. t; f irst· ,.,, 'r s Lill not too sure . Uh, we think it might be I ook:i 111-~ . [; j rn le.::;:.; tube 1>c'c:tuse th . tomorrow is 11:;c· Ll1<: :;11.111c l, ·r:!111.Lquv J\ r· t.:Lmi.ll1-; :Ls Carpenter Jiad stn.rted. Uh . we l,h lrik 11(1:;ci 1,.1.Y- ,m • :I.~-; l111,·c·rvj nt,~ Lil • O:lonisphcrc edge on. The ozonisphere , ,. appr·ox·im11.L ·ly ul1 , 011 , L'r •om 10 t l'.> kilometers hitsh up to rO, some- t.!1inr, .L:ik that . It (H.·ems to huv u 11lll.Ximum around 2:> or 20 kil omete s . 1rh, l1J1 ozone 1i8 you know, is very ve y absorbing in the ultraviolet, BE.:lt 11 r:: _.I in ·:wL c·tir11plcLc, ,dJsorl 1;.1.nl; lw·J.ow 3000 !"or s ol;ir radiation c.:oming '.rlu:, t'C :i.s anoL! 1e r· weak band o ozone i n the ed, y ll(Jw, t:tnd 1~, .c; 1 jn tbc • l,,,rnd uh, at, uh, dista nce 5000 . 6000 7000 and i J • ·1iy cl ock I ill absortion this way Ur r1 rt w- D.I< 1r1.om· l,11.nd p1 · ::orr, _(;h :ir1r'. .l .i kc· l;hn./., . And ·i (; clo :J s 11 tract , tt \./c · I.J, 1111 , L11,:n· i:: PrLly an 1·q, 1i vnlc·1d; oJ' ;2 rnjJirnc-tc1 ·s tir · ) n1il:iinc ·l,c-r:; :t l·,mcl~JJl 1er, , !.11:1.I; i:; 01 · 1·(1111 ·~:" , l,e:1 ·1.1.11: :c ' ,·,miplc l.1 , (r:orrt,j , 1111.1.t:i on ) o.L' th sw1­ J :i,g}1 l: . llow,,vc1 ·, wl 1e:n ,yu1r lo k at l.lrJs c:u.ge c,11 you ' re look:ing throueh :,o i I. <Loe,:: :11./.,tl-j,c:t out 11 lot uf' red 1 'L 1li('t '1' :: c; 1•r·l.:r.i11.J_y ,1, ]nl. ()I' l '(•d, yr • IJ.c, 1✓, 11nd 1•1 ·<·<:11 :in 1,/ 1C' lilu · sky any- iv: '.Y . /\11<1 1,_y ·1 l.l.1·:1.1 • 1, i 11,•~ i.11a1. ,111l. _y1•11 ,·11d_ up wi 1.11 nnnLl,l·t · kJ 11'1 of' blue . I 11 i'·w l. , 1.11 i :: i :: 1•111:i.l. i I, 1-1.·1:: . I~, . we 1·1·11 ' I, :-JLll'<' a rr l l.h('ll ycst.e:r'l.iay , \,/t • 1•,. l.:tkh11 •: , 1.J,,,y l 1wl l11·c•1r l,:tkin1,'. w-il. 11 Ll,cjr· 1'.11 1 ,:amc- ·a tllll u.li , ~n the , ·,l./l'1'i111'. ir, l,fi<- Lop 111" Ll r<' ~(• . Br:lt 11 ,·,mr i r·rncu. l,y p! ,oi;ol,';rapliy, motion p ie t trre photocraphy. The explanation I haven 't had a cha nce to I givr may or may not )C: i['.'.;l t , I don ' t know. 'l'l1 .r, ' n a l so 8. dust layer in here within J.nok u. t all the 1,ther p r·ohlcm •. l.l 1r· :.;j tuut.i.on d()wn by U11: wh :Ltc l i clit too well I ,lon ' L know, :it rtuty be v ·ry c·ompli -1-it d . ''o 11crc 's another situation where un oh.; r v1::1.Lion lnLer <·(in1':i rmed .Y• uJ-1, 1.1.notl,cr Get oi' ast1·onauts doing l fh , <:nupcr· mack •0,ume v r:y intcrcstinB ob- clown un t }1c <:l oud:.: und >-1.:i 1· p;low j::.; vr-r,y trarn;p,~r-cnt j n s olur !"adiation and Ll1at.. sort u !' t hin/~ so wh 11 you l o k ti.mm y ou ' r·e e;ettinc u.h, sort of r·je;rrt 11 hjrnl j(·, , you ' r··· /'. t t:in1~ an ·i nte ri sem·rrt of, of ligh t here and y ou :.;c ,·J011ds a rid 01 · ,·our~;c· Ll1 ' rcsL i s :J. l.'ucto1· <>L' t wo d :i ff ent . 'l'l 1i s i:.; i1,Le C" Lin1: 1eca1tsc the p1·1fpl,· rll)W I Li'(' 1-1111 ·l,:i 111'. ,,11 1.11, · po <·-v a1r.l I. :J.i. 1· 1~Juw expvt·.Lm-nt whi h wi l l be 1111 . 1,wl L. w1 • • ,. l<lild:: . 'I'1r ( · r ·, • ' : ; •L11• , I.I 1( • r • i 1 1 L< •1·1 · : ; I. i 111 '. I. i l, LI ( • l,.Y- 1~ I·~x l 1 II" l, . ln 1, w•i L:1 l trt mnon. ·r is i rJ I JJ 1, McDj v.il.t ,tnd \.fliitc· \./, :11 l':ine, i.l ' the @)on is out :Lt is jll w 11i 11n ti 111 '. Ll1c ca r t J1 ' :.,; Jen, :1.ntl p· r l ,u _p:__; the' il. w-as 1 J.ittle bri r✓,htc r l,J11 u 1 !.11 ' /J. ,i , . / '..11 ,w Wi l('J I l,l tl'/ '( ' j r• n11 rrl( )() fj t he ol·./1cr. wny ;.;,,rotmd. But 1,;h • l n Pact Lhc•y pref er Lhe Lit i n,1~ 1.1 1 J i)I(: o.r tl.c.:m11rk 11 t;:i.on :i s mud , mon: 1·1 rw 1:1.t night t han i n t I1c <I a _yt :lmc:. T'hc c!.lty-L:i1r1c 1ll.t.Y tl rc <" J owl si l,1J:·t1.:ion i ::: tih v er y dif· i cult 11. :;ccms U11J.t effec:t 01. they, they ct.lWttys l,!1 • c;low, I.i s i l, thr our:h t he· :;omc .I i,'-~hi.. ; ('dgc o n u.lr ~low. But you also a:ce looki~ through the a i r i s r;omine; oun ; you' r e l ooking so t of taking t wo pa sses rd r 1~- uw jn::;tc 1;t.d of one , l onp: b i g pa t h and y ou a r e getting and _y1, u. 1H ·<~ 11ul. /'. -·l;t I ll'. vc r _y mur·l1 l :i h