Three-day Gemini 11 mission set
Explore the source record for details and available documents.
Source record↗
SEARCH · Search NASA
Results for “GEMINI 11 MISSION”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Effects of radiation during space flight on microorganisms and plants on the Biosatellite II and Gemini XI missions.
Radiation effects on microorganisms and plants during space flight on Biosatellite 2 and Gemini 11 missions
De Serres, F. J.↗
Experiment D016: Power tool evaluation
Power tool evaluation was not attempted during the Gemini 11 mission because of the premature termination of the on-umbilical extravehicular activity (EVA). The experiment had been scheduled for the Gemini 8 mission, but early mission termination prevented completion of the experiment. However, the objective, equipment description, and experimental precedures are described briefly in this report.
Ettredge, V. L.↗
Experiment S009: Nuclear Emulsion
The first exposure on a spacecraft of a nuclear emulsion apparatus designed to collect 1000 high quality tracks of heavy nuclei under a negligible thickness of matter (0.07 g/sq cm) is described. The cosmic ray detector consisted of a stack of nuclear emulsions that were designed to register at least 400 heavy nuclei tracks for each 10 hours of useful exposure. The spacecraft had to be oriented in a heads-up attitude during the 10-hour period to eliminate atmospheric albedo particles. The results are as follows: (1) a definite odd-even effect, with low abundances for elements of atomic number 7, 9, and 11; (2) a ratio O/C approximately 0.9; (3) Ne/C, Mg/C, and Si/C ratios between 0.2 and 0.3; (4) an abundance gap in the region 15 less than or equal to Z less than or equal to 19; and (5) a ratio (20 less than or equal to Z less than or equal to 28)/C 0.2, with a large concentration at Z = 26. These results are indicative that successful exposures of nuclear emulsions were obtained on the Gemini 11 mission.
Odell, F. W.↗
Summary analysis of the Gemini entry aerodynamics
The aerodynamic data that were derived in 1967 from the analysis of flight-generated data for the Gemini entry module are presented. These data represent the aerodynamic characteristics exhibited by the vehicle during the entry portion of Gemini 2, 3, 5, 8, 10, 11, and 12 missions. For the Gemini, 5, 8, 10, 11, and 12 missions, the flight-generated lift-to-drag ratios and corresponding angles of attack are compared with the wind tunnel data. These comparisons show that the flight generated lift-to-drag ratios are consistently lower than were anticipated from the tunnel data. Numerous data uncertainties are cited that provide an insight into the problems that are related to an analysis of flight data developed from instrumentation systems, the primary functions of which are other than the evaluation of flight aerodynamic performance.
Whitnah, A. M.↗
Ultraviolet calibration procedures for Gemini experiment M-407
Ultraviolet calibration procedures for determining spectral reflectivity of lunar surface for use in Gemini experiments
LUNAR SURFACE↗
Science experiments summary
Science experiments conducted during Gemini 10, 11 and 12 missions
Foster, W. B.↗
Space food systems - Mercury through Apollo.
Major achievements which characterized the development of food systems used by American astronauts in manned space flight are reviewed throughout a period spanning the Mercury, Gemini, and Apollo programs up to and including the Apollo 11 lunar landing mission. Lists of food types are accompanied by information on packaging, storage, preparation, consumption, and quality of particular products. Experience gained from development efforts for the Manned Orbiting Laboratory Program is also discussed.
Roth, N. G.↗
Gemini experiment S026
The results of the reduction and analysis of data obtained from the S026 experiment from Gemini 10 and 11 flights are presented. The electron and ion sensors were continuously operative throughout both missions from shroud removal (about 6 minutes after Agena liftoff to power-down conditions one week later). Data on ion and electron currents, electron temperature, and vehicle potential were obtained at a sample rate of 32 times per second on positive ions for each of two ion sensors and once every 1.067 seconds for the electron sensor. Only the data reduction of the Gemini plasma wake measurements comprising roughly twenty minutes of data for six maneuvers programed for wake measurements are considered. The intermediate depletion zone, between 1 and 10 vehicle radii downstream from the object, is emphasized. The smallest characteristic radius of interest is 1.34 feet and the largest is 5 feet. This implies a separation span extending from approximately 1.5 feet at the closest approach to at least 50 feet into the far field.
Medved, D. B.↗
Gemini Program Mission Report: Gemini IV
The second manned mission of the Gemini Program, Gemini IV, was launched from Complex 19 at Cape Kennedy, Florida, at 10:16 a.m. e.s.t. on June 3, 1965. The mission was successfully concluded on June 7, 1965, with the recovery of the spacecraft by the prime recovery ship, the aircraft carrier U.S.S. Wasp, at 27 deg 44' N. latitude, 74 deg 11' W. longitude at 2:28 p.m. e.s.t. This manned long-duration flight was accomplished 10 weeks after the three-orbit manned flight which qualified the Gemini spacecraft and systems for orbital flight. The spacecraft was manned by Astronaut James A. McDivitt, command pilot, and Astronaut Edward H. White II, pilot. The flight crew completed the 4-day mission in excellent physical condition, and demonstrated full control of the spacecraft and competent management of all aspects of the mission.
Source record↗
Ablators - From Apollo to Future Missions to Moon, Mars and Beyond
Apollo was designed to carry astronauts safely back from the Moon at return speeds exceeding 11 km/s and requireddevelopment of a new ablative thermal protection system (TPS) to protect the capsule from entry heating. Mercuryand Gemini, that preceded Apollo, were focused on Earth orbiting system demonstration and lessons learned fromthem were used in Apollo. The ablative material and associated system development for Lunar return conditionsrequired considerable ground and flight testing. Mars Viking Lander missions required a new lighter weight ablatoras entry heating was benign compared to Apollo. Pioneer-Venus and Galileo Probe missions required a new and morecapable ablator than Apollo. After two decades, Mars Pathfinder followed by Mars Exploration Rover missions,smaller than Viking but more demanding, were able to use Viking ablative TPS. At the same time, advances in manufacturing and materials technology led to development of innovative lightweight ablators. These new ablators enabled Stardust and Genesis Sample Return Missions. Around the turn of this century, NASA decided on a scaled-upversion of the Apollo capsule for human exploration of Moon and Mars and the ablative heat shield to protect the CrewExploration Vehicle ended up being the Apollo ablative TPS. The Artemis 1 mission is currently fitted with tiledsystem, different than Orion EFT-1 but with the Apollo ablative material as a result of lessons learned. NASA iscurrently planning on sample return missions from Mars, and this will require robust ablative TPS that can providehigher reliability than any other past mission. There are still unexplored high scientific value destinations in the solarsystem. In situ exploration of Uranus, Neptune, Saturn and sample return missions with return speed much higher thanStardust will require ablators capable of withstanding extreme entry that are also efficient. New ablative TPS havebeen developed in anticipation of these future missions. This paper is intended to tell the story of these ablators,illustrated through examples. We see the use of flight proven ablators was sometimes a risky proposition and newablators perceived to be higher risk have proved otherwise. The history of ablators illustrates the challenges eachmission had to address, either through the use of flight proven or new ablative TPS, to be successful.
Venkatapathy, Ethiraj↗
The Challenges of Developing a Food System for a Mars Mission
A viewgraph describing the food system that NASA is developing for Manned Mars Missions is shown. The topics include: 1) The President's Vision for U.S. Space Exploration -January 14, 2004; 2) Introducing Orion (and Ares); 3) Mercury (1961-1963); 4) Gemini (1965-1966); 5) Apollo (1968-1972); 6) Skylab (1973-1974); 7) Shuttle/Mir (1995-1998); 8) Shuttle (1981-present) International Space Station (2000-present); 9) NASA Stored Food System; 10) Advanced Food Technology; 11) Orion Missions; 12) Orion Challenges; 13) Food Packaging; 14) Mars Mission Assumptions; 15) Planetary Food System Selected Crops; 16) Food Processing Equipment Constraints; 17) Crew Involvement Constraints; 18) Advanced Food Technology Integration; 19) Research Highlights Internal; and 20) Research Highlights External.
Perchonok, Michele↗
Radiation and zero-gravity effects on human leukocytes and Neurospora crassa
The two parts of this experiment have resulted in proof that neither orbital space flight nor any of the stresses connected with it produced significant, unpredicted genetic damage, at least insofar as chromosomal-aberration production is a valid measure of this general type of effect. Furthermore, the Gemini 11 results lead to the conclusion that no synergistic effect exists between radiation and factors that are associated with space flight. No significant difference was found between dose-effect curves for survival or mutation induction of the inflight and ground-based samples irradiated on filters. Thus, like the blood experiment, this part of the experiment failed to result in data that were appropriate for confirmation of the apparent synergism that was observed in the Gemini 3 blood experiment. Also, the Nuerospora crassa experiment provided conclusive data that there is no difference in the genetic effects of irradiation during space flight and the genetic effects obtained in ground-based experiments. Both the Gemini 11 blood experiment and the Neurospora crassa experiment thus have failed to result in data confirmatory of the apparent synergism observed on the Gemini 3 mission.
Bender, M. A.↗
Extravehicular Activity (EVA) 101: Constellation EVA Systems
A viewgraph presentation on Extravehicular Activity (EVA) Systems is shown. The topics include: 1) Why do we need space suits? 2) Protection From the Environment; 3) Primary Life Support System (PLSS); 4) Thermal Control; 5) Communications; 6) Helmet and Extravehicular Visor Assy; 7) Hard Upper Torso (HUT) and Arm Assy; 8) Display and Controls Module (DCM); 9) Gloves; 10) Lower Torso Assembly (LTA); 11) What Size Do You Need?; 12) Boot and Sizing Insert; 13) Boot Heel Clip and Foot Restraint; 14) Advanced and Crew Escape Suit; 15) Nominal & Off-Nominal Landing; 16) Gemini Program (mid-1960s); 17) Apollo EVA on Service Module; 18) A Bold Vision for Space Exploration, Authorized by Congress; 19) EVA System Missions; 20) Configurations; 21) Reduced Gravity Program; and 22) Other Opportunities.
Jordan, Nicole C.↗
Blood volume changes
Analysis of radionuclide volume determinations made for the crewmembers of selected Gemini and Apollo missions showed that orbital spaceflight has an effect on red cell mass. Because the methods and the protocol developed for earlier flights were used for the crews of the three Skylab missions, direct comparisons are possible. After each Skylab mission, decreases were found in crewmembers' red cell masses. The mean red cell mass decrease of 11 percent or 232 milliliters was approximately equal to the 10 percent mean red cell mass decrease of the Apollo 14 to 17 crewmembers. The red cell mass drop was greatest and the postrecovery reticulocyte response least for crewmembers of the 28-day Skylab 2 mission. Analyses of data from the red cell mass determinations indicate that the red cell mass drops occurred in the first 30 days of flight and that a gradual recovery of the red cell mass deficits began approximately 60 days after launch. The beginning of red cell mass regeneration during the Skylab 4 flight may explain the higher postmission reticulocyte counts.
Johnson, P. C.↗
Apollo experience report: Real-time auxiliary computing facility development
The Apollo real time auxiliary computing function and facility were an extension of the facility used during the Gemini Program. The facility was expanded to include support of all areas of flight control, and computer programs were developed for mission and mission-simulation support. The scope of the function was expanded to include prime mission support functions in addition to engineering evaluations, and the facility became a mandatory mission support facility. The facility functioned as a full scale mission support activity until after the first manned lunar landing mission. After the Apollo 11 mission, the function and facility gradually reverted to a nonmandatory, offline, on-call operation because the real time program flexibility was increased and verified sufficiently to eliminate the need for redundant computations. The evaluation of the facility and function and recommendations for future programs are discussed in this report.
Allday, C. E.↗
Apollo 7 to 11 - Medical Concerns and Results
The goal of the Apollo Program is to land men on the moon and safely return them to earth. The medical task thus outlined required confirmation of the Gemini findings and definition and solution of any problems encountered in the four Apollo flights prior to the Apollo 11 lunar landing. The medical concerns included the following: 1. The effect of decreased red blood cell mass and decreased exercise capacity and of cardiovascular de conditioning on the ability of the crew to do lunar-surface activity; 2. The capability to work effectively in one-sixth the force of gravity and the energy cost of such work; 3. The ability to get adequate rest and sleep in flight and on the lunar surface; 4. The prevention of preflight, inflight, and post-flight illness by proper preventive medicine; 5. The possible development of motion sickness of vestibular origin; 6. The conduct of a post-flight quarantine of crew and lunar samples. The results of the Apollo 7 to 11 missions, demonstrating the ability of man to handle this difficult task and the environment successfully, are discussed in detail and are related to the future of manned flight.
Berry, C. A.↗