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  • Other Sources  (199)
  • ASTRONAUTICS (GENERAL)  (199)
  • 1985-1989  (199)
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  • 1986  (199)
  • 1
    Publication Date: 2006-06-12
    Description: Selected hints derived from 5 years experience in experiment hardware design, hardware qualification, safety provisions, experiment testing, payload integration, flight preparation, battery transport, and postmission checkout are presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 255-265
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  • 2
    Publication Date: 2006-06-12
    Description: At the beginning of the Get-Away Special (GAS) flight program, the GAS Project flew a Flight Verification Payload on STS-3 to make measurements of the vibrations, acoustic and magnetic environments of the canister, and to obtain thermal profiles of internal and external components of the GAS system. Two types of GAS canister end caps (insulated end cap and silverized teflon covered end cap) were used on the two flights (STS-7 and STS-8) so that a direct comparison of the thermal performance was obtained. These observations were compared with a simple thermal model of the instrument in the GAS canister in order to assess whether such simple models can be useful to experimenters in predicting the thermal response of their payloads.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: The 1985 Get Away Special Experimenter's Symposium; p 151-164
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  • 3
    Publication Date: 2006-06-12
    Description: Project MAUS is a part of the German material sciences program and provides autonomous payloads for the Space Shuttle. These payloads are housed in canisters which are identical with those of NASA's Get Away Special program. The main components of the hardware are: a standard system consisting of power supply, experiment control, data acquisition and the experiment modules containing experiment specific hardware. So far, three MAUS modules with experiments from the area of material sciences have been flown as GAS payloads. They deal with the effects of reduced sedimentation, convection phenomena caused by temperature gradients and the behavior of dispersed particles ahead of a solid/liquid interface.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 101-108
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  • 4
    Publication Date: 2006-06-12
    Description: The results of the Get Away Special (GAS) Arts-Science payload G-38, processed in orbit on board the Space Shuttle Challenger during mission 41-G STS 17, October 5 to 13, l984 are explained. The payload G-38 was created as a unified Arts-Science payload that simultaneously explored the process of vapor deposition in the vacuum and weightlessness of the shuttle environment and created a series of space sculptures utilizing this process. The purpose of the experiment was to test the sputter deposition process in space and to create five subtle spherical sculptures with metallic coatings of gold, silver, platinum and chrome.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 267-273
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  • 5
    Publication Date: 2006-06-12
    Description: Zeolites are hydrated, crystalline aluminosilicates with alkali and alkaling earth metals substituted into cation vacancies. Typically zeolite crystals are 3 to 8 microns. Larger cyrstals are desirable. Large zeolite crystals were produced (100 to 200 microns); however, they have taken restrictively long times to grow. It was proposed if the rate of nucleation or in some other way the number of nuclei can be lowered, fewer, larger crystals will be formed. The microgravity environment of space may provide an ideal condition to achieve rapid growth of large zeolite crystals. The objective of the project is to establish if large zeolite crystals can be formed rapidly in space.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 133-140
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  • 6
    Publication Date: 2006-06-12
    Description: The current materials research being done in microgravity solidification and the future experimentation planned onboard a space shuttle mission is reported. The Department of Engineering Mechanics at the USAF Academy is developing a microgravity furnace to be used on board the space shuttle. The microgravity furnace will be used to conduct materials research dealing with such topics as immiscible alloy solidification. The purpose behind this research project is three-fold: to develop a simple, inexpensive, and easy to use furnace to conduct space materials research, to conduct a solidification experiment on a lead-zinc alloy in space that macrosegregates due to gravity, and to provide a research mechanism for students to get involved with space materials research.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 85-86
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  • 7
    Publication Date: 2006-06-12
    Description: A sealed window assembly for the Get Away Special (GAS) payloads was developed from a synthetic fused silica. The details of the design and development of this window assembley are given.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 275-284
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  • 8
    Publication Date: 2006-06-12
    Description: Four hours, fourteen minutes and forty-two seconds after the space shuttle, Challenger, was launched on mission 51B, a small satellite was ejected into independent orbit from a Getaway Special canister. This event was an exciting milestone in a project conceived over seven years ago. It is hoped that the story of NUSAT (Northern Utah SATellite) will be an inspiration for other experimentors to exploit this new service of the Getaway Special program. The purpose and history of the project, the NUSAT spacecraft, the ground station and its operation, and some future directions envisioned by the participants are described.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 87-99
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  • 9
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    Publication Date: 2006-06-12
    Description: The highlights of the Utah State University's participation in the space program are listed. Proposed experiments include: a study of the velocity of a bubble in water under the influence of a temperature gradient; reflight of an experiment on surface tension driven convective flow; surface waves in zero-G; crystallization in zero-G (vapor phase and liquid phase); bio gas generation; and penicillum growth; study of undamped oscillations in a vacuum and zero-G. The effect that spinoffs have had on the Utah State University were discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 219-230
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  • 10
    Publication Date: 2006-06-12
    Description: The Mitre Corporation of Bedford Mass. and the Worcester Polytechnic Institute are developing several experiments for a future Shuttle flight. Several design practices for the development of the electrical equipment for the flight hardware have been standardized. Some of the ideas are presented, not as hard and fast rules but rather in the interest of stimulating discussions for sharing such ideas.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 109-116
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  • 11
    Publication Date: 2006-06-11
    Description: Polls were taken at the Project Explorer meetings regarding flying without the radio experiment transmitting. The radio downlinks require extra coordination and are sensitive to certain payloads. The poll results were unanimous. The radio downlinks are vital in providing data on the health and status of the total experiments package, in real time, during the flight. The amateur radio operators, prepared to receive the downlinks and OSCAR-10 relays, revealed that there was enormous interest throughout the world, to participate. This sets the stage for the reflight opportunities which the GAS program has provided. Major activities, pertinent to the STS-41G flight preparations by the GAS #007 team and support group, are listed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: The 1985 Get Away Special Experimenter's Symposium; p 73-80
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  • 12
    Publication Date: 2006-06-11
    Description: Trying to get a project started? Well, since the introduction of the Get Away Special Program, there have been 451 reservations placed by people who, just like yourself, are eager to send a small payload into space; and yet only 33 of them have actually succeeded. Even more staggering, many of those who have flown have done so more than once; meaning that less than 10% of all GAS users have actually sent something into space. Some of the problems that face GAS users are approached and it is hoped that they will be helpful, especially to those new to the program. Some of the subject areas include selecting a project, and payload management.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 65-72
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  • 13
    Publication Date: 2006-06-11
    Description: There are four separate experiments integrated into the single payload of G-285 which are supported by internal payload power, thermal environment control, command and data handling facilities and structural subsystems. The four experiments contained in this payload are: a single spectrometer performing two experiments - one to study night time shuttle glow phenomena in the ultraviolet and the other to observe NO2 concentrations over equatorial latitudes in the day; a fluids management experiment using centrifugation for particle/liquid/vapor separation; and an experiment using Phycomyces fungi to study the gravireceptor mechanism theory. The experiments are supported by a microprocessor, data storage devices, power and thermal control subsystems.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 49-56
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  • 14
    Publication Date: 2006-06-11
    Description: The experiment is to study polymeric membranes. Presently, semipermeable membranes are being manufactured from several different kinds of polymers all over the world and specific applications have been identified in fluid separation processes such as reverse osmosis, ultrafiltration and electrodialysis. Although, the ultrastructure of asymmetric and composite membranes have been under intensive study, still there are many questions about the factors affecting this structure and their degree of correlation. Nevertheless, there is indication that the entire morphological structure of polymeric membranes could be affected by the difference in specific gravity between the cast solution and the coagulation liquid normally used in the membranes preparation process. The casting of semipermeable membranes in space might help to identify the effect of gravity upon the structure of these membranes. It is important to recognize that the casting process involves changes of state and that in a microgravity environment, there will be a reduction on buoyancy-driven natural convection and density gradients.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 41-44
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  • 15
    Publication Date: 2006-06-11
    Description: The Directional Electrostatic Accretion Process (DEAP) is described with respect to both the physical process and its application to manufacturing in space. This high precision portable manufacturing method will revolutionize current practices in manufacturing and repair of spacecraft and space structures. The cost effectiveness of this process will be invaluable to future space manufacturing projects.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 19-24
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  • 16
    Publication Date: 2006-06-11
    Description: The experience has shown that a GAS experiment can be a valuable education tool. It can return results far in excess of the resources invested. The best estimate on the financial investment per student indicates that it is somewhat less than the cost of a school lunch. That's a bargain in a time when educational bargains are hard to come by. To reach this goal means reaching far beyond the students who could possibly design or fly experiments in a single canister. The greatest value of CAN DO is that it serves as a catalyst and inspiration for other activities. To not reach out would have turned it into an overblown, expensive science fair project for a few exceptional students. To fully exploit the benefit of a GAS canister, you should build on a well established science enrichment program. As part of a comprehensive plan, a GAS can be one of the most motivating educational tools available.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 11-17
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  • 17
    Publication Date: 2006-02-14
    Description: The latest fluid dynamic and material science experiments in the microgravity environment have emphasized the importance of the residual gravity level and of the g-jitter on fluid physics phenomena. The tethered elevator presents the possibility of providing variable g-levels (both steady and g-jitter) around a very low steady g-level (that can be realized when the elevator is near the center of mass of the space station-tether complex). When positioning a variable periodic oscillation to the payload a clean g-jitter disturbance can be obtained that would not be otherwise obtainable by other systems. These two possibilities make the elevator a facility to help resolve a number of still open questions that are preventing wider utilization of the space environment in the microgravity area.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 137-147
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  • 18
    Publication Date: 2006-06-12
    Description: The Project Explorer payload represents the first attempt at broadcasting digitized voice signals via a Space Shuttle flight on amateur radio frequencies. These amateur ham-radio frequencies will be transmitting real time data while the experiments are operating. Experiments 1, 2, and 3 represent the work of students ranging from materials processing to the science of biology. Experiment 1 will study the solidification of two hypereutectic alloys, lead-antimony and aluminum-copper. Experiment 2 will investigate the examination and growth of radish seeds in space. Experiment 3 will examine the electrochemical growth process of potassium tetrocyonoplatinate hydrate crystals and Experiment 4 involves amateur radio transmissions, monitoring and support of the entire Get Away Special (GAS) 007 payload.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Goddard Space Flight Center The 1985 Get Away Special Experimenter's Symposium; p 125-131
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  • 19
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    Publication Date: 2011-08-19
    Description: Using the Spacewatch Camera, a search was conducted for objects in geosynchronous earth orbit. The system is equipped with a CCD camera cooled with dry ice; the image scale is 1.344 arcsec/pixel. The telescope drive was off so that during integrations the stars were trailed while geostationary objects appeared as round images. The technique should detect geostationary objects to a limiting apparent visual magnitude of 19. A sky area of 8.8 square degrees was searched for geostationary objects while geosynchronous debris passing through was 16.4 square degrees. Ten objects were found of which seven are probably geostationary satellites having apparent visual magnitudes brighter than 13.1. Three objects having magnitudes equal to or fainter than 13.7 showed motion in the north-south direction. The absence of fainter stationary objects suggests that a gap in debris size exists between satellites and particles having diameters in the millimeter range.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Icarus (ISSN 0019-1035); 68; 412-417
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  • 20
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    Publication Date: 2011-08-19
    Description: Various JPL space missions are discussed. Consideration is given to the objectives and capabilities of the Hubble Telescope, the SIR-B, the Magellan spacecraft, and the Mars Observer missions. The planned Topex and Comet Rendezvous Asteroid Flyby mission are described. The development of an autonomous surface roving vehicle to collect samples on Mars is proposed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Spaceflight (ISSN 0038-6340); 28; 207-210
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  • 21
    Publication Date: 2011-08-19
    Description: NASA's Comet Rendezvous Asteroid Flyby (CRAF) mission to P/Tempel 2 is described with attention given to CRAF spacecraft design. Infrared/visible spectrometers, dust counters, magnetometers, and plasma-wave analyzers are an integral part of the CRAF payload. CRAF's subsystems consist of the following: (1) a structure subsystem, (2) a temperature control subsystem, (3) a propulsion module subsystem, (4) an attitude control subsystem, (5) a command and data subsystem, (6) a radio frequency subsystem, and (7) a power and pyrotechnics subsystem. It is concluded that the CRAF mission will enable the first detailed study of the cometary nucleus.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: (ISSN 0007-084X); 39; 263-272
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  • 22
    Publication Date: 2011-08-19
    Description: The Infrared Astronomical Satellite (IRAS) was launched in 1983 for the purpose of surveying the sky in a broad area of the infrared portion of the spectrum. While the primary objects of interest of IRAS were stars and nebulae, other types of space-related objects could also be observed. These include comets, asteroids, and earth orbiting objects. Theoretical analysis indicates that IRAS could observe objects with a diameter of 1-mm at a range of 100-km and objects with a diameter of 1-cm at a range of 1000-km, while current ground-based observations of particles in low earth orbit are limited to objects larger than 1-cm. Thus, these data offer a unique opportunity to ascertain the number density of particles below the present observable limit. At NASA/JSC a preliminary analysis of an IRAS data set has been performed to detect and describe this population, and the results of this study are presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Advances in Space Research (ISSN 0273-1177); 6; 7, 19
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  • 23
    Publication Date: 2011-08-19
    Description: Commerce Lab is conceived as an adjunct to the National Space Transportation System (NSTS) by providing a focal point for commercial missions which could utilize existing NSTS carrier and resource capabilities for on-orbit experimentation in the microgravity sciences. In this context, the Commerce Lab provides an enabling facility and test bed for commercial flight opportunities. Commerce Lab program activities to date have focused on mission planning for private sector involvement in the space program to facilitate the commercial exploitation of the microgravity environment for materials processing research and development. It is expected that Commerce Lab will provide a logical transition between currently planned NSTS missions and future microgravity science and commercial R&D missions centered around the Space Station. The present study identifies candidate Commerce Lab flight experiments and their development status and projects a mission traffic model that can be used in commercial mission planning.
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  • 24
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    Publication Date: 2011-08-19
    Description: The success of Spacelab 2 is examined critically. Particular attention is given to the solar telescopes which were mounted on the instrument pointing system; these were designed to study solar irradiance, coronal helium, and exploding granules. Plasma experiments and the cosmic ray experiment (the 'Chicago Egg') are also described.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Sky and Telescope (ISSN 0037-6604); 72; 438-445
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  • 25
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    Publication Date: 2011-08-19
    Description: The characteristics of the Comet Halley spacecraft 'fleet' (VEGA 1 and VEGA 2, Giotto, Suisei, and Sakigake) are presented. The major aims of these missions were (1) to discover and characterize the nucleus, (2) to characterize the atmosphere and ionosphere, (3) to characterize the dust, and (4) to characterize the nature of the large-scale comet-solar wind interaction. While the VEGA and Giotto missions were designed to study all four areas, Suisei addressed the second and fourth. Sakigake was designed to study the solar wind conditions upstream of the comet. It is noted that NASA's Deep Space Network played an important role in spacecraft tracking.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: EOS (ISSN 0096-3941); 67; 478-481
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  • 26
    Publication Date: 2011-08-19
    Description: Changes made by radio control from the ground in the Voyager 2 spacecraft as it approached Uranus are described. Reduced power required that subsystems and heaters had to be switched on and off in carefully synchronized fashion. Low light levels required increased exposure times, so the jiggling of the spacecraft had to be minimized. Coding changes were made and image data were compressed to cope with the reduced bit rate at larger distances. Successful efforts to cope with failures in the primary radio receiver and in the computer instructions for image compression are described, as are changes made on the ground in the spacecraft navigation.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Scientific American (ISSN 0036-8733); 255; 36-45
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  • 27
    Publication Date: 2011-08-19
    Description: This paper describes the scientific and technical background and prospects for the Space Infrared Telescope Facility (SIRTF). SIRTF is a cryogenically-cooled, one meter-class space telescope which will be operated by NASA as an observatory for infrared astronomy, in the mid-1990's. SIRTF will provide detailed studies of even the faintest IRAS sources, important new capabilities for the study of known astrophysical phenomena, and the potential to make new and unexpected discoveries about the nature of the universe. The long-life SIRTF mission has undergone intensive review by the SIRTF Science Working Group, which was selected in mid-1984. This paper presents the outcome of that review process and describes the SIRTF program as it is now envisioned. Particular emphasis will be placed on the choice of orbit for SIRTF, the SIRTF scientific performance requirements, and the baseline design concept for the SIRTF facility and mission.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 28
    Publication Date: 2011-08-19
    Description: The need for spacecraft bus technology advances in order to develop the spacecraft for the 21st century is discussed. Consideration is given to the power and electric propulsion systems for mass-limited satellites such as LEO and GEO. The goal of spacecraft bus technology programs is to design a cost-effective spacecraft which operates well in the satellite environment. The possibility of collaboration between government and industry is examined.
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  • 29
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    Publication Date: 2011-08-19
    Description: The Ulysses mission to explore the heliosphere within a few astronomical units of the sun over the full range of heliographic latitudes, thereby providing the first characterization of the uncharted third heliospheric dimension, is discussed. The scientific objectives of the mission are reviewed, and the nine flight experiments which make up the spacecraft payload are summarized. The Ulysses trajectory and mission timeline are described, as are the spacecraft itself and the mission operations. The timing of the mission with the solar cycle is discussed.
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  • 30
    Publication Date: 2011-08-19
    Description: Spacelab 3 provided the platform for the first extensive application of holography in space. Holograms of excellent quality were recorded during the flight, providing information on the solution growth of triglycine sulfate crystals under microgravity conditions. The suppression of convection and the development of a symmetric concentration-depletion region around each crystal were clearly shown. Crystal growth was governed by diffusion mass transport across the depletion region. The successful performance of the holographic unit has prompted NASA to schedule a slightly modified version for reflight on IML-1; opportunities now exist for other investigators to use this facility.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Optics Letters (ISSN 0146-9592); 11; 407-409
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  • 31
    Publication Date: 2011-08-19
    Description: The use of the proposed Space Station for technological experimentation is discussed. The general objectives and capabilities of the Station and the status of planning are reviewed; the external and internal environmental conditions at the 500-km 28.5-deg-inclination Station orbit are described; and six conceptual Technology Development Missions designed by NASA and included in the Mission Requirements Data Base are briefly characterized and illustrated with drawings. The missions considered concern spacecraft-materials performance, solar dynamic power, data transfer and processing microelectronics, long-term cryogenic-fluid storage, active-optics technology, and cryogenic-propellant transfer, storage, and reliquefaction.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Journal of Vacuum Science and Technology A (ISSN 0734-2101); 4; 281-285
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  • 32
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    Publication Date: 2011-08-19
    Description: Preliminary results of physical experiments carried out during the Spacelab 2 Shuttle mission are summarized. Attention is given to experiments in the fields of plasma dynamics; solar physics; high-energy astrophysics; and astronomy. Plasma experiments included an ejectable plasma diagnosics package and measurements of the passive charging of the Shuttle vehicle in the surrounding space plasma. The solar physics instrument package consisted of a solar spectral irradiance monitor; a solar optical universal polarimeter (SOUP); and a solar helium abundance high-resolution telescope and spectrograph (HRTS). Astronomical observations were performed using a scanning infrared telescope (IRT) which consisted of a highly baffled herschelian telescope and 10 detectors covering wavelengths from 2 to 120 microns. Cosmic-ray nuclei were detected and analyzed using gas Cerenkov counters and a transition radiation detector. Addition experiments included a thin film fluid dynamics payload and analysis of blood samples taken from the mission specialists. Complete data records from the experiments have now been distributed for an analysis period which will take at least a year. A table listing the Spacelab 2 experiments and their principal investigators is provided.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Nature (ISSN 0028-0836); 319; 540-542
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  • 33
    Publication Date: 2011-08-19
    Description: The experimental observation of the behavior of acoustically rotated free drops in the microgravity environment of low earth orbit has yielded the first data which meet the restrictions of existing theoretical treatments. Rotating drops displayed both 'axisymmetric' and 'two-lobed' shapes in the presence and absence of applied torques. Their dimensions and general development confirm the existence of the distinct shape families and the bifurcation point between them. The data also indicate that the secular instability in the axisymmetric family occurs at a lower rotation velocity than predicted
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Physical Review Letters (ISSN 0031-9007); 56; 452-455
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  • 34
    Publication Date: 2011-08-19
    Description: The objective of the Ulysses project is to explore the heliosphere within 1-2 AU of the sun at high latitudes. The spacecraft for the mission is spin stabilized, contains a large diameter parabolic high gain antenna, a Radioisotope Thermoelectric Generator (RTG), and a 5.5 m radial boom. The spacecraft instruments used to measure the properties of the solar corona, the solar wind, the sun-wind interface, the heliospheric magnetic field, solar and nonsolar cosmic rays, solar radio bursts, plasma waves, and the interstellar/interplanetary neutral gas and dust are described. The roles of various organizations involved in the management of the Ulysses project are discussed. Particular attention is given to the composition and capabilities of the RTG, and the transmission of the spacecraft telemetry data.
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  • 35
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    Publication Date: 2011-08-19
    Description: The Galileo mission to Jupiter will make the first direct sampling of the atmosphere of the solar system's largest planet and will spend as long as 22 months orbiting Jupiter. Launch date, trajectory, Jupiter arrival, and number of orbits of that planet depend on NASA's flight schedules since destruction of the Space Shuttle Challenger on Jan. 28, 1986. Galileo's responses to the schedule changes caused by the Challenger explosion are discussed.
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  • 36
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    Publication Date: 2011-08-19
    Description: An overview of manned space flight is given. This describes the key goals and achievements of the space programs of the United States and of the Soviet Union. The importance of the 'Man' in manned space flight is emphasized. Human factors are shown to have played an ever increasing role in the design of manned spacecraft.
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  • 37
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    Publication Date: 2011-08-19
    Description: The engineers of the Voyager 2 mission to Uranus had to deal with dwindling consumables, navigational challenges unique to the Uranian system, low light-level imaging, increasing communications problems, and failed equipment onboard the spacecraft, each of which could affect the success of the mission. The techniques for coping with each of these factors are discussed in detail. For instance, steadying of the spacecraft, achieved by cancelling the momentum change imparted to it by high-rate operations of the digital tape recorder, enhanced the data quality from several instruments, particularly the cameras. A careful power management scheme made it possible to conduct a successful radio occultation experiment which yielded detailed information on the Uranian atmospheric structure, including temperature and composition. A unique picture of the back-lit ring system was obtained.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 38
    Publication Date: 2011-08-19
    Description: The management of the Ulysses project, a probe which will fly a solar polar orbit, is described. The 5-yr mission will feature a flyby of Jupiter to deflect the spacecraft into a high-inclination orbit. Data on the solar corona, solar wind, the sun-wind interface, the heliospheric magnetic field, solar and nonsolar cosmic rays, etc., will be gathered as a function of the solar latitude. NASA will track and control the probe with the Deep Space Network. JPL provides project management for NASA while the Directorate of Scientific Programs performs ESA management functions. The DOE will provide a radioisotope thermoelectric generator while NASA and ESA each supply half the scientific payload. A NASA-ESA Joint Working Group meets about twice per year to monitor the project and discuss the technical and scientific requirements. Safety issues and measures which are being addressed due to the presence of the Pu-238 heat source for the RTG are discussed.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 39
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    In:  Other Sources
    Publication Date: 2011-08-19
    Description: The contributions of NSSDC and SPAN to the September 11, 1985 ICE-Comet Giacobini-Zinner encounter are outlined. The NSSDC is a centralized archive and distribution center for data obtained from NASA space and earth science flight investigations while SPAN is a mission-independent computer-to-computer network used to gain electronic access to NASA facilities, coinvestigators, and data for many scientists. The ICE encounter revealed the value of SPAN and NSSDC in providing rapid access to important science data.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: EOS (ISSN 0096-3941); 67; 105
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  • 40
    Publication Date: 2011-08-19
    Description: Smith and Greenspan (1984) examined theoretically the idea of using a uniform rotation of the floating zone system to confine the thermocapillary flow in crystal growth experiments to the melt sidewall, leaving the interior of the melt passive. Here, that model is extended to a full zone with a more realistic temperature distribution imposed on the sidewall, and both linear and nonlinear thermocapillary flows are theoretically studied. Linearized, analytical solutions are found using singular perturbation theory and the various sidewall boundary layers described by Greenspan (1969) for rotating fluids. The analytical and linearized numerical results are compared, and the linear and nonlinear flows are discussed. The results demonstrate that the thermocapillary flow is strong and that rotation cannot confine the flow. Temperature advection by strongly nonlinear flow is significant even for the small Prandtl number of silicon.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Journal of Crystal Growth (ISSN 0022-0248); 74; 301-320
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  • 41
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: The possible impacts and interactions of the agency's planning activities for the Orbit Transfer Vehicle (OTV) that is tentatively scheduled for initial operational capability in the late 1990's are identified. In general, the various Mars missions require vehicles of significant size and performance far greater than that provided by any OTV configuration currently being seriously considered. Therefore, interactions and impacts on these current concepts are minimal. These impacts and interactions fall into categories of technologies, systems, and operations. Each category is addressed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 1011-1017
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  • 42
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: Several potential ways of utilizing the space station, including utilization of learning experiences (such as operations), utilization of specific elements of hardware which can be largely common between the SS and Mars programs, and utilization of the on-orbit SS for transportation node functions were identified and discussed. The probability of using the SS in all of these areas seems very good. Three different ways are discussed of utilizing the then existing Low Earth Orbit (LEO) SS for operational support during assembly and checkout of the Mars Space Vehicle (SV): attaching the SV to the SS; allowing the SV to co-orbit near the SS; and a hybrid of the first 2 ways. Discussion of each of these approaches is provided, and the conclusion is reached that either the co-orbiting or hybrid approach might be preferable. Artists' conception of the modes are provided, and sketches of an assembly system concept (truss structure and subsystems derivable from the SS) which could be used for co-orbiting on-orbit assembly support are provided.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 1018-1034
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  • 43
    Publication Date: 2013-08-31
    Description: In the mid 1990's, the space station will become a point from which inter-planetary vehicles can be launched. The practicalities of a manned Mars mission are now being studied, along with some newer concepts for human life support. Specifically, the use of organisms such as plants and algae as the basis for life support systems is now being actively considered. A Controlled Ecological Life Support System (CELSS) is composed of several facilities: (1) to grow photosynthetic plants or algae which will produce food, oxygen and potable water, and remove carbon dioxide exhaled by a crew; (2) to process biomass into food; (3) to oxidize organic wastes into CO2; and (4) to maintain system operation and stability. Such a system, when compared to using materials stored at launch, may have distinct weight and cost advantages, depending upon crew size and mission duration, as well as psychological benefits for the crew. The use of the system during transit, as well as in establishing a re-visitable surface camp, will increase the attractiveness of the CELSS concept for life support on interplanetary missions.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 363-376
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  • 44
    Publication Date: 2013-08-31
    Description: The initial concepts developed for the in-orbit assembly of a Manned Mars Vehicle and for the Earth-to-Orbit (ETO) delivery of the required hardware and propellant are presented. Two (2) Mars vehicle concepts (all-propulsive and all-aerobrake) and two (2) ETO Vehicle concepts were investigated. Both Mars Vehicle concepts are described in Reference 1, and both ETO Vehicle concepts are described in Reference 2. The all-aerobrake configuration reduces the number of launches and time required to deliver the necessary hardware/propellent to orbit. Use of the larger of the 2 ETO Vehicles (HLLV) further reduces the number of launches and delivery time; however, this option requires a completely new vehicle and supporting facilities.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 306-315
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  • 45
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: Two Mars surface based build-up scenarios are presented in order to help visualize the mission and to serve as a basis for trade studies. In the first scenario, direct manned landings on the Martian surface occur early in the missions and scientific investigation is the main driver and rationale. In the second senario, Earth development of an infrastructure to exploit the volatile resources of the Martian moons for economic purposes is emphasized. Scientific exploration of the surface is delayed at first in this scenario relative to the first, but once begun develops rapidly, aided by the presence of a permanently manned orbital station.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group papers, Volume 1, Section 1-4; p 252-262
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  • 46
    Publication Date: 2013-08-31
    Description: A concept is presented for a flyby mission of the planet. The mission was sized for the 2001 time period, has a crew of three, uses all propulsive maneuvers, and requires 442 days. Such a flyby mission results in significantly smaller vehicles than would a landing mission, but of course loses the value of the landing and the associated knowledge and prestige. Stay time in the planet vicinity is limited to the swingby trajectory but considerable time still exists for enroute science and research experiments. All propulsive braking was used in the concept due to unacceptable g-levels associated with aerobraking on this trajectory. LEO departure weight for the concept is approximately 594,000 pounds.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 219-227
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  • 47
    Publication Date: 2013-08-31
    Description: Material applicable to Mars missions are excerpted from an earlier study covering a broader range of applications of solar sails. The basic principles of solar sail operation are provided, and the implications on trajectories and mission are discussed briefly. Concepts of solar sails and interplanetary vehicles are described and discussed. Some of the important solar sail material considerations are presented and some selections criteria are provided.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 176-187
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  • 48
    Publication Date: 2013-08-31
    Description: Vehicle design requirements of a reusable system for manned Mars missions which employ aerocapturing techniques to obtain desired orbital velocities are defined. Requirements for vehicle L/D and ballistic coefficient are determined for expected aerocapture velocities. Conclusions are presented concerning g-loads environment and TPS requirements for a vehicle that aerocaptures at Mars and Earth. Although the goal of a reusable system (based on current state-of-art technologies) was not obtained, the viability of aerocapture at Mars and Earth was established.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 114-128
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  • 49
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: The Case for Mars workshops conducted in 1984 dealt with a program to establish a permanent scientific research base at Mars. The participants, viewed a Mars base as the much needed long-term focus for the space program. A permanent base was chosen rather than the more conventional concept of a series of individual missions to different sites became the permanent base offers much greater scientific return plus greater crew safety and the potential for growth into a true colony. The results of the workshops are summarized.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 342-360
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  • 50
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    In:  CASI
    Publication Date: 2016-06-07
    Description: A wide variety of space station applications for tethers were reviewed. Many will affect the operation of the station itself while others are in the category of research or scientific platforms. One of the most expensive aspects of operating the space station will be the continuing shuttle traffic to transport logistic supplies and payloads to the space station. If a means can be found to use tethers to improve the efficiency of that transportation operation, it will increase the operating efficiency of the system and reduce the overall cost of the space station. The concept studied consists of using a tether to lower the shuttle from the space station. This results in a transfer of angular momentum and energy from the orbiter to the space station. The consequences of this transfer is studied and how beneficial use can be made of it.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 239-267
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  • 51
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    In:  CASI
    Publication Date: 2016-06-07
    Description: Ideas of deep space exploration are considered. The role of tethers in deep space is of most concern. A proposal of a tethered instrument package in orbit about the Moon is explored. The idea of a sling on the surface of the Moon which would take solar energy and build up momentum of the sling is studied. The NASA idea of a Mars Aeronomy Orbiter which would use a tether to enhance the planned Mars Orbiter is reviewed. It is also proposed that a tether can be attached to an asteroid during a spacecraft flyby. The possibility of using tethers to provide a transportation system for payloads which are coming to the surface from escape, and which are leaving Mars and escaping from Mars itself is also studied. A proposal from the Jet Propulsion Lab. on collecting comet or asteroid samples and returning them to Earth is reviewed. A tethered penetrator which could collect core samples is the proposed way. Also considered is the area of electrodynamic tethers at Jupiter.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 127-151
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  • 52
    Publication Date: 2016-06-07
    Description: Two separate projects were carried out to study alloys whose solidification structures can be strongly influenced by the presence of a container during melting and solidifications. One project involved containerless solidification of hypermonotectic Au35Rh65 alloys. This alloy exhibits liquid immiscibility over a temperature range. It has been suggested that containerless melting might be one solution to the problem of sedimentation in the dispersions of immiscible liquid phases. However, surface tension driven flows could also lead to accumulation of the minority liquid phase at the external surface of a containerlessly melted alloy. The research underway is a first step in determining the influence of containerless, microgravity processing on immiscible alloys. Nickel-niobium alloys were studied using the drop tube facility. One alloy in this system, a Ni60Nb40 alloy, is a good candidate for the formation of a bulk metallic glass. Amorphous alloys of this composition were produced using thin film and mechanical alloying techniques. However, theory indicates that if heterogeneous nucleation can be avoided, it should be possible to produce an amorphous structure in this system using a moderate cooling rate from the melt. The containerless melting and solidification capabilities of the drop tube faciltiy provide ideal conditions for a study of this type. To date, several Ni60Nb40 samples have been levitated, melted and cooled during 4.6 seconds of free fall in the 100 meter drop tube. Structures obtained are discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Research Reports: 1985 NASA(ASEE Summer Faculty Fellowship Program; 25 p
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  • 53
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    In:  CASI
    Publication Date: 2016-06-07
    Description: The studies that have been carried out on Tethered Constellations are briefly addressed. A definition of a tethered constellation is any number of masses/platforms greater that two connected by tethers in a stable configuration. Configurations and stability constraints are reviewed. Conclusions reached are: (1) The 1-D, horizontal, passively stabilized constellations have been ruled out; (2) Fishbone constellations have been also ruled out; (3) Alternative stable 2-D configurations have been devised such as the quadrangular configuration stabilized by electrodynamic forces (ESC), the quadrangular configuration stabilized by differential air drag (DSC), and the pseudo elliptical configuration stabilized by electrodynamic forces (PEC). Typical dimensions for these constellations are 10 km (horizontal) by 20 km (vertical) with balloon diameters around 100 m in the case of a DSC and a power consumption around 7 KW for an ESC or PEC.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 285-308
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  • 54
    Publication Date: 2016-06-07
    Description: One of the important parameters in the analysis of sediment entrainment and transport is gravitational attraction. The availability of a laboratory in Earth orbit would afford an opportunity to conduct experiments in zero and variable gravity environments. Elimination of gravitational attraction as a factor in such experiments would enable other critical parameters (such as particle cohesion and aerodynamic forces) to be evaluated much more accurately. A Carousel Wind Tunnel (CWT) is proposed for use in conducting experiments concerning sediment particle entrainment and transport in a space station. In order to test the concept of this wind tunnel design a one third scale model CWT was constructed and calibrated. Experiments were conducted in the prototype to determine the feasibility of studying various aeolian processes and the results were compared with various numerical analysis. Several types of experiments appear to be feasible utilizing the proposed apparatus.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Lyndon B. Johnson Space Center Space Station Planetology Experiments (SSPEX); 3 p
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  • 55
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: A Mars landing mission in 2000 presents a structural challenge. Earlier studies have indicated that a Mars landing was then feasible using current structural techniques. Since these earlier studies, technology advances were made to enhance the capability. Lighter and stronger materials, large structures programs, and supercomputers now exist and even greater advances are expected. The feasibility of a Mars landing does not depend on the structure. If the space travelers can withstand the trip, the necessary structures can be provided to deliver them. If artificial gravity is required the structure can also provide for it. The structural challenge is to provide structural designs that are lightweight with high reliability. In order to do this advanced technology must be utilized to the fullest on all structural elements.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 733-744
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  • 56
    Publication Date: 2013-08-31
    Description: Drawing upon the extensive Soviet and Skylab medical observations, the need for artificial gravity (g) on a manned Mars mission is discussed. Little hard data derived from well done experiments exist. This dearth of information is primarily due to two factors. Inability to collect tissues from astronauts for ethical or operational reasons. Second, there was not opportunities to fly animals in space to systematically evaluate the extent of the problem, and to develop and then to prove the effectiveness of countermeasures. The Skylab and space station will provide the opportunity to study these questions and validate suggested solutions.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 630-633
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  • 57
    Publication Date: 2013-08-31
    Description: Issues relating to the selection of initial landing sites for manned Mars missions are discussed from a geological viewpoint. The two prime objectives for initial manned exploration should be the youngest unambiguous lava flows (to tie down the late end of the cratering history curve for Mars) and old highland crust, which is best sampled and studied through the use of large impact basins as natural, planetary drill-holes. Exploration of these two sites will provide data on Martian chronology, volcanism, impact processes and gross chemical structure that will enable a first-order global synthesis through integration of these results with the global remote-sensing data already in hand from Viking and that to be provided by the Mars Observer Mission.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 578-590
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  • 58
    Publication Date: 2013-08-31
    Description: The necessity and advantage of surface transportation was well demonstrated by the Apollo 15, 16, and 17 missions. Baseline surface transportation elements for further studies are Lunar Rover, Elastic Loop Mobility System, Mobile Laboratory, Airplane, and Rocket Powered Flying Vehicles. These types of surface transportation are discussed. Starting points for further in-depth studies are identified.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 437-444
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  • 59
    Publication Date: 2013-08-31
    Description: As the number of scientific experiments for the surface of Mars grows, the need for effective surface transportation becomes critical. Because of the diversity of the experiments proposed, as well as the desire to explore Mars from the equator to the poles, the optimum surface vehicle configuration is not obvious. Five candidate vehicles are described, with an estimate of their size and performance. In order to maximize the success of a manned Mars mission, it appears that two vehicles should be designed for surface transportation: an advanced long-range rover, and a remotely-piloted airplane.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 415-422
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  • 60
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    In:  CASI
    Publication Date: 2013-08-31
    Description: Trajectory and mission requirement data are presented for Earth Mars opposition and conjunction class roundtrip flyby and stopover mission opportunities available between 1997 and 2045. The opposition class flyby mission uses direct transfer trajectories to and on return from Mars. The opposition class stopover mission employs the gravitational field of Venus to accelerate the space vehicle on either the outbound or inbound leg in order to reduce the propulsion requirement associated with the opposition class mission. The conjunction class mission minimizes propulsion requirements by optimizing the stopover time at Mars.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 103-113
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  • 61
    Publication Date: 2013-08-31
    Description: The use of libration points as transfer nodes for an Earth-Mars transportation system is briefly described. It is assumed that a reusable Interplanetary Shuttle Vehicle (ISV) operates between the libration point and Mars orbit. Propellant for the round-trip journey to Mars and other supplies would be carried from low Earth orbit (LEO) to the ISV by additional shuttle vehicles. Different types of trajectories between LEO and libration points are presented, and approximate delta-V estimates for these transfers are given. The possible use of lunar gravity-assist maneuvers is also discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 66-77
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  • 62
    Publication Date: 2013-08-31
    Description: The options for recovering a returned manned Mars spacecraft are surveyed. Earth parking orbits from libration point to low circular are discussed, with a 500 km perigee, 24 hour period elliptical orbit chosen as a baseline for further calculation. Several techniques for recovering up to 100 metric tons of returned spacecraft are investigated, including recovery by a low Earth orbit (LEO) based orbit transfer vehicle (OTV) pushing the spacecraft to LEO, and OTV transporting and aerobrake to the spacecraft, and an OTV delivering propellant to the spacecraft. Methods utilizing OTVs results in less total mass in LEO, but may not be the minimum cost solutions if significant development and testing are required.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 53-65
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  • 63
    Publication Date: 2013-08-31
    Description: A number of manned Mars mission types, propulsion systems, and operational techniques are compared. Conjunction and opposition class missions for cryogenic, hybrid (cryo/storable), and NERVA propulsion concepts are addressed. In addition, both Earth and Mars orbit aerobraking, direct entry of landers, hyperbolic rendezvous, and electric propulsion cases are examined. A common payload to Mars was used for all cases. The basic figure of merit used was weight in low Earth orbit (LEO) at mission initiation. This is roughly proportional to launch costs.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 37-52
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  • 64
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    In:  CASI
    Publication Date: 2013-08-31
    Description: A discussion is presented of the basic principles of aerobraking. Typical results are given for the application of aerobraking to orbital capture at Mars, descent to the Mars surface and orbital capture on return to Earth.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 21-36
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  • 65
    Publication Date: 2013-08-31
    Description: A series of simulated manned Mars missions was analyzed by a computer model. Numerous mission opportunities and mission modes were investigated. Sensitivity trade studies were performed of the vehicle all-up mass and propulsion stage sizes as a function of various levels of conservatism in mission velocity increment margins, payload mass and propulsive stage characteristics. The longer duration but less energetic type of conjunction class mission is emphasized. The specific mission opportunity reviewed was for a 1997 departure. From the trade study results, a three and one-half stage vehicle concept evolved, utilizing a Trans-Mars Injection (TMI) first stage derived from the Space Shuttle External Tank (ET).
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 292-305
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  • 66
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: The requirements, issues, and design options are reviewed for manned Mars landers. Issues such as high 1/d versus low 1/d shape, parking orbit, and use of a small Mars orbit transfer vehicle to move the lander from orbit to orbit are addressed. Plots of lander mass as a function of Isp, destination orbit, and cargo up and down, plots of initial stack mass in low Earth orbit as a function of lander mass and parking orbit, detailed weight statements, and delta V tables for a variety of options are included. Lander options include a range from minimum landers up to a single stage reusable design. Mission options include conjunction and Venus flyby trajectories using all-cryogenic, hybrid, NERVA, and Mars orbit aerobraking propulsion concepts.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 239-251
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  • 67
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    In:  CASI
    Publication Date: 2013-08-31
    Description: A concept is presented for a three man crew to fly by the planet Mars. The ground rule for the study is to execute the mission as quickly as possible which dictates using late 1990's technologies and space infrastructure. The proposed mission described herein uses a preliminary concept for the agency's Manned Orbit Transfer Vehicle (MOTV) and proposed space station elements. The space vehicle will depart from the LEO space station and is delivered to Low Earth Orbit (LEO) by a future launch vehicle of a Shuttle Derived Launch Vehicle (SDV) class. The trajectory parameters are chosen such that the mission duration is on the order of one year, with a two and one-half hour period within ten planetary radii of Mars. If the issues of acceptable crew g loads and entry vehicle heat load can be resolved, then the returning vehicle can aerobrake at Earth into a space station compatible orbit. Otherwise, a propulsive maneuver will be required to reduce vehicle velocity prior to Earth entry interface. It is possible to execute a mission of reasonable capability at an initial LEO departure weight of 716,208 pounds for the aerobraked case of 1,350,000 pounds for the propulsive case.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 203-218
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  • 68
    Publication Date: 2013-08-31
    Description: The utimate design of a manned Mars base will be the result of considerable engineering analysis and many trade studies to optimize the configuration. Many options and scenarios are available and all need to be considered at this time. Initial base elements, two base configuration concepts, internal space architectural concerns, and two base set-up scenarios are discussed. There are many variables as well as many unknowns to be reckoned with before people set foot on the red planet.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 386-396
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  • 69
    Publication Date: 2013-08-31
    Description: The problem of orbit transfers from a Mars parking orbit with an inclination of 165 degrees to the Mars Moon is addressed. The transfer can be accomplished using a three impulse transfer. The current 1999 baseline manned Mars mission requires a Mars parking orbit with an inclination of 165 degrees. This orbit inclination is necessary due to the direction of the Mars arrival and departure asymptotes of the interplanetary trajectory. The selection of this inclination for the parking orbit minimized the delta velocity requirements at Mars arrival and departure. This presents a problem in making transfer from this orbit to either Phobos or Deimos since it is a retrograde orbit. It is possible to make this transfer efficiently using a three impulse transfer and an intermediate transfer orbit with a very large apogee altitude. How the intermediate transfer orbit apogee can be determined based on a preselected transfer time, the delta velocities required as a function of transfer time, and the propellant required at a function of mission module weight for a transfer time of 5 days is shown. The data presented is specifically for the 1999 opposition class mission but the methods outlined are applicable to any other mission which requires a high inclination parking orbit.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 154-161
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  • 70
    Publication Date: 2013-08-31
    Description: Fuel and oxidizer produced on the surface of Mars and on the Martian Moon Phobos can reduce the cumulative mass of fuel and oxidizer which must be launched to low Earth orbit for Mars exploration missions. A scenario in which ten conjunction class trajectory missions over a twenty year period land a surface base and propellant production facilities on the Martian surface and on Phobos was examined. Production of oxygen on Phobos provides the greatest benefit. If all the propellant for Mars operations and Earth return is produced at Phobos and on Mars, a 30% reduction in cumulative low Earth orbit mass can be achieved at the end of the 20 year period.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 162-175
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  • 71
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    In:  CASI
    Publication Date: 2013-08-31
    Description: Representative interplanetary space vehicle systems are sized to compare and show sensitivity of the initial mass required in low Earth orbit to one mission mode and mission opportunity. Data are presented to show the requirements for Earth-Mars opposition and conjunction class roundtrip flyby and stopover mission opportunities available during the time period from year 1997 to year 2045. The interplanetary space vehicle consists of a spacecraft and a space vehicle acceleration system. Propellant boil-off for the various mission phases is given for the Lox/LH (Liquid Oxygen/Liquid Hydrogen) propulsion systems. Mission abort information is presented for the 1999 Venus outbound swingby trajectory, transfer profile.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 87-102
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  • 72
    facet.materialart.
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    In:  CASI
    Publication Date: 2013-08-31
    Description: A discussion is presented comparing past and present major accomplishments of the U.S. and the Soviet Union in space. It concludes that the Soviets are presently well ahead of the U.S. in several specific aspects of space accomplishment and speculates that the Soviet strategy is directed towards sending a man to the vicinity of Mars by the end of this century. A major successful multinational space endeavor, INTELSAT, is reviewed and it is suggested that the manned exploration of Mars offers a unique opportunity for another such major international cooperative effort. The current attitude of U.S. leadership and the general public is assessed as uniformed or ambivalent about the perceived threat of Soviet dominance in space.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 13-18
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  • 73
    Publication Date: 2011-08-19
    Description: The objectives of the Giotto magnetometer experiment are the investigation of the interaction between Comet Halley and the solar wind 0.9 AU from the Sun, to within 500 km of the cometary nucleus, and the study of the interplanetary magnetic field. The instrumentation consists of a triaxial and a separate biaxial system of fluxgate sensors of the ring-core type, the associated analog electronics and a digital processor. The measuring ranges of + or 1 16 up to + or - 65536 nT are digitized by a 12-bit analog-to-digital converter. Memory modes allow the bridging of gaps in telemetry coverage of up to 10 days. Because of the dust hazard near closest approach, a magnetometer boom could not be included in the spacecraft design. The magnetic contamination problem was attacked by the use of two magnetometers and by a magnetic-cleanliness program. In-flight results show that the instrument is working flawlessly, though magnetic-contamination problems remain.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA The Giotto Mission: Its Scientific Investigations; p 1-14
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  • 74
    Publication Date: 2011-08-19
    Description: The main objectives of the IUE Halley's Comet program are: study of the physical and chemical properties of a comet clearly different from those observed previously with IUE; study of the long-term evolution of the gas and dust coma and the ion and dust tails, by combining IUE data with UV and in-situ observations obtained by other spacecraft; and assessment of the gas and dust environment of Halley in terms of its possible impact on the trajectories of the flyby spacecraft. Another program investigates the CS scale length, and the rotational profile of CS in order to test and calibrate dynamic-flow models of comets. These observations will begin in August 1985 when the heliocentric distance of the comet is 2.8 AU and its total visual magnitude + 13. They will continue into the ninth IUE observing period, through mid-1986.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Space Missions to Halley's Comet; p 129-133
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  • 75
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    Publication Date: 2011-08-19
    Description: The Astro-1 mission was to be launched in March 1986 for an effective duration of 7 days, chosen to overlap spacecraft encounters with Halley's Comet, i.e., Vega-2 (on 9 March) and Giotto (on 13/14 March). The ultraviolet instrument complement while not designed with cometary research as the prime objective, was well suited to the study of comets. The opportunity of an extended mission during the time of the spacecraft encounters of Halley's Comet offered an extraordinary opportunity for a synergistic interaction between the intercept spacecraft, the Earth-orbital Astro-1 mission, and ground-based observations. The addition of visual-wavelength, wide-field cameras would enhance the scientific return of the mission. Loss of Challenger cancelled the mission.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Space Missions to Halley's Comet; p 117-127
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  • 76
    Publication Date: 2011-08-19
    Description: Use of the ISEE-3 satellite (renamed ICE) to study the interaction between the solar wind and a cometary atmosphere by passing through the plasma tail by intercepting Comet Giacobini-Zinner on 11 September 1985 is described. Details of the targeting strategy are discussed. Additional scientific objectives following the tail intercept of Comet Giacobini-Zinner include the support of Comet Halley studies through the measurement of solar-wind conditions upstream of P/Halley in October 1985 and March 1986.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Space Missions to Halley's Comet; p 99-115
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  • 77
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    In:  Other Sources
    Publication Date: 2011-08-19
    Description: The 'dual keel' design currently under consideration for NASA's Space Station program is of rectangular configuration to yield greater space along the truss structure for the attachment of payloads, by comparison with a previously considered single-keel truss design. The placing of the pressurized modules much nearer the center of gravity of this station configuration allows accelerations that are closer to 1 micro-g than the earlier alternative. The U.S. Servicing Facility and Telerobotic System, and the Canadian Mobile Servicing Center, will be incorporated in order to meet a large variety of Space Station servicing requirements.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Aerospace America (ISSN 0740-722X); 24; 30
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  • 78
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    In:  Other Sources
    Publication Date: 2011-08-19
    Description: The Gravity Probe-B (GP-B) experiment is one of the most sophisticated and challenging developments to be undertaken by NASA. Its objective is to measure the relativistic drift of gyroscopes in orbit about the earth. In this paper, the experiment is described, and the strategy of phased procurements for accomplishing the engineering development of the hardware is discussed. The microcomputer is a very convenient and powerful tool in the management of GP-B. It is used in creating and monitoring such project data as schedules, budgets, hardware procurements and technical and interface requirements. Commercially available software in word processing, database management, communications, spreadsheet, graphics and program management are used. Examples are described of the efficacy of the application of the computer by the management team.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 79
    Publication Date: 2011-08-19
    Description: The analysis of the STS-7 flight experiments of the GeSe-xenon system yielded positive results which surpass the original objectives of these experiments. The mass transport rates of GeSe observed in microgravity environment are in close agreement with theoretically predicted values for diffusion limited mass transport. This supports the earlier proposed hypothesis for the interpretation of flux anomalies observed in previous space experiments. In addition, the STS-7 flight experiments led to the observation of unexpected crystal growth phenomena. The largest GeSe single crystals obtained in microgravity grew in the ampul without direct wall contact which could suggest homogeneous nucleation. The space grown crystals are much larger and have considerably improved surface and bulk morphologies relative to corresponding ground control specimens. The combined results are of basic scientific importance and of technological significance.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Electrochemical Society, Journal (ISSN 0013-4651); 133; 1015-102
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  • 80
    Publication Date: 2011-08-19
    Description: The encounter, on September 11, 1985, between the International Cometary Explorer (ICE) and the comet Giacobini-Zinner, is described in detail. The primary goal of this encounter was to study the interaction between the solar wind and the comet. At the time of the encounter, the spacecraft was approximately 50 times farther from the earth than it was designed to go, making it difficult to recover data. The seven instruments on board ICE which were operational in this mission were the plasma electron, magnetometer, plasma waves, radio waves, plasma composition, low-energy cosmic ray, and energetic proton instruments. The encounter is depicted schematically, showing the times different regions were crossed. The spacecraft velocity vector, measured relative to the comet, made a 93 deg angle with respect to the plasma tail axis. The spacecraft crossed the center of the comet ion tail at approximately 1102 U.T. A cold, dense plasma was found near the center of the tail; at the very center was a temperature reading of only 13,000 K and a density of 670 electrons/cu cm. Alfven's model of comet tail formation was confirmed and it was found that water group ions are the dominant comet component. Pulses were detected which were attributed to dust particles hitting the spacecraft.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Science (ISSN 0036-8075); 232; 353-356
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  • 81
    Publication Date: 2011-08-19
    Description: In June 1985, two instrumented balloons were placed in the atmosphere of Venus as part of the VEGA mission. Each balloon traveled about 30 percent of the way around the planet at a float altitude near 54 kilometers. In situ sensors measured pressure, temperature, vertical wind velocity, cloud particle backscatter, ambient light level, and frequency of lightning. A ground-based network of 20 radio antennas tracked the balloons by very long baseline interferometry (VLBI) techniques to monitor the Venus winds. The history, organization, and principal characteristics of this international balloon experiment are described.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Science (ISSN 0036-8075); 231; 1407
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  • 82
    Publication Date: 2013-08-31
    Description: A major goal of a manned Mars mission is to explore the planet and to investigate scientific questions for which the intensive study of Mars is essential. The systematic exploration of planets was outlined by the National Academy of Science. The nearest analogy to the manned Mars mission is the Apollo program and manned missions to the Moon, but the analogy is limited. The case is argued here that Mars may have to be explored far more systematically than was the pre-Apollo Moon to provide the detailed information necessary if plans are made to use any of the resources available on Mars. Viking missions provided a wealth of information, yet there are great gaps in the fundamental knowledge of essential facts such as the properties of the Martian surface materials and their interaction with the atmosphere. Building on a strong data base of precursor missions, human exploration will allow great leaps in understanding the Martian environment and geologic history and its evolutionary role in the solar system.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 566-577
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  • 83
    Publication Date: 2013-08-31
    Description: Several types of manned Mars surface missions, including sorties, fixed-base, and hybrid missions, which can be envisioned as potentially desirable approaches to the exploration and utilization of Mars are identified and discussed. Some of the advantages and disadvantages of each type are discussed briefly. Also, some of the implications of the types of missions on the surface elements' design are discussed briefly. Typical sets of surface elements are identified for each type of mission, and weights are provided for each element and set.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 423-436
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  • 84
    Publication Date: 2013-08-31
    Description: A hydrogen-oxygen fuel cell system is identified as a viable power source for a long range inhabited surface transportation system for the exploration of Mars. Power system weights and power requirements are determined as a function of vehicle weight. For vehicles weighing from 2700 to 7300 kg in LEO, the total power system weight ranges from 1140 to 1860 kg, with the reactants and energy conversion hardware (fuel cells, reactant storage, and radiator) weighing 430 to 555 kg and 610 to 1110 kg, respectively. Vehicle power requirements range from 45 kW for a 2700 kg vehicle to 110 kW for a 7300 kg vehicle. Power system specific weights and power profiles for housekeeping and the operation of scientific equipment such as coring drills and power tools are also specified.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 397-405
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  • 85
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    In:  CASI
    Publication Date: 2013-08-31
    Description: The assembly of a manned Mars interplanetary spacecraft in low Earth orbit can be best accomplished with the support of the space station. Station payload requirements for microgravity environments of .001 g and pointing stability requirements of less than 1 arc second could mean that the spacecraft may have to be assembled at a station-keeping position about 100 meters or more away from the station. In addition to the assembly of large modules and connective structures, the manned Mars mission assembly tasks may include the connection of power, fluid, and data lines and the handling and activation of components for chemical or nuclear power and propulsion systems. These assembly tasks will require the use of advanced automation and robotics in addition to Orbital Maneuvering Vehicle and Extravehicular Activity (EVA) crew support. Advanced development programs for the space station, including on-orbit demonstrations, could also be used to support manned Mars mission technology objectives. Follow-on studies should be conducted to identify space station activities which could be enhanced or expanded in scope (without significant cost and schedule impact) to help resolve key technical and scientific questions relating to manned Mars missions.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 1035-1044
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  • 86
    Publication Date: 2013-08-31
    Description: Manned Mars Mission departures from low lunar orbit (LLO), L2, and low Earth orbit (LEO), using oxygen or oxygen and hydrogen produced on the Lunar surface; or Phobos produced propellants; are compared to departures from LEO using Earth produced propellants. The economy of a given scheme is a function of the ratio of Earth launch to lunar launch costs per unit mass. To achieve savings on the order of 40% of total Earth launch costs for steady state operations requires the availability of both oxygen and hydrogen on the Moon and launch per unit mass costs of lunar surface to LLO in the range of 25% of Earth to LEO costs.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 188-200
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  • 87
    Publication Date: 2013-08-31
    Description: Calculations are presented for the 1999 opposition class mission and a procedure for obtaining singlar occultation data for any other given Mars mission is given. Occultation data for a Mars orbiter in a 24.5 hour parking orbit and a Mars base were calculated for: sunlight occultation - the time in darkness; and radio communication occultation - the communication losses between the lander and the orbiter, the lander and Earth, and orbiter and Earth.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 142-153
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  • 88
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    In:  CASI
    Publication Date: 2013-08-31
    Description: Parking orbits for a manned Mars mission are examined for ease of access to the Martian moons. Delta V plots for a variety of burns versus elliptical orbit apoapsis are included. A high elliptical orbit (24 hour period, 500 km periapsis, 20 to 30 deg. inclination) minimizes delta V to the Martian moons and Mars orbit insertion (MOI) and trans-Earth injection (TEI) delta Vs.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 78-86
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  • 89
    Publication Date: 2013-08-31
    Description: A short review of the history of planetary quarantine, the issues, and changes in official advisory groups' pronouncements are presented. Then a discussion of the current situation and some ideas on how best to address them are outlined. Both manned and unmanned or automatic missions are discussed and their advantages and impediments outlined.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 550-555
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  • 90
    Publication Date: 2013-08-31
    Description: Rock drilling and coring conceptual designs for the surface activities associated with a manned Mars mission are proposed. Straightforward extensions of equipment and procedures used on Earth are envisioned for the sample coring and shallow high explosive shot holes needed for tunneling and seismic surveying. A novel rocket exhaust jet piercing method is proposed for very rapid drilling of shot holes required for explosive excavation of emergency radiation shelters. Summaries of estimated equipment masses and power requirements are provided, and the indicated rotary coring rigs are scaled from terrestrial equipment and use compressed CO2 from the Martian atmosphere for core bit cooling and cuttings removal. A mass of 120 kg and power of 3 kW(e) are estimated for a 10 m depth capability. A 100 m depth capacity core rig requires about 1150 kg and 32 km(e). The rocket exhaust jet equipment devised for shallow (3m) explosive emplacement shot holes requires no surface power beyond an electrical ignition system, and might have a 15 kg mass.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 458-469
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  • 91
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    In:  CASI
    Publication Date: 2013-08-31
    Description: A set of roving vehicle design requirements were postulated, corresponding to an idealized Mars transport vehicle operational scenario which could serve as a reference for a manned Mars mission. The ability of conventional vehicles to satisfy these requirements were examined. The study indicated that no conventional vehicle could satisfy all of the requirements, as the vehicles are presently configured. Consequently, the requirements have to either be relaxed and/or an alternative, less conventional vehicle design will have to be developed. A possible unconventional vehicle design which has received considerable attention for DARPA and the Army is the walker vehicle. The design issues associated with this vehicle are presented, along with a comparison of the performance capabilities of this technology vs. conventional vehicle technology.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Missions. Working Group Papers, Volume 1, Section 1-4; p 445-457
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  • 92
    Publication Date: 2013-08-31
    Description: Planning and development for a permanently manned scientific outpost on Mars requires an in-depth understanding and analysis of the functions the outpost is expected to perform. The optimum configuration that accomplishes these functions then arises during the trade studies process. In a project this complex, it becomes necessary to use a formal methodology to document the design and planning process. The method chosen for this study is called top-down functional decomposition. This method is used to determine the functions that are needed to accomplish the overall mission, then determine what requirements and systems are needed to do each of the functions. This method facilitates automation of the trades and options process. In the example, this was done with an off-the shelf software package called TK! olver. The basic functions that a permanently manned outpost on Mars must accomplish are: (1) Establish the Life Critical Systems; (2) Support Planetary Sciences and Exploration; and (3) Develop and Maintain Long-term Support Functions, including those systems needed towards self-sufficiency. The top-down functional decomposition methology, combined with standard spread sheet software, offers a powerful tool to quickly assess various design trades and analyze options. As the specific subsystems, and the relational rule algorithms are further refined, it will be possible to very accurately determine the implications of continually evolving mission requirements.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, Volume 1, Section 1-4; p 470-493
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  • 93
    Publication Date: 2013-08-31
    Description: The process for selecting guest investigators for participation in the Control of Flexible Structures (COFS)-1 program is described. Contracts and grants will be awarded in late CY87. A straw-man list of types of experiments and a distribution of the experiments has been defined to initiate definition of an experiments package which supports development and validation of control structures interaction technology. A schedule of guest investigator participation has been developed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA(DOD Control)Structures Interaction Technology, 1986; p 319-325
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  • 94
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    Publication Date: 2013-08-31
    Description: The Control of Flexible Structures (COFS) program is divided into three areas of research. These three areas are controls/structures analysis development, ground test experiments, and in-space experiments. The ground test experiments are intended to validate analyses and to confirm through hardware tests our technical readiness to successfully fly the Mast hardware. There is this close relation to the results of ground tests and analytical predictions that must be understood before flight experiments may be attempted. Details relative to each program area are given.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA(DOD Control)Structures Interaction Technology, 1986; p 233-251
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  • 95
    Publication Date: 2013-08-31
    Description: The Mast Flight System is composed of several subsystems. Primary among these is the Deployable Mast Subsystem (DMS) which consists of a beam assembly and an associated mechanism for deploying and retracting the beam. The beam assembly is a joint dominated graphite epoxy and titanium truss as is expected of future large space structures. Integral to the beam assembly are actuators, sensors and associated electronics which are available for excitation and damping as desired by the experimenter. The beam structural characteristics can also be modified as desired by the experimenter using the Parameter Modification Device installed at the end of the beam. Data measured on the beam by the sensors and commands to the actuators are transmitted along the beam digitally at 150 Hz using a standard 1553 type bus. The Modular Distributed Information Sybsystem (MDIS) computer functions as bus master and ensures that all experimental data is saved for future analysis. The MDIS computer also performs a safing function to prevent inadvertent overexcitation of the beam. Finally, the Excitation and Damping Subsystem (EDS) computer is available to the experimenter for implementation of control algorithms or any other numerical operations as desired. Data from all system sensors can be accessed by the EDS computer.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Langley Research Center NASA(DOD Control)Structures Interaction Technology, 1986; p 253-263
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  • 96
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    Publication Date: 2016-06-07
    Description: The chairman of the Technology Applications in Space Working Group summarizes the technology issues for each of the disciplines in Tethered Satellite Systems. The disciplines are Tether Materials and Configurations, Tether System Dynamic Simulation Capability, Tether System Instrumentation, TAS Program Related Science Instrumentation, Atmospheric/Aerothermodynamic tethered system research, and TAS Discipline Program Accomplishment. To enable these tether applications, design and development programs have been recommended and are presently underway relative to the demonstration of the hollow cathode concept which is an enabling electrodynamic tether mission technology.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 279-283
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  • 97
    Publication Date: 2016-06-07
    Description: The capabilities of tether systems in orbit are going to be demonstrated by the first planned flights of the Tethered Satellite System (TSS). These test flights will investigate the properties of tether systems as low altitude atmospheric research facilities and as electric power generators. Studies are being conducted with the purpose of testing a variety of concepts and approaches. A comparative analysis of results will allow the choosing of the most promising ideas for further development. The broad range of applications presently under study include applications in electrodynamics, transportation, microgravity in addition to basic research. The SATP project definition study is now about midway through its first phase. The analyses conducted have led to an appraisal of users interest in the project and to a deeper understanding of the problems associated with large, long-lived tether systems in space. In addition, two specialized platform designs, devoted to microgravity and precise pointing applications, are being studied because of their potential usefulness and the promise of technical feasibility.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 269-278
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  • 98
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    In:  CASI
    Publication Date: 2016-06-07
    Description: Possible scientific applications in the field of the neutral ionized atmosphere and of the solid Earth in terms of the TSS are summarized. Studies of the vertical, zonal, and meridional neutral winds and temperature, whose extensive variations suggest the importance of energy transfer mechanism in modifying the structural properties of the region are reviewed. Layers below the F region of high plasma density that propagate to lower altitudes with drift velocities will be studied for their electron and ion composition and motion. These are to be measured by the TSS in conjunction with ground based radar observations. Basic fluid dynamics problems will be studied onboard tethered satellites. Studies will be conducted on the structure of the equatorial electrojet, in particular its longitudinal and meridional extent. Magnetic measurements will also be used to probe the tether current distribution in the plasma sheath.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 117-126
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  • 99
    facet.materialart.
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    In:  CASI
    Publication Date: 2016-06-07
    Description: Power and thrust applications of the electrodynamic tether are considered. The induced voltage in the tether wire is in the same direction in the case of a power generator and a spacecraft motor, and the difference involves whether one allows that voltage to drive a current to generate power. Or, if one uses an onboard power supply with a higher voltage to drive a current in the opposite direction, which then provides thrust. Return circuit currents must be spread out through the ionosphere sufficiently so that ionosphere conductivities are very high and so that anomalous resistance is not produced in the ionosphere which would prevent the current from flowing. This is largely a function of the plasma contactors that are used. Three have been most frequently considered. It is concluded that, for the primary power and thrust applications, the hollow cathode seems to be far superior to the electron gun for producing high current contact to the ionosphere. This has led to a study of the Plasma Motor Generator (PMG) because it is capable of being reversed. The PMG theory is explored along with other power and thrust applications of the electrodynamic tether.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 161-184
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  • 100
    Publication Date: 2016-06-07
    Description: A new experiment concept has been proposed for the shuttle/tethered satellite system missions, which can provide high resolution, global density mappings of certain ionospheric species. The technique utilizes bistatic LIDAR to take advantage of the unique dual platform configuration offered by these missions. A tuned, shuttle-based laser is used to excite a column of the atmosphere adjacent to the tethered satellite, while triangulating photometic detectors on the satellite are employed to measure the fluorescence from sections of the column. The fluorescent intensity at the detectors is increased about six decades over both ground-based and monostatic shuttle-based LIDAR sounding of the same region. In addition, the orbital motion of the Shuttle provides for quasi-global mapping unattainable with ground-based observations. Since this technique provides such vastly improved resolution on a synoptic scale, many important middle atmospheric studies, heretofore untenable, may soon be addressed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Volume 1; p 329-347
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