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  • Books
  • Other Sources  (320)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (320)
  • 1995-1999
  • 1985-1989  (320)
  • 1986  (320)
  • 1
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    Communication satellite technology trends (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A chronology of space-Earth interconnectivity is presented. The Advanced Communications Technology Satellite (ACTS) system, Land Mobile Satellite, space-Earth antennas, impact of antenna size on coverage, intersatellite links are outlined. This presentation is represented by graphs and charts only.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-Lewis Research Center, Spacecraft 2000; p 27-58
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Application of advanced technology to a permanently manned Space Station (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Advanced technologies developed by NASA's Space Station Advanced Development Program (ADP), which cover some 70 application areas, are discussed. Current data are presented that show promising applications in four of these areas: the Environmental Control and Life Support, Extravehicular Activities, Electrical Power, and Thermal Subsystem Design.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 86-60
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Future trends in spacecraft design and qualification (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Material and structures issues that must be resolved in order to develop the technology data base needed to design and qualify the next generation of large flexible spacecraft are discussed. This invoves the development of new ground test and analysis methods and the conduct of appropriate instrumented in-space flight experiments for final verification. A review of present understanding of material behavior in the space environment and identification of future needs is presented. The dynamic verification and subsequent qualification of a spacecraft structure currently rely heavily on ground-based tests, coupled with the verified analysis model. Future space structures, such as large antennas, Space Station and other large platforms, will be of sizes difficult to test using current ground test methods. In addition to size, other complex factors, such as low natural frequencies, lightweight construction and many structural joints, will also contribute significant problems to the test and qualification process in an Earth-gravity environment. These large spacecraft will also require new technology for controlling the configuration and dynamic deformations of the structures. Future trend in large flexible structures will also involve long-life design missions (10 to 20 years). In low earth orbit (LEO), materials will be subjected to repeated thermal cycles, ultraviolet radiation, atomic oxygen and vacuum. For high orbits such as geo-synchronous earth orbit (GEO), the materials will also be subjected to large doses of high energy electrons and protons. Understanding degradation and material stability over long-mission time periods will confront the designer with many issues that are unresolved today.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Mechanical Qualification of Large Flexible Spacecraft Structures; 9 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The New Space Network: the Tracking and Data Relay Satellite System (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: When the Tracking and Data Relay Satellite System (TDRSS)is completed, the system, together with its various NASA support elements will be known simply as the Space Networks. It will substantially increase information exchanges between low-orbiting spacecraft and the ground. The structural design, functions, earth-based links, and present and future use are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-EP-251(S) , NAS 1.19:251(S)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Tether propulsion (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The principle and applications of tethering are examined. Tethering works by momentum transfer; the center of mass of a system consisting of (for example) a Space Shuttle and a tethered payload such as the Advanced X-ray Astrophysical Facility continues to follow the original orbit. Given a slight outward velocity, the payload begins to lag behind because it has the same linear velocity as the Shuttle but is at a greater distance from the earth. Any displacement from the local vertical causes a restoring force at each end tending to restore the system to a vertical orientation. When vertically above the Shuttle, the payload has the same angular velocity but a greater linear velocity; thus momentum is transferred from the Shuttle to the payload. It is computed that a tether 32 nautical miles long could deploy AXAF into a 320-nautical mile orbit from a lower, elliptical Shuttle orbit, thus saving 5000 pounds of Shuttle propellant. Various types of tether are considered: Kevlar and steel, uniform and tapered. Numerous cases appear to be feasible for boost and deboost as well as momentum transfer, using such reaction masses as the Space Station, a lunar orbiter, the Martian moons Phobos and Deimos, various asteroids, and moons of the major planets.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 24; 40-43
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Future directions in materials and structures for space applications (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A comprehensive evaluation is made of materials and structural technology requirements for future space transportation systems, large spacecraft, and space structures. Exceptional promise is noted in carbon-carbon composites for large area thermal protection systems. High temperature test facilities, techniques, and instrumentation systems have unfortunately been neglected, and a materials systems data base suitable for high confidence design of long life space structures has yet to be compiled with a view to material environments in low earth and geosynchronous orbits. A coordinated analysis, ground test, and in-orbit experimentation program for candidate structure designs is called for.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-1185
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Further observations of Space Shuttle plasma-electrodynamic effects from OSS-1/STS-3 (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Recent analyses of ion measurements obtained from the Differential Ion Flux Probe (DIFP) on the deployed Plasma Diagnostics Package (PDP) during the OSS-1/STS-3 mission have provided an additional insight into the plasma-electrodynamics of the Space Shuttle Orbiter: (1) Measured ion flow directions and energies suggest that the disturbance created in the ionospheric plasma by the Shuttle Orbiter may be confined to an interaction region that extends on the order of 10 m in the forward direction and has a boundary thickness of about 2 m. (2) A correlation between the DIFP and pressure gauge measurements indicates a direct, local proportionality between the neutral gas and ion densities. (3) Preliminary results from a theoretical model of the possible interaction between measured secondary, high inclination ion streams and the ambient plasma indicate the generation of broad-band electrostatic noise such as that observed by wave instruments on the PDP.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Geophysical Research Letters (ISSN 0094-8276); 13; 217-220
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Dust collection on serviceable satellites (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: One rationale for the Space Shuttle program which was dramatically realized during the repair of the Solar Maximum Mission (SMM) is the efficiency of in-orbit satellite servicing. An unexpected benefit of this repair mission was the return of parts of the Solar Max satellite which had been exposed for four years to the space environment. Studies conducted on these parts have yielded valuable data on the micrometeorite flux and composition at shuttle altitudes during this time period. The scientific results from studies of the cosmic dust component of the observed particle impacts are not yet complete but it is clear from the preliminary data available that such studies will be a valuable adjunct to the studies of cosmic dust particles collected in the atmosphere. The success of the initial studies of particles collected during repairs of the SMM spacecraft on a surface not specifically designed as a particle collector nor retrieved in a manner intended to minimize or eliminate local contamination raises the possibility that even more interesting results might be obtained if serviceable satellites were initially designed with these objectives in mind. All designs for modern satellites utilize some form of thermal blanket material in order to minimize thermal stresses inside the spacecraft. It is proposed that all future satellites be designed with standardized removeable sections of thermal blanket material which could be replaced during on-orbit servicing and returned to earth for detailed study.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Lunar and Planetary Inst. Trajectory Determinations and Collection of Micrometeoroids on the Space Station; p 76
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    X-ray satellite (Rosat) (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An overview of the current status of the ROSAT X-Ray satellite project is given. Areas discussed include an overview of problem areas, systems and mechanical subsystems, the electrical subsystem, power supply, data processing and transmission, the wide field camera, ground support equipment and the production scheduling. It is shown that the project is proceeding according to schedule, including the hardware production and costs. However, it is stated that estimated additional costs will exceed the plan. The previous schedule for production of the flight model will no longer be met. A modified milestone plan has been worked out with Dornier Systems. The current working schedule calls for a launch data of December 21, 1987; however, this does not take into account a 4-week buffer prior to transporting the flight model to the launch site. As of the date of this report, milestone M5 has been met. Previous problems with the gold vapor deposition on the flight model mirror due to contamination have been eliminated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-88481 , NAS 1.15:88481 , SR-4 , DFVLR-RF-TN-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The suitability of various spacecraft for future space applications missions (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The Space Applications Advisory Committee (SAAC) of NASA's Advisory Council was asked by the Associate Administrator for Space Science and Applications to consider the most suitable future means for accomplishing space application missions. To comply with this request, SAAC formed a Task Force whose report is contained in this document. In their considerations, the Task Force looked into the suitability of likely future spacecraft options for supporting various types of application mission payloads. These options encompass a permanent manned space station, the Space Shuttle operating in a sortie mode, unmanned platforms that integrate a wide variety of instruments or other devices, and smaller free fliers that accommodate at most a few functions. The Task Force also recognized that the various elements could be combined to form a larger space infrastructure. This report summarizes the results obtained by the Task Force. It describes the approach utilized, the findings and their analysis, and the conclusions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-88986 , NAS 1.15:88986
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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