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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (364)
  • 1985-1989  (364)
  • 1
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    Robotics for the United States Space Station (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Advances in robotics technology that will be necessary for the NASA Space Station to achieve its optimal level of automation are examined. The present state and emerging trends in teleoperator systems, hybrid teleoperated robots, and autonomous robots are reviewed, and scenarios of assembly, inspection, satellite servicing, and manufacturing are presented in order to illustrate potential uses of automation and robotics on the Space Station. Individual important technology development areas for Space Station robotics are surveyed, including end effectors and mechanization, control systems, telepresence and human factors, preception, manipulation in space, operation planning and data bases, and hardware maintenance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Robotics (ISSN 0167-8493); 1; 205-222
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The multi-disciplinary design study. A life cycle cost algorithm (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Life-cycle cost (LCC) is investigated as a comprehensive design criterion for two major interrelated spacecraft subsystems, Controls and Structures. A Multi-Disciplinary Design Tool (MDDT) is developed to evaluate the sensitivity of LCC to subsystem design parameters. Major costs addressed are: non-recurring; launch; ground support; maintenance; expendables; and software. Examples and results from the MDDT are described, including a structural optimization study between different truss designs; a solar array feathering trade for a minimal drag configuration during umbra; and the cost of active control of a flexible structure is compared against the cost of passive damping using visco-elastic material.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-178192 , NAS 1.26:178192 , GE-DOC-87SDS-024
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Active spacecraft potential control: An ion emitter experiment (1988)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The cluster spacecraft are instrumented with ion emitters for charge neutralization. The emitters produce indium ions at 6 keV. The ion current is adjusted in a feedback loop with instruments measuring the spacecraft potential. The system is based on the evaporation of indium in the apex field of a needle. The design of the active spacecraft potential control instruments, and the ion emitters is presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA, The Cluster Mission: Scientific and Technical Aspects of the Instruments; p 95-102
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Measurement of orbital dynamics of the OAST-1 Solar Array using recorded video images (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The OAST-1 Solar Array Experiment was flown on Shuttle mission STS-41D on August 31, 1984 for NASA's Office of Aeronautics and Space Technology. It is pointed out that this was the first flight demonstration of the operation of a large solar array which was designed for multiple deployments and retractions. The array represents also a new class of very lightweight, flexible, low-frequency structures. A program was, therefore, implemented with the aim to study the structural dynamics of the array on the basis of a photogrammetric analysis of data obtained with the existing Shuttle closed circuit television (CCTV) system. The present paper has the objective to describe the experiment and its implementation, taking into account the unique process of analyzing the video data.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 85-213
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of the Spacelab Astro-1 mission heat pipe radiator (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the design and performance of the Astro Integrated Radiator System (IRS). The system was recently ground tested and proven successful in rejecting approximately 400 watts of heat. The radiator was constructed from an aluminum panel configured to form two orthogonal planes. Heat pipes were adhesively bonded and riveted to the radiator to isothermalize the surface. The IRS was subjected to a full thermal vacuum test to validate the thermal math model and to qualify the radiator for space flight. The thermal performance met prescribed temperature limits with margins at both extremes, and no mechanical failures occurred.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 851352
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    BASD: SIRTF Telescope Instrument Changeout and Cryogen Replenishment (STICCR) study (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Space Infrared Telescope Facility (SIRTF) is a long-life cryogenically cooled space-based telescope for infrared astronomy from 2 micrometer to 700 miocrometers currently under study by NASA-ARC, and planned for launch in approximately the mid 90's. SIRTF will operate as a multi-user facility, initially carrying 3 instruments at the focal plane. It will be cooled to below 2 K by superfluid liquid helium to achieve radiometric sensitivity limited only by the statistical fluctuations in the natural infrared background radiation over most of its spectral range. The lifetime of the mission will be limited by the lifetime of the liquid helium supply, and is currently baselined to be 2 years. The telescope changes required to allow in-space replenishment of the 2,000 liter superfluid helium tank are investigated. A preliminary design for the space services equipment is also developed. The impacts of basing the equipment and servicing on the space station are investigated. Space replenishment and changeout of instruments requires changes to the telescope design and preliminary concepts are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-177381 , NAS 1.26:177381 , F85-06
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The Modular Combustion Facility for the Space Station Laboratory - A Requirements and Capabilities Study (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes a modular combustion facility for the Space Station, designed to provide facility-level services to interchangeable experiment modules, each of which designed specifically for the needs of a particular combustion experiment. The facility-level services are to include computer devices for the data acquisition, experimental control, and data reduction and analysis; the electrical power conversion and control; video cameras and recordings; the cooling-loop supply; waste management; gas supply; precision gas-mixing; and the combustion diagnostics support. Summarized categories of the data base are provided, which were developed to assimilate and to process the responses from the investigators.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-0505 , E-8378
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Technology requirements for an orbiting fuel depot: A necessary element of a space infrastructure (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Advanced planning within NASA has identified several bold space exploration initiatives. The successful implementation of these missions will require a supporting space infrastructure which would include a fuel depot, an orbiting facility to store, transfer and process large quantities of cryogenic fluids. In order to adequately plan the technology development programs required to enable the construction and operation of a fuel depot, a multidisciplinary workshop was convened to assess critical technologies and their state of maturity. Since technology requirements depend strongly on the depot design assumptions, several depot concepts are presented with their effect on criticality ratings. Over 70 depot-related technology areas are addressed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101370 , E-4414 , NAS 1.15:101370
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Self-contained space qualifiable optical contamination monitor (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experiments operating in the VUV as well as those employing cryocooled optical surfaces are the most seriously affected by spacecraft contamination due to outgassing of foreign materials, reaction byproducts of thruster firings, system venting emissions, etc. Attention is presently given to a self-contained optical contamination monitor, furnishing in-flight and/or real-time monitoring of VUV reflectivity and transmittance. The time-lining of measurement results with other spacecraft events will allow the direct evaluation of spacecraft operation effects on critical optical surfaces.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Optical system contamination: Effects, measurement, control; May 19, 1987 - May 22, 1987; Orlando, FL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    The detection and observation of meteoroid and space debris impact features on the Solar Max satellite (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of optical observations on the entire population of impact pits and holes discovered on nearly all of the returned parts of the Solar Maximum Mission satellite are described. Some statistically significant new results on impact dynamics are obtained as well as new number vs. size distributions for craters and holes ranging from 40 to 900 microns. The local spacecraft geometric shielding corrections are calculated and applied to the data. Some selected compositional results are presented which indicate that the Space Shuttle can be a source of impacting debris.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Lunar and Planetary Science Conference; Mar 14, 1988 - Mar 18, 1988; Houston, TX; United States
    Format: text
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    NASA TECHNICAL REPORTS
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