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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (4)
  • 2020-2022
  • 2005-2009
  • 1990-1994  (4)
  • 1990  (4)
  • 1
    Publication Date: 2013-08-31
    Description: Future NASA space missions include the possibility of manned landings and exploration of Mars. Environmental and operational constraints unique to Mars must be considered when selecting and designing the power system to be used on the Mars surface. A technique is described which was developed to simulate the deposition of dust on surfaces. Three kinds of dust materials were studied: aluminum oxide, basalt, and iron oxide. The apparatus was designed using the Stokes and Stokes-Cunningham law for particle fallout, with additional consideration given to particle size and shape. Characterization of the resulting dust films on silicon dioxide, polytetrafluoroethylene, indium tin oxide, diamondlike carbon, and other surfaces are discussed based on optical transmittance measurements. The results of these experiments will guide future studies which will consider processes to remove the dust from surfaces under Martian environmental conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Goddard Space Flight Center, 16th Space Simulation Conference Confirming Spaceworthiness Into the Next Millennium; p 447-456
    Format: application/pdf
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  • 2
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    In:  Other Sources
    Publication Date: 2013-08-29
    Description: Viewgraphs and discussion on agent-independent planning are presented. Topics covered include: definitions; Space Station Freedom robotics environment; transition from crewmember to robots; agent-independent planning system flow; independence between plans and agents; existing testbed; benefits of approach; and directions of future research.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington, Technology for Space Station Evolution. Volume 4: Power Systems(Propulsion)Robotics; p 445-461
    Format: text
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  • 3
    Publication Date: 2019-06-28
    Description: The principles of the operation of plasma sources for the neutralization of the surface of a spacecraft traveling in the presence of hot plasma are discussed with special attention given to the hollow-cathode-based plasma contactors. Techiques are developed that allow the calculation of the potentials and particle densities in the near environment of a hollow cathode plasma contactor in both the test tank and the LEO environment. The techniques and codes were validated by comparison of calculated and measured results.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 90-1556
    Format: text
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  • 4
    Publication Date: 2015-12-15
    Description: Dust elevated in local or global dust storms on the Martian surface could settle on photovoltaic (PV) surfaces and seriously hamper their performance. Using a recently developed technique to apply a uniform dust layer, PV surface materials were subjected to simulated Martian winds in an attempt to determine whether natural aeolian processes on Mars would sweep off the settled dust. Three different types of dust were used. The effects of wind velocity, angle of attack, height above the Martian surface, and surface coating material were investigated. It was found that arrays mounted on an angle of attack approaching 45 deg show the most efficient clearing. Although the angular dependence is not sharp, horizontally mounted arrays required much higher wind velocities to clear off the dust. From this test it appears that the arrays may be erected quite near the ground, but previous studies have suggested that saltation effects can be expected to cause such arrays to be covered by soil if they are set up less than about a meter from the ground. Particle size effect appear to dominate over surface chemistry in these experiments, but additional tests are required to confirm this.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Goddard Space Flight Center, 16th Space Simulation Conference Confirming Spaceworthiness Into the Next Millennium; p 379-396
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