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  • 1
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    Space Environmental Testing at GSFC (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: One critical piece of information needed in the thermal design of all spacecraft are the thermal properties of the coatings and the determination of how those properties change due to the space environmental over the lifetime of a spacecraft. At the Goddard Space Flight Center (GSFC) we have the ability to measure the beginning of life (BOL) thermal properties of thermal control coatings such as solar absorptance, emittance as a function of temperature, conductivity and we can also determine how those properties will change over the lifetime of the spacecraft.
    Keywords: Space Radiation
    Type: LEGNEW-OLDGSFC-GSFC-LN-1249 , 2009 Contamination, Coatings and Materials Workshop; Jul 21, 2009 - Jul 23, 2009; Greenbelt, MD; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An Improved Formulation for Calorimetric Emittance Testing of Spacecraft Thermal Control Coatings (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft often really heavily on passive thermal control to maintain operating temperature. An important parameter in the spacecraft heat balance equation is the emittance of thermal control coatings as a function of coating temperature. One method for determining the emittance of spacecraft thermal control from elevated temperature to cryogenic temperatures relies on a calorimetric technique. The fundamental equation governing this test method can be found in numerous places in the literature and although it generally provides reasonable results, its formulation is based on a conceptual flaw that only becomes apparent when the sample temperature approaches the wall temperature during testing. This paper investigates the cause for this error and develops the correct formulation for calorimetric emittance testing. Experimental data will also be presented that illustrates the difference between the two formulations and the resulting difference in the calculated emittance.
    Keywords: Instrumentation and Photography
    Type: Protection of Materials and Structures From Space Environment; May 19, 2008 - May 23, 2008; Toronto; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Weathering of Thermal Control Coatings (2007)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft radiators reject heat to their surroundings. Radiators can be deployable or mounted on the body of the spacecraft. NASA's Crew Exploration Vehicle is to use body mounted radiators. Coatings play an important role in heat rejection. The coatings provide the radiator surface with the desired optical properties of low solar absorptance and high infrared emittance. These specialized surfaces are applied to the radiator panel in a number of ways, including conventional spraying, plasma spraying, or as an applique. Not specifically designed for a weathering environment, little is known about the durability of conventional paints, coatings, and appliques upon exposure to weathering and subsequent exposure to solar wind and ultraviolet radiation exposure. In addition to maintaining their desired optical properties, the coatings must also continue to adhere to the underlying radiator panel. This is a challenge, as new composite radiator panels are being considered as replacements for the aluminum panels used previously. Various thermal control paints, coatings, and appliques were applied to aluminum and isocyanate ester composite coupons and were exposed for 30 days at the Atmospheric Exposure Site of the Kennedy Space Center s Beach Corrosion Facility for the purpose of identifying their durability to weathering. Selected coupons were subsequently exposed to simulated solar wind and vacuum ultraviolet radiation to identify the effect of a simulated space environment on the as-weathered surfaces. Optical properties and adhesion testing were used to document the durability of the paints and coatings. The purpose of this paper is to present the results of the weathering testing and to summarize the durability of several thermal control paints, coatings, and appliques to weathering and postweathering environments.
    Keywords: Composite Materials
    Type: 07ICES-40 , 37th International Conference on Environmental Systems; Jul 09, 2007 - Jul 12, 2007; Chicago, IL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Optical Properties of Thermal Control Coatings After Weathering, Simulated Ascent Heating, and Simulated Space Radiation Exposure (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft radiators reject heat to their surroundings and coatings play an important role in this heat rejection. The coatings provide the combined optical properties of low solar absorptance and high infrared emittance. The coatings are applied to the radiator panel in a number of ways, including conventional spraying, plasma spraying, or as an applique. Not designed for a terrestrial weathering environment, the durability of spacecraft paints, coatings, and appliques upon exposure to weathering and subsequent exposure to ascent heating, solar wind, and ultraviolet radiation was studied. In addition to traditional aluminum panels, new isocyanate ester composite panels were exposed for a total of 90 days at the Atmospheric Exposure Site of Kennedy Space Center's (KSC) Beach Corrosion Facility for the purpose of identifying their durability to weathering. Selected panel coupons were subsequently exposed to simulated ascent heating, solar wind, and vacuum ultraviolet (UV) radiation to identify the effect of a simulated space environment on as-weathered surfaces. Optical properties and adhesion testing were used to document the durability of the paints, coatings, and appliques.
    Keywords: Nonmetallic Materials
    Type: NASA/TM-2008-215259 , E-16525 , 39th Central Regional Meeting of the American Chemical Society; Jun 10, 2008 - Jun 14, 2008; Columbus, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The evaluation of GOES black paint materials (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The purpose of this paper is to study the contamination effect of black paint materials on the GOES instrument performance. The GOES spacecraft materials were originally selected for their low outgassing properties. Samples of the materials were tested according to the ASTM E-595 test method to fulfill the total mass loss and collected volatile condensable materials criteria for traditional spacecraft material selection. Due to the instrument design, the cavity will experience high temperatures during operation greater than the specified temperature in the ASTM test. As a result of this high cavity temperature, normally stable paint materials on the painted surface may severely outgas even though they have passed the ASTM test. Further enhancement of the contaminant remaining on the mirror by UV irradiation is also a great consideration. This concern prompted an investigation into the outgassing characteristics of the black paints at the predicted operating temperatures.
    Keywords: NONMETALLIC MATERIALS
    Type: AIAA PAPER 92-2155 , AIAA Materials Specialist Conference; Apr 16, 1992 - Apr 17, 1992; Dallas, TX; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Space Environmental Testing at GSFC (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents an overview of space environmental testing at NASA Goddard Space Flight Center. The contents include: 1) Solar Absorptance measurements; 2) Emittance measurements; 3) Transient Calorimetric Technique; 4) Electrostatic charge testing; 5) UV degradation testing; 6) Solar Wind Facility; and 7) Solar Wind testing.
    Keywords: Space Radiation
    Type: 2009 Contamination, Coatings and Materials Workshop; Jul 21, 2009 - Jul 23, 2009; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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