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  • 1
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    Low-temperature heat pipe experiment package (HEPP) for LDEF (S1001) (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The principal objectives of the experiment are to determine zero-g start-up performance for conventional and diode low temperature heat pipes, to evaluate heat pipe performance in zero-g for an extended period of time, to determine zero-g transport capability of each heat pipe, and to determine diode operation, including forward conductance, turndown ratio, and transient behavior. Two heat pipes, a fixed conductance transporter heat pipe and a thermal diode heat pipe, are coupled with a radiant cooler system. Both pipes are charged with ethane. Also integrated with the radiator is a phase change material (PCM) canister which provides temperature stability during transport tests. N-heptane, which has a melting/freezing point of 182 K, is used as the PCM. The high heat capacity (28 W-hr of latent heat) provided by the canister permits high power heat pipe testing at constant temperature.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Langley Research Center Long Duration Exposure Facility (LDEF); p 70-73
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The degradation of alzak by short wavelength ultraviolet radiation (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The changes in reflectance of thermal aluminum coating samples exposed to different irradiating utraviolet wavelengths are discussed. It is shown that the coating is damaged faster and further by 180 to 210 in radiation than by Lyman alpha radiation. On an equivalent incident energy basis, Lyman alpha does less damage than 180 to 210 nm radiation. Above 300 nm no degradation is observed for long exposures and below 300 nm increasing degradation with decreasing wavelength is found. It is concluded that Lyman alpha radiation need not be included in laboratory testing of this thermal coating for spacecraft structures.
    Keywords: PHYSICS, GENERAL
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 59-66
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Thermal vacuum and solar simulation test of the Explorer XXXVIII spacecraft (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Explorer 38 critical component equilibrium temperature tests in thermal vacuum chamber using modified solar simulator, noting agreement with model
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 69-999 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AMERICAN SOCIETY FOR TESTING AND MATERIALS, AND INST. OF ENVIRONMENTAL SCIENCES, SPACE SIMULATION CONFERENCE, 4TH; Sep 08, 1969 - Sep 10, 1969; LOS ANGELES, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Design and evaluation of a rotating variable conductance heat pipe system (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Analysis of the Dynamics Explorer high orbiter spacecraft showed that the proposed louver system, along with existing radiator heat rejection areas on the S/C surface were insufficient to safely control the S/C's thermal excursions caused by highly varying internal power levels and solar input angles. A variable conductance heat pipe system in conjunction with a conventional radial heat pipe system was designed, built, tested, and shown to resolve this problem. The conventional pipes, radial, spinning at 10 rpm were required to carry 35 watts each after experiencing despin from 80 rpm. The VCHPs attached to the radial pipes at the S/C perimeter distributed the excess energy via a finned radiator attached around the S/C's center.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-422 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The use of a thermal utility with space-platform-mounted instruments (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A thermal utility is a high-capacity heat transport system that serves as a common, temperature-controlled heat sink or source to more than one payload. The feasibility of using a thermal utility for space-platform-mounted instruments which have a range of temperature level and heat rejection requirements is examined and significant design parameters are identified. A baseline, pumped, two-phase heat transport system has been defined for NASA's proposed Space Platform, and its capability to satisfy the thermal requirements of a range of multidisciplinary instruments has been assessed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-1114 , Thermophysics Conference; Jun 23, 1981 - Jun 25, 1981; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
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