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  • 1
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    An investigation of the thermal radiation properties of certain spacecraft materials Final report (1962)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Thermal radiation analysis for anodized aluminum - anodizing process evaluation for optimum properties under space conditions for spacecraft temperature control
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-74772 , STL-8633-6014-SU-000
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Extended Development of Variable Conductance Heat Pipes (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A high-capacity vapor-modulated heat pipe was designed and tested. In 1977, a program was undertaken to use the aforementioned heat pipe to study protection from freezing-point failure, increase control sensitivity, and transient behavior under a wide range of operating conditions in order to determine the full performance potential of the heat pipe. A new concept, based on the vapor-induced-dry-out principle, was developed for passive feedback temperature control as a heat pipe diode. This report documents this work and describes: (1) the experimental and theoretical investigation of the performance of the vapor-modulated heat pipe; and (2) the design, fabrication and test of the heat pipe diode.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-152183 , TRW-31183-6001-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight data analysis and further development of variable-conductance heat pipes (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Continuing efforts in large gains in heat-pipe performance are reported. It was found that gas-controlled variable-conductance heat pipes can perform reliably for long periods in space and effectively provide temperature stabilization for spacecraft electronics. A solution was formulated that allows the control gas to vent through arterial heat-pipe walls, thus eliminating the problem of arterial failure under load, due to trace impurities of noncondensable gas trapped in an arterial bubble during priming. This solution functions well in zero gravity. Another solution was found that allows priming at a much lower fluid charge. A heat pipe with high capacity, with close temperature control of the heat source and independent of large variations in sink temperature was fabricated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-137782 , RR-1 , TRW-26263-6021-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Vapor-modulated heat pipe report. Flight data analysis and further development of variable-conductance heat pipes (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and testing of a heat pipe for spacecraft application is presented. The application in mind calls for heat loads up to 20 watts, a set-point temperature of 294K, and a sink that varies from -220K to nearly as high as the set-point. The overall heat pipe length is 137 cm. Two basically different mechanisms of achieving variable conductance in the pipe by vapor-flow throttling were studied. In one, the thermal resistance between the heat source and sink is due to a saturation-temperature drop corresponding to the vapor-pressure drop developed across the valve. In the other, the pressure difference across the valve induces capillary groove and wick dry out in an evaporation region, and thus results in an increased thermal resistance. This mechanism was selected for fabrication and testing. The pipe is a stainless-steel/methanol two-heat-pipe system. Results are presented and discussed. Engineering drawings and specifications of the pipe are shown.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146143 , TRW-26263-6015-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    High-temperature reflectance measurements with the paraboloid reflectometer. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: High temperature directional reflectance measurements of ablative materials as function of sample temperature using paraboloid reflectometer
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 68-25 , ; ACE(|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING; Jan 22, 1968 - Jan 24, 1968; NEW YORK, NY
    Format: text
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  • 6
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    Thermal radiative properties of solar sail film materials (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Techniques have been developed for controlling the temperature and enhancing the performance of metallized, ultrathin polymer film used as the sail material for the proposed Halley's Comet rendezvous solar sail vehicle. The coating technology development is described whereby film emissivity is increased sufficiently on one side to a point where the sail, in its cranking orbit, could go to a heliocentric distance of 0.25 AU and still operate within the temperature limits of the basic film material. This capability resulted in significant improvement in several mission performance parameters; e.g., a lengthened launch period through increased vehicle performance and more latitude in the selection of basic film candidates.
    Keywords: CHEMISTRY AND MATERIALS (GENERAL)
    Type: AIAA PAPER 78-852 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Electrostatic propulsion beam divergence effects on spacecraft surfaces, volume 3 (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tests were conducted to determine the effects of electrostatic propulsion beam divergence effects on spacecraft surfaces. The subjects discussed are: (1) sensitive surfaces on the ATS 6 spacecraft, (2) the cesium ion source and testing facility, (3) cesium ion effects on thermophysical properties, and (4) simulated charge-exchange ion exposure. The compatibility of the ATS 6 ion engine experiment with the engineering subsystems and other experiments aboard the ATS 6 spacecraft was analyzed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-136933 , TRW-11985-6003-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Heat pipe life and processing study (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The merit of adding water to the reflux charge in chemically and solvent cleaned aluminum/slab wick/ammonia heat pipes was evaluated. The effect of gas in the performance of three heat pipe thermal control systems was found significant in simple heat pipes, less significant in a modified simple heat pipe model with a short wickless pipe section. Use of gas data for the worst and best heat pipes of the matrix in a variable conductance heat pipe model showed a 3 C increase in the source temperature at full on condition after 20 and 246 years, respectively.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-159581 , TRW-32937-6001-TU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Flight data analysis and further development of variable-conductance heat pipes (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The work focuses on the mathematical modeling of three critical mechanisms of heat-pipe operation: (1) the effect that excess liquid has on heat-pipe performance; (2) the calculation of the dryout limit of circumferential grooves; (3) an efficient mathematical model for the calculation of the viscous-inertial interaction in the vapor flow. These mathematical models are incorporated in the computer program GRADE II, which is described.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-137953 , RR-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Heat Pipe Materials Compatibility (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental program to evaluate noncondensable gas generation in ammonia heat pipes was completed. A total of 37 heat pipes made of aluminum, stainless steel and combinations of these materials were processed by various techniques, operated at different temperatures and tested at low temperature to quantitatively determine gas generation rates. In order of increasing stability are aluminum/stainless combination, all aluminum and all stainless heat pipes. One interesting result is the identification of intentionally introduced water in the ammonia during a reflux step as a means of surface passivation to reduce gas generation in stainless-steel/aluminum heat pipes.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-135069 , TRW-26148-6004-RU-00 , GRC-E-DAA-TN10587
    Format: application/pdf
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