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  • 1
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    Test results of prototype two-phase reservoirs for the CAPL flight experiment (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Capillary Pumped Loop Flight Experiment (CAPL) was designed to test components being considered for inclusion in the Earth Observing System (EOS) instrument thermal control system. The thermal operating conditions of a capillary pumped loop (CPL) heat transport system are controlled by a two-phase reservoir. Three prototype two-phase reservoirs designed for use in microgravity applications were built to CAPL specifications and performance tested at NASA Goddard Space Flight Center using anhydrous ammonia as the working fluid. Test results for liquid expulsion rates and CPL operational control are presented for each reservoir.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 92-2888
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Vapor resistant arteries (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A vapor block resistant liquid artery structure for heat pipes. A solid tube artery with openings is encased in the sintered material of a heat pipe wick. The openings are limited to that side of the artery which is most remote from the heat source. The liquid in the artery can thus exit the artery through the openings and wet the sintered sheath, but vapor generated at the heat source is unlikely to move around the solid wall of the artery and reverse its direction in order to penetrate the artery through the openings. An alternate embodiment uses finer pore size wick material to resist vapor entry.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Vapor resistant arteries (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A vapor block resistant liquid artery structure for heat pipes. A solid tube artery with openings is encased in the sintered material of a heat pipe wick. The openings are limited to that side of the artery which is most remote from the heat source. The liquid in the artery can thus exit the artery through the openings and wet the sintered sheath, but vapor generated at the heat source is unlikely to move around the solid wall of the artery and reverse its direction in order to penetrate the artery through the openings. An alternate embodiment uses finer pore size wick material to resist vapor entry.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Thermal Vacuum Test Performance of the Hubble Space Telescope (HST) Wide Field Camera 3 (WFC3) Variable Conductance Heat Pipe Assembly (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Variable Conductance Heat Pipe (VCHP) Assembly of the HST Wide Field Camera 3 was subjected to thermal vacuum (TN) environmental testing. The test program included both maximum and minimum environments as well as simulated on-orbit cycling. Elements of the VCHP assembly included a VCHP, an optical bench cold plate with an imbedded constant conductance heat pipe, and a VCHP reservoir radiator with a proportionally controlled heater. The purpose of the test was to characterize and demonstrate the assembly s ability to control the temperature of the cold plate, which provides a stable thermal environment for the instrument s optical bench. This paper discusses the VCHP Assembly control performance and control authority during the dynamic hot and cold 90-minute orbit cycling test phases.
    Keywords: Quality Assurance and Reliability
    Type: SAE-2003-01-2459 , International Conference on Environmental Systems; Jul 07, 2003 - Jul 10, 2003; Vancouver, British Columbia; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    CPL Materials Life Cycle Test Facility (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Capillary Pumped Loop (CPL) Materials Life Cycle Test Facility at the Goddard Space Flight Center (GSFC) will identify the operational parameters controlling the performance of a CPL over an extended period of time. The primary purpose of the facility is to investigate the long-term chemical compatibility between the anhydrous ammonia working fluid and the CPL materials of construction. Chemical reactions occurring within the system may produce non-condensable gases or particulate debris that can lead to a degradation in system performance. Small liquid samples will be drawn from the system at specific time intervals and analyzed to check for the presence of non-condensable gases. Periodic maximum and minimum heat load tests will be performed on the CPL to monitor trends in the overall system performance.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: SAE PAPER 921406 , ; 7 p.|SAE, International Conference on Environmental Systems; Jul 13, 1992 - Jul 16, 1992; Seattle, WA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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