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  • 1
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    Cryogenic Two-Phase Flight Experiment: Results overview (1995)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This paper focuses on the flight results of the Cryogenic Two-Phase Flight Experiment (CRYOTP), which was a Hitchhiker based experiment that flew on the space shuttle Columbia in March of 1994 (STS-62). CRYOTP tested two new technologies for advanced cryogenic thermal control; the Space Heat Pipe (SHP), which was a constant conductance cryogenic heat pipe, and the Brilliant Eyes Thermal Storage Unit (BETSU), which was a cryogenic phase-change thermal storage device. These two devices were tested independently during the mission. Analysis of the flight data indicated that the SHP was unable to start in either of two attempts, for reasons related to the fluid charge, parasitic heat leaks, and cryocooler capacity. The BETSU test article was successfully operated with more than 250 hours of on-orbit testing including several cooldown cycles and 56 freeze/thaw cycles. Some degradation was observed with the five tactical cryocoolers used as thermal sinks, and one of the cryocoolers failed completely after 331 hours of operation. Post-flight analysis indicated that this problem was most likely due to failure of an electrical controller internal to the unit.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: The 1995 Shuttle Small Payloads Symposium; p 111-123
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Development and test results of a two-phase reservoir for thermal transport systems used in micro-gravity (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the development and testing of a two-phase fluid reservoir for use in advanced thermal control systems designed for space applications. The aim of this development is to construct a highly reliable reservoir with the capability of controlling the saturation temperature of the system working fluid. The design considerations are described along with the methods of achieving the operational requirements. In addition, results from the initial testing of the prototype are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: SAE PAPER 911591
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A study of high-temperature heat pipes with multiple heat sources and sinks. I - Experimental methodology and frozen startup profiles. II - Analysis of continuum transient and steady-state experimental data with numerical predictions (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Experimental profiles for heat pipe startup from the frozen state were obtained, using a high-temperature sodium/stainless steel pipe with multiple heat sources and sinks to investigate the startup behavior of the heat pipe for various heat loads and input locations, with both low and high heat rejection rates at the condensor. The experimental results of the performance characteristics for the continuum transient and steady-state operation of the heat pipe were analyzed, and the performance limits for operation with varying heat fluxes and location are determined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME, Transactions, Journal of Heat Transfer (ISSN 0022-1481); 113; 1003-101
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Flight Test Results for the HST Orbital Systems Test (HOST) Capillary Pump Loop Cooling System (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Near Infrared Camera and Multi Object Spectrometer (NICMOS) was installed in the Hubble Space Telescope (MST) in February 1997. Shortly thereafter, the instrument experienced a thermal short in its solid nitrogen dewar system which will significantly shorten the instrument's useful life. A reverse Brayton cycle mechanical refrigerator will be installed during the Third Servicing Mission (SM3) to provide cooling for the instrument, and thereby extend its operations. A Capillary Pump Loop (CPL) and radiator system was designed, built and tested to remove up to 500 watts of heat from the mechanical cryocooler and its associated electronics. The HST Orbital Systems Test (HOST) platform was flown on the Space Shuttle Discovery (STS-95) as a flight demonstration of the cryocooler system, CPL control electronics, and the CPL/Radiator. This paper will present the flight test results and thermal performance of the CPL system in detail.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: 99ES-85 , Environmental Systems; Jul 12, 1999 - Jul 15, 1999; Denver, CO; United States
    Format: text
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    NASA TECHNICAL REPORTS
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