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  • 1
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    Long term performance of the advanced thermal control flight experiment (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Advanced Thermal Control Flight Experiment (ATFE) is providing the first zero-g flight data for the performance of a thermal diode heat pipe and an electrical Feedback Controlled Heat Pipe (FCHP). The temperature stability derived from the melting and freezing of octadecane is also being evaluated in this experiment. Flight data for the different operational modes are compared to ground test data, and the performance of the individual components is analyzed. Also, the ATFE's long term behavior from launch through September 30, 1975, is evaluated. The temperature control capability of a thermal diode, phase change material, and FCHP was demonstrated over more than 500 days of flight operation and each of these components should be considered in future applications. Both the diode and FCHP transport more than 20 W in the normal and passive modes during maximum conditions. Up to 30 W has been carried by the FCHP when the auxiliary heater is applied. The "OFF-conductance" of the diode has improved substantially in flight. A 1.4 W decrease in backflow has been realized by more complete blockage. The variable conductance behavior of the FCHP is essentially unchanged with time and relative to ground tests. Degradation of the radiator and reservoir surfaces have resulted in a partial loss of control by the FCHP during normal mode operation; however, manual control at an elevated set point has demonstrated the FCHP's ability to provide regulated temperature control to within + or - 2 C. The same pipe when operated as a passive VCHP controlled at 35 + or - 10 C with the same test conditions.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: ESA Heat Pipes; p 629-643
    Format: text
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  • 2
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    Application of axial grooves to cryogenic variable conductance heat pipe technology (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Tests results obtained with an ATS axial groove aluminum extrusion adapted for use as a cryogenic thermal diode and/or a variable conductance heat pipe are presented. Ethane at a nominal operating temperature of 185 C was used as working fluid. In addition to both active and passive gas control, diode designs utilizing gas blockage or liquid trap were investigated. Specific requirements and performance parameters such as transient behavior, reservoir sizes, shutdown energy, etc., were evaluated. Results are also presented for tests where the liquid trap was used as a secondary heat pipe to demonstrate thermal switching with simultaneous heat pipe operation and diode shutdown.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: ESA Heat Pipes; p 183-195
    Format: text
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  • 3
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    ATS-6 - Flight performance of the Advanced Thermal Control Flight Experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Advanced Thermal Control Flight Experiment on ATS-6 was designed to demonstrate the thermal control capability of a thermal diode (one-way) heat pipe, a phase-change material for thermal storage, and a feedback-controlled heat pipe. Flight data for the different operational modes are compared to ground test data, and the performance of the components is evaluated on an individual basis and as an integrated temperature-control system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
    Format: text
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  • 4
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    ERTS-C (Landsat 3) cryogenic heat pipe experiment definition (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight experiment designed to demonstrate current cryogenic heat pipe technology was defined and evaluated. The experiment package developed is specifically configured for flight aboard an ERTS type spacecraft. Two types of heat pipes were included as part of the experiment package: a transporter heat pipe and a thermal diode heat pipe. Each was tested in various operating modes. Performance data obtained from the experiment are applicable to the design of cryogenic systems for detector cooling, including applications where periodic high cooler temperatures are experienced as a result of cyclic energy inputs.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-143797 , BK005-1009
    Format: application/pdf
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  • 5
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    HEPP - A low temperature Heat Pipe Experiment Package developed for flight on-board the Long Duration Exposure Facility /LDEF/ (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Heat Pipe Experiment Package (HEPP) is designed to provide a flight evaluation system for low temperature heat pipes. The HEPP will be flown aboard the Long Duration Exposure Facility which will be launched and retrieved as part of the Space Shuttle program. The experiment contains two heat pipes: an axially grooved fixed conductance heat pipe and a liquid blockage thermal diode. A phase change material canister is also integrated with a radiant cooler system. Additional hardware consists of supporting electrical equipment, including electronics for signal conditioning and command functions, a data recorder, and a hermetically sealed battery which powers the experiment. A thermal model was developed to simulate the behavior of the HEPP and a ground test program was conducted to verify the predicted performance of the equipment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-459 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
    Format: text
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  • 6
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    Development and test of two flexible cryogenic heat pipes (1976)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Results are presented for a comprehensive test program directed toward determining the physical and thermal performance of two flexible cryogenic heat pipes that can provide a highly efficient thermal link between a detector and a space radiator or other cooling system in spacecraft applications. A 100-200 K high-power heat pipe is tested with methane at 100-140 K while a 15-100 K low-temperature pipe is designed for operation with nitrogen and oxygen and is optimized for oxygen in the range 75-90 K. Parametric performance and design tradeoff studies are carried out to determine the optimum geometry and materials for the container and wicking systems. A spiral multiwrap wick in conjunction with braided bellows appears to be a workable solution to the problem of developing highly flexible heat transport devices for cryogenic applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 76-478 , Thermophysics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
    Format: text
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  • 7
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    Development of a low temperature phase change material package (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Test data obtained for a low temperature phase change material (PCM) canisters are presented. The canister was designed to provide up to 30 w-hrs of storage capacity at approximately -90 C with an overall thermal conductance which is greater than 8 w/deg C. N-heptane which is an n-paraffin and has a -90.6 C freezing point was used as the working fluid. The canister was fabricated from aluminum and has an aluminum honeycomb core. Its void volume permits service temperatures up to 70 C. Results obtained from component and system's tests indicate well defined melting and freezing points which are repeatable and within 1 C of each other. Subcooling effects are less than 0.5 C and are essentially negligible. Measured storage capacities are within 94 to 88% the theoretical.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 77-762 , Thermophysics Conference; Jun 27, 1977 - Jun 29, 1977; Albuquerque, NM
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  • 8
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    Axially grooved heat pipes - 1976 (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper summarizes the 'state-of-the-art' of axially grooved heat pipes. Applications are identified and the related heat pipe design and performance are defined. Recent developments in the analysis, design and fabrication of axially grooved hardware are also discussed. A mathematical model which predicts the hydrodynamic behavior and accounts for liquid recession, liquid/vapor shear interaction and 1-g puddle flow is also presented. Performance data for various fluids in the 100-500 K range is compared to predictions from the Groove Analysis Program (GAP). Finally, a simplified closed form solution which accounts for gravity effects, self-priming and composite pumping by the grooves as well as all of the hydrodynamic losses is also discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 77-747 , Thermophysics Conference; Jun 27, 1977 - Jun 29, 1977; Albuquerque, NM
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  • 9
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    Performance analysis of the advanced thermal control flight experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flight data for the different operational modes of the advanced thermal control flight experiment are presented and compared with ground-test data. Performance of the system with feedback control is compared to performance without such control, and performances of the individual components are analyzed. Finally, changes in performance from launch through March 31, 1975, are discussed and analyzed. All thermal control components are performing as predicted for the existing flight environment. However, the daily reservoir and radiator temperatures during peak solar input are greater than those experienced in ground acceptance tests. These increased temperatures have resulted in a loss of control by the feedback-controlled variable-conductance heat pipe for several hours around the period of maximum insolation. The higher temperatures are apparently due to contamination and/or degradation of the second-surface mirrors which cover the reservoir and radiator.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 75-727 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; May 27, 1975 - May 29, 1975; Denver, CO
    Format: text
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  • 10
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    Analysis of fourth sounding rocket heat pipe experiment, summary report (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An analysis was made of the cryogenic axial groove methane and axial groove nitrogen heat pipes. Data cover the establishment of reliable start-up and operational data for the cryogenic pipe and its reference control pipes, and requirements for and the applicability of cryogenic heat pipes to NASA coolers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145817
    Format: application/pdf
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