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  • 1
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    Dynamic Rheological Studies of Coagulation and Fibrinolysis (1979)
    American Institute of Physics
    Details
    Publication Date: 1979-12-01
    Print ISSN: 0148-6055
    Electronic ISSN: 1520-8516
    Topics: Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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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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    NASA TECHNICAL REPORTS
  • 3
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    Heat pipes for spacecraft temperature control: An assessment of the state-of-the-art (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Spacecraft applications that require the efficient cooling of high-powered components, the precise temperature control of sensitive electronic and optical components, and the protection of cooled components from temporary, adverse environmental conditions are increasing. Heat pipes using gas, vapor, liquid, or voltage control to provide variable conductance or diode thermal behavior have been and are continuing to be developed to meet increasingly difficult requirements. The various control techniques are critically evaluated using characteristic features and properties, including heat transport capability, volume and mass requirements, complexity and ease of fabrication, reliability, and control characteristics. As a result, advantages and disadvantages of specific approaches are derived and discussed. Using four development levels, the state-of-the-art of the various heat pipe temperature control techniques is assessed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: ESA Heat Pipes; p 167-181
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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    Heat pipes for spacecraft temperature control: An assessment of the state-of-the-art (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Various heat pipe temperature control techniques are critically evaluated using characteristic features and properties, including heat transport capability, volume and mass requirements, complexity and ease of fabrication, reliability, and control characteristics. Advantages and disadvantages of specific approaches are derived and discussed. Using four development levels, the state of-the-art of the various heat pipe temperature control techniques is assessed. The need for further research and development is discussed and suggested future efforts are projected.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-73096
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    "Thermal-diode" heat pipe (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Device transfers heat in one direction and blocks heat transfer in opposite direction.
    Keywords: MECHANICS
    Type: ARC-10997 , NASA Tech Briefs (ISSN 0145-319X); 1; 2; P. 237
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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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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    NASA TECHNICAL REPORTS
  • 8
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    A variable conductance heat pipe flight experiment - Performance in space (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Ames Heat Pipe Experiment (AHPE) is a variable conductance heat pipe/radiator system which was launched aboard the OAO-C spacecraft in August, 1972. All available flight data was reviewed and those from a few orbits were selected for correlation with predictions from an analytical model of the system. The principal conclusion of this study is that gas controlled variable conductance heat pipes can perform reliably for long time periods in the space environment and can effectively provide temperature stabilization for spacecraft electronics. Furthermore, the performance of such systems can be adequately predicted using existing analysis tools.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 75-725 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; May 27, 1975 - May 29, 1975; Denver, CO
    Format: text
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    NASA TECHNICAL REPORTS
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