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  • 1
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    Techniques associated with thermal-vacuum testing of the OAO C heat pipes (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanical problems associated with the testing of two heat pipes installed in the OAO C spacecraft are described. The test problems discussed concern the specially designed heat removal devices, the mobile tilt table, the table position indicator, and the heat input machanisms. It was determined that the techniques used were adequate for thermal-vacuum testing of heat pipes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-6875 , G-1065
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Heat pipe investigations (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The OAO-C spacecraft has three circular heat pipes, each of a different internal design, located in the space between the spacecraft structural tube and the experiment tube, which are designed to isothermalize the structure. Two of the pipes are used to transport high heat loads, and the third is for low heat loads. The test problems deal with the charging of the pipes, modifications, the mobile tilt table, the position indicator, and the heat input mechanisms. The final results showed that the techniques used were adequate for thermal-vacuum testing of heat pipes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-66072 , X-322-72-153
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Techniques associated with thermal-vacuum testing of the OAO-C heat pipes (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanical problems associated with testing the two high-heat load pipes are discussed. One of these pipes was tested three times before being accepted. The first test resulted in the discovery of non-condensable hydrogen gas, which prevented the pipe from functioning properly. The second test was a repeat of the first, to see if all the gas had been removed. The third test was to see if any changes had occurred to the pipe as a result of saddle modifications. Saddle modifications were necessary because the epoxy binding agent between the saddles and the pipe had decomposed during the testing. The test problems discussed deal with the specially designed heat-removal devices, the mobile tilt table, the table position indicator, and the heat input mechanisms, all of which were necessary to conduct a high-heat load, thermal-vacuum test. The final results showed that the techniques used were adequate for thermal-vacuum testing of heat pipes.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: PAPER-80 , Space Simulation; p 933-946
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Heat-pipe sensor for remote leveling (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: System gives level readings in inaccessible areas. Level sensor is equipped with three thermocouples used to measure temperature differences that arise when pipe is tilted. When platform on which pipe is resting is level, three thermocouple recordings are identical. When readings are unequal, platform is leveled by remote control. System can replace expensive optical equipment and can function in cold, vacuum, and hot humid environments that produce nonlinear expansion and contraction in conventional equipment. Other advantages include low cost, no moving parts, and operation in toxic environments.
    Keywords: MACHINERY
    Type: GSC-12095 , NASA Tech Briefs (ISSN 0145-319X); 5; 2; P. 219
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Design and evaluation of a rotating variable conductance heat pipe system (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Analysis of the Dynamics Explorer high orbiter spacecraft showed that the proposed louver system, along with existing radiator heat rejection areas on the S/C surface were insufficient to safely control the S/C's thermal excursions caused by highly varying internal power levels and solar input angles. A variable conductance heat pipe system in conjunction with a conventional radial heat pipe system was designed, built, tested, and shown to resolve this problem. The conventional pipes, radial, spinning at 10 rpm were required to carry 35 watts each after experiencing despin from 80 rpm. The VCHPs attached to the radial pipes at the S/C perimeter distributed the excess energy via a finned radiator attached around the S/C's center.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-422 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Phenomena associated with bench and thermal-vacuum testing of super conductors - Heat pipes. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Test failures of heat pipes occur when the functional performance is unable to match the expected design limits or when the power applied to the heat pipe (in the form of heat) is distributed unevenly through the system, yielding a large thermal gradient. When a thermal gradient larger than expected is measured, it normally occurs in the evaporator or condenser sections of the pipe. Common causes include evaporator overheating, condenser dropout, noncondensable gas formation, surge and partial recovery of evaporator temperatures, masking of thermal profiles, and simple malfunctions due to leaks and mechanical failures or flaws. Examples of each of these phenomena are described along with corresponding failure analyses and corrective measures.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Annual Technical Meeting on Realism in environmental testing and control; Apr 02, 1973 - Apr 05, 1973; Anaheim, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Heat pipe investigations (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques associated with thermal-vacuum and bench testing, along with flight testing of the OAO-C spacecraft heat pipes are outlined, to show that the processes used in heat transfer design and testing are adequate for good performance evaluations.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7219 , G-7311
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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