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A Contact Conductance Interface for a Space Constructable Heat Pipe Radiator
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English
Abstract
A connectable/disconectable thermal interface has been developed for the constructable radiator system under development at NASA-Johnson Space Center. A contact heat exchanger approach which involves pressurized clamping of a segmented cylindrical heat exchanger on the outside of a round heat pipe evaporator section was designed, fabricated, and tested. Dry metal-to-metal contact conductance heat transfer is utilized. Test results have indicated excellent contact conductances of up to 8500 w/m2°c (1500 Btu/ft2°F) at 2000 kPa (300 psi) clamping force. The feasibility and fabricability of the design have been demonstrated.
Citation
Oren, J. and Fleming, M., "A Contact Conductance Interface for a Space Constructable Heat Pipe Radiator," SAE Technical Paper 831101, 1983, https://doi.org/10.4271/831101.Also In
References
- Fletcher, L. S. “Thermal Conductance of Gasket Materials for Spacecraft Joints” AIAA Paper No. 73-49 January 1973
- Leach, J. W. “Joint Conductance Element Test for the Self Contained Heat Rejection Module Contact Heat Exchanger” Vought Corp. Report No. T211-RP-009 15 August 1974
- Oren, J. A. “Study of Thermal Management for Space Platform Applications” NASA CR-165238 December 1980