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Contact Conductance Evaluation for A Full Scale Space Erectable Radiator Pressurized Interface
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English
Abstract
The baseline thermal control configuration for the Space Station Freedom includes a contact heat exchanger to provide efficient heat transfer between the two-phase thermal bus heat collection/delivery system and the radiator panel heat rejection system. The contact heat exchanger provides a dry interface for a modular radiator system with easy on-orbit panel replacement. July 1988 testing of the Space Erectable Radiator System (SERS) at NASA-JSC provided thermal/vacuum data for three full-scale prototype units of a pressurized dry contact heat exchanger design. Derived contact conductance values agreed with predictions and previous element tests and demonstrated high conductance for relatively low pressure levels. A limited amount of data was also obtained below the operating pressure, resulting in contact conductance trends with respect to interface pressure.
Citation
Duschatko, R., "Contact Conductance Evaluation for A Full Scale Space Erectable Radiator Pressurized Interface," SAE Technical Paper 891463, 1989, https://doi.org/10.4271/891463.Also In
References
- Lieblein, S. “Analysis of Temperature Distribution and Radiant Heat Transfer Along a Rectangular Fin of Constant Thickness,” NASA TN D-196 November 1959
- Voss, F.E. “Thermal Contact Conductance of Pressurized Surfaces,” AIAA-88-0467 January 1988
- Oren, J. Fleming, M. “A Contact Conductance Interface for a Space Constructable Heat Pipe Radiator,” SAE 831101 1983