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Performance of the Spacelab Astro-2 Mission Integrated Radiator System
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English
Abstract
This paper presents the design, test, and flight performance of the Astro Integrated Radiator System, or IRS, a passive thermal control system which made its second Space Shuttle flight during March, 1995. The system was designed to provide thermal control for a cluster of ultraviolet telescopes which were mounted to an Instrument Pointing System (IPS) developed by the European Space Agency. Having no fluid piped to the payload over the gimbals of the IPS to provide heat transport, the thermal control of the telescopes and their supporting electronics had to be thermally autonomous, and the IRS was conceived to perform this task.
Citation
Hamner, R. and Watkins, H., "Performance of the Spacelab Astro-2 Mission Integrated Radiator System," SAE Technical Paper 961539, 1996, https://doi.org/10.4271/961539.Also In
References
- Humphries, W. R. Stallings R. D. Hamner R. M. Cotton J. A. “Performance of the Spacelab Astro-1 Mission Heat Pipe Radiator” SAE Technical Paper No. 851352 , 15th ICES San Francisco 1985
- Hamner, R. M. Hornsby L. S. “Flight Performance of the Spacelab Astro-1 Mission Integrated Radiator System” SAE Technical Paper No. 911589 , 21st ICES San Francisco 1991
- Hamner, R. M. Hornsby L. S. “Design and Performance of the Spacelab Astro-1 Mission Integrated Radiator System” 4th European Symposium on Space Environmental Control Systems Florence, Italy 21-24 October 1991