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Magellan Thermal Integration Analysis
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English
Abstract
The Space Shuttle Atlantis was launched on 5 May 1989 and, soon after, its pay-load, the Magellan Venus Radar Mapper, was successfully boosted toward Venus by an Inertial Upper Stage. Shuttle flights carrying payloads require a thermal integration analysis to predict and evaluate the integrated vehicle's thermal radiation exchange factors, environmental heat loads, and temperatures as a function of mission time. This was accomplished by using geometric and thermal mathematical models for hot and cold case mission timelines. This paper outlines the mission timeline and discusses these models, environments, and assumptions. Components that exceed their design temperature limits in the nominal missions are identified and discussed.
Authors
Citation
Bauer, S., "Magellan Thermal Integration Analysis," SAE Technical Paper 891603, 1989, https://doi.org/10.4271/891603.Also In
References
- “390 Node” Atmospheric Orbiter Midsection/Payload Bay Thermal Math Model Description (Model No. SSX002D) REV D, NASA September 1983
- Orbiter Midsection/Payload Bay Thermal Math Model De scription (Model No. SSX001D) REV D, NASA June 1983
- Boeing Doc. D290-10953-1 “IUS/TDRS-A STS-6 First Flight Thermal Model Report,” 28 June 1983
- ICD-B-81214 “(STS)/Inertial Upper Stage(IUS)/Magellan(MGN) Interface Control Document,” 12 November 1987
- Boeing Doc. D290-10871-9 “Final Post Flight Evaluation Report TDRS-C(IUS-7),” 16 December 1988