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Thermal Design of the Lunar Exploring Spacecraft
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Abstract
The thermal design of the LUNAR-A spacecraft, investigating the internal structure of the moon, is a challenge due to the widely varying thermal environments. A passive thermal control philosophy of radiators, multilayer insulation (MLI) and heaters was used for the LUNAR-A thermal design. Verification of the design was performed separately for the major spacecraft modules which consisted of a main structure, a propulsion subsystem and penetrators. As consequence, acceptable thermal performance can be expected for all phases of the mission. This paper describes the thermal design, analysis, thermal model testing and in-orbit temperature predictions.
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Ohnishi, A., Kobayashi, Y., Matsufuji, Y., Miyazaki, S. et al., "Thermal Design of the Lunar Exploring Spacecraft," SAE Technical Paper 972469, 1997, https://doi.org/10.4271/972469.Also In
References
- “NASA Space Vehicle Design Criteria (Environment) Lunar Surface Models” May 1969
- Smith Robert E, West George S. “Space And Planetary Environment Criteria Guidelines for Use in Space Vehicle Development, 1982 Revision (Volume 1)” NASA Technical Memorandum 82478 1983
- Yamakawa Hiroshi Kawaguchi Junichiro Nakajima Takashi Terada Hiroshi Ogasawara Masahiro Matsuoka Masatoshi “LUNAR-A Trajectory Description” ISTS '94-Yokohama May 1994