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タイトルElectrostatic protection of the Solar Power Satellite and rectenna
本文(外部サイト)http://hdl.handle.net/2060/19800014859
著者(英)Freeman, J. W.; Reiff, P. H.; Haymes, B.; Bohannon, J.; Cooke, D.; Few, A. A., Jr.
著者所属(英)Rice Univ.
発行日1979-05-01
言語eng
内容記述Several features of the interactions of the solar power satellite (SPS) with its space environment were examined theoretically. The voltages produced at various surfaces due to space plasmas and the plasma leakage currents through the kapton and sapphire solar cell blankets were calculated. At geosynchronous orbit, this parasitic power loss is only 0.7%, and is easily compensated by oversizing. At low-Earth orbit, the power loss is potentially much larger (3%), and anomalous arcing is expected for the EOTV high voltage negative surfaces. Preliminary results of a three dimensional self-consistent plasma and electric field computer program are presented, confirming the validity of the predictions made from the one dimensional models. Magnetic shielding of the satellite, to reduce the power drain and to protect the solar cells from energetic electron and plasma ion bombardment is considered. It is concluded that minor modifications can allow the SPS to operate safely and efficiently in its space environment. The SPS design employed in this study is the 1978 MSFC baseline design utilizing GaAs solar cells at CR-2 and an aluminum structure.
NASA分類LAUNCH VEHICLES AND SPACE VEHICLES
レポートNO80N23348
NASA-CR-161438
権利No Copyright
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/172609


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