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タイトルThe Small Explorer power system electronics
著者(英)Temkin, D.; Ahmad, A.; Culver, H.; Dakermanji, G.; Carlsson, U.; Rodriguez, G. E.
著者所属(英)NASA Goddard Space Flight Center
発行日1991-08-01
言語eng
内容記述The power system electronics for the NASA Goddard Space Flight Center Small Explorer Satellites are intended to satisfy various planned missions. The selected topology is a direct energy transfer (DET) system with the battery connected directly to the bus. The shunt control technique is a linear sequential full shunt which provides a simple solar array interface and can support both 3 axis stabilized and spinner satellites. In addition, it can meet stringent electromagnetic interference requirements which are expected on some Small Explorer Missions. The Power Systems Electronics (PSE) performs battery charge control using both temperature compensated charge/discharge ratio ampere hour integration and voltage-temperature control. The PSE includes all the circuits needed to perform telemetry and command functions using an optical MIL-STD-1773 interface.
NASA分類SPACECRAFT PROPULSION AND POWER
レポートNO92N13173
権利Copyright, Distribution within the U.S. granted by agreement
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/231781


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