微小卫星无姿控下太阳电池阵输出功率研究  

Research of solar array output for the minisatellite without attitude control

作　　者：林君毅[1] 尹兴月[1] 

机构地区：[1]中国电子科技集团公司第十八研究所,天津300384

出　　处：《电源技术》2012年第10期1478-1480,共3页Chinese Journal of Power Sources

摘　　要：微小卫星多采用体装式太阳电池阵,运行在100~1 000 km的轨道。卫星的飞行姿态对太阳电池阵的输出功率有重要影响。对于无姿态控制的微小卫星,分析了不同条件下太阳电池阵的功率输出。针对卫星在轨飞行,预计了太阳电池阵的输出功率及变化规律,为卫星功率计算提供了计算依据。The minisatellites operate in orbits of around 100 km to 1 000 km above the Earth＇s surface,powered by body mounted solar array.The output of the solar array was related to the minisatellite＇s attitude.For the minisatellite without attitude control,the output of the solar array was analyzed,and the law of change of output in-orbit was also predicted,which was important to the power analysis for minisatellite.

关 键 词：微小卫星 太阳电池阵 功率 姿态 

分 类 号：TM914[电气工程—电力电子与电力传动]