摘要
针对倾斜轨道小卫星必然会面对的光学姿态敏感器受阳光干扰的问题,分析太阳高度角的变化规律,提出了计算太阳高度角的经验公式,并在此基础上提出了平台偏航姿态机动方案,可以使光学姿态敏感器规避阳光干扰,并可以简化整星热控和帆板驱动设计,提高了整星的可靠性.
Considering the optic attitude sensor of inclined-orbit small satellite interfered by sunlight, the variation law of solar height angle is analyzed. For computing and analyzing easily, a handy experience formula of solar height angle is proposed. Based on the formula, a yaw-axis attitude maneuver scheme is presented, which can avoid sunlight interferer and make thermal control design and solar array drive law design conveniently.
出处
《空间控制技术与应用》
CSCD
北大核心
2016年第3期33-37,共5页
Aerospace Control and Application
基金
上海航天核攀资助项目(ZY2015-003-3)
关键词
倾斜轨道
太阳高度角
姿态机动
inclined-orbit
solar height angle
attitude maneuver
