摘要
针对高分七号(GF-7)卫星控制分系统高精度姿态确定、姿态控制和快速机动的需求,文章采用星敏感器相对基准标定,将甚高精度星敏感器与前后视相机进行一体化安装的布局方式,并采用了数传天线轨迹平滑和干扰力矩补偿算法控制天线,采用高刚度高稳定度太阳翼驱动机构(SADA)控制太阳翼,从而实现了卫星的高精度姿态确定和高稳定度姿态控制。经在轨验证,结果表明:姿态稳定度小于0.00006(°)/s,优于姿态控制分系统的指标要求,可为遥感卫星姿态控制分系统设计提供参考。
According to the need of high accuracy of attitude determination and control,and fast maneuver for the GF-7 satellit attitude control subsystem,calibrating the relative reference of star sensor and an integration distribution of payload and very high precision star sensors are designed in this paper.High stability of three-axis control is realized by adopting a very high stability solar array drive assembly(SADA)system,and using DTA(data transmission antenna)trajectory planning and the feedforward compensation of DTA disturb torque.Based on on-orbit data of GF-7 satellite,the estimated attitude stability is less than 0.00006(°)/s,highly superior to the index of the attitude control subsystem.Therefore,the scheme of this attitude control subsystem provides a reference for other satellites.
作者
刘洁
王淑一
陆栋宁
陈超
LIU Jie;WANG Shuyi;LU Dongning;CHEN Chao(Beijing Institute of Control Engineering,Beijing 100094,China)
出处
《航天器工程》
CSCD
北大核心
2020年第3期89-95,共7页
Spacecraft Engineering
基金
国家重大科技专项工程。
