一种同步自旋卫星姿态控制优化方法  

An Optimization Method of Attitude Control for Spin-Stabilized Geostationary Satellites

作　　者：李全军[1] 袁勇[1] 李建勇[1] 赵亮[1] 

机构地区：[1]西安卫星测控中心,西安710043

出　　处：《飞行器测控学报》2014年第6期530-534,共5页Journal of Spacecraft TT&C Technology

摘　　要：根据同步自旋卫星姿态的运动规律以及自旋卫星姿态的长期实测数据,建立了姿态变化规律方程,采用最小二乘方法求解姿态变化方程,实现对自旋卫星姿态预测,预测误差小于0.05°。针对目前工程应用中姿态保持周期短的问题,结合姿态及轨道倾角变化规律,建立目标姿态选取的约束方程,并利用投影梯度法求解约束方程,寻求姿态保持时间长的姿态控制目标。实际应用结果表明:该方法可以延长姿态控制周期,使自旋卫星姿态保持周期达到1a。An equation of attitude variation is established based on the attitude motion of spin-stabilized geostationary satellites and long term measurement data. The equation of attitude variation is deduced by least squares. According to the equation, the trend of change of attitude can be predicted and the error of the predicted attitude is less than 0.05°. Based on the variation of attitude and orbit inclination, a constraint equation of target attitude is established to solve the problem of short attitude keeping period in engineering applications. Projection gradient method is used to solve the constraint equation and target attitude of long keeping period is found. Practical application results show that the method prolongs the period of attitude control and the period of attitude control is up to one year for spin- stabilized satellites.

关 键 词：自旋稳定卫星 姿态控制 目标姿态 姿态保持周期 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]