基于姿态敏感器的地球同步轨道卫星自主导航研究  

Attitude Sensor Based Autonomous Navigation Research For GEO Spacecrafts

作　　者：郭建新[1] 解永春[1] 

机构地区：[1]北京控制工程研究所,北京100080

出　　处：《航天控制》2003年第4期1-6,共6页Aerospace Control

基　　金：国家自然科学基金(69984007)

摘　　要：本文提出了一种基于姿态敏感器的地球同步轨道卫星自主导航方法,作为解决未来高轨道卫星自主运行的先决条件。在整个系统中,以包含摄动项的HILL 方程作为状态方程,根据由姿态敏感器给出的卫星本体相对于地球和另外两个空间天体的方位,推导出测量方程,进而用简化的推广 Kalman 滤波算法进行状态估计。仿真表明,该方法收敛速度快,精度较高,是一种可行的地球同步轨道卫星自主导航方法。In this paper, a method of autonomous navigation based upon attitude sensors for GEO satellite is presented as a prerequisite to realize autonomous operation of GEO satellites in the near future. In the autonmous navigation system, its state equation is HILL equation including perturbation terms and its measurement equation is derived from the orientation of the GEO satellite relative to the earth and other two stars in space, measured by attitude sen- sors. A simplified Expanded Kalman filter is used as the state estimator of the navigation sys- tem. The results of simulation show that the method is suitable for autonomous navigation of GEO satellites due to its fast convergence and good accuracy.

关 键 词：姿态敏感器 地球同步轨道卫星 自主导航方法 地面测控站 状态方程 滤波算法 数学仿真 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]