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.
出处
《航天控制》
CSCD
北大核心
2003年第4期1-6,共6页
Aerospace Control
基金
国家自然科学基金(69984007)
