基于太阳敏感器的静止轨道卫星轨道估计方法研究  

Sun Sensor-Based Orbit Position Estimating Method for GEO Satellites

作　　者：徐菁宇[1] 高益军[1] 

机构地区：[1]北京控制工程研究所,北京100190

出　　处：《空间控制技术与应用》2009年第6期41-44,共4页Aerospace Control and Application

摘　　要：为解决目前通过星上配置敏感器进行地球同步轨道卫星自主轨道估计的问题,利用太阳敏感器和红外地球敏感器的测量信息进行轨道估计.根据地球静止轨道的特点,结合Hill方程,利用太阳敏感器和红外地球敏感器的测量信息以及轨道的摄动特性,建立导航系统的状态方程和测量方程.数学仿真结果表明,该方法可以较准确地估计出卫星的经度漂移,是一种可行的地球同步轨道卫星自主导航方法.In order to estimate orbit position of GE0 satellites using existing on-board equipments, this paper describes the system composed of sun sensors and earth sensors. According to nature of orbit of GEO sat- ellites combined with Hill equation, state equations and measurement equations of this system are established by using measurement information from sun sensors and earth sensors, as well as orbit perturbation characteristics. Simulation results show that longitude＇ s excursion of the satellite can be accurately estimated by this method, and it is a feasible autonomous navigation method for GEO satellites

关 键 词：静止轨道卫星 太阳敏感器 红外地球敏 感器 轨道估计 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]