基于GPS的低轨伴飞卫星自主导航轨道确定

An Orbit Determination Method Based on GPS for Autonomous Navigation of Flyaround Satellite

对基于EKF算法的相对导航滤波器和基于全球卫星定位系统(GPS)伪距测量的伴飞星定轨进行了研究。用几何法与相对动力学方法联合获得目标星轨道信息,给出了伴飞卫星伪距测量定位的模型。仿真结果表明:该定轨方法可用于低轨卫星实时定位导航,定轨精度较高。

The orbit determination for flyround satellite based on extended Kalman filtering （EKF） relative navigation algorithm and GPS pseudo-range observations positioning was studied in this paper. The target satellite information was obtained by the geometry and relative dynamics, and the positioning model of pseudo-range observations for the flyround satellite was established, The simulation results showed that this method would be used in the fits real-time orientation and navigation with high positioning accuracy.