基于星光大气折射的卫星自主轨道确定

本文研究了利用星敏感器进行卫星轨道确定的自主导航方案。这种自主导航方案完全利用高精度的CCD星敏感器，以及大气对星光折射的数学模型及误差补偿方法，精确敏感地平，从而实现航天器的精确定位。以某太阳同步轨道卫星为背景，针对本文给出的星光折射光的卫星导航方案，结合推广的卡尔曼滤波算法，使用模拟数据进行了仿真研究，定位精度为38m。仿真结果说明，星光折射角的测量误差和大气折射模型的不确定性是影响导航精度的主要因素。

Autonomous orbit determination for earth satellites by starlight atmospheric refraction

An approach of autonomous navigation for satellites is described in this paper using refraction measurements of starlight passing through the upper atmosphere.An Extended Kalman Filter (EKF) is designed to estimate the satellites' position and velocity.Simulation for a sun-synchronous orbit satellite is done.Results show that the satellite's position accuracy is about 0.038km.Moreover,results show that the measurement error of starlight refraction angle and the uncertainty of the atmospheric refraction model are two principal factors deteriorating the navigation accuracy.