基于摄动轨道的卫星自主天文导航仿真研究

针对星光折射间接敏感地平的卫星自主天文导航方法，利用推广的卡尔曼滤波方法进行仿真研究。为了准确建立运动模型，在系统方程中引入了非球形地球引力中的二阶带谐项；在考虑具有指数密度的球状分层大气的基础上，建立了以星光视高度为观测量的量测方程。在建立了推广的卡尔曼滤波方程后，文章进行了计算机仿真，并对仿真结果进行了详细的误差分析，结果表明基于摄动轨道的星光折射间接敏感地平的卫星自主天文导航方法能取得较高的导航精度。

Simulation and Research on the Satellite Autonomous Celestial Navigation Based on the Perturbative Orbit

This paper studies the method of the autonomous satellite celestial navigation by sensing Stellar Horizon of Atmospheric Refraction In order to establish the exact motion model, the 2nd zonal harmonic of the nonspherical earth gravity is introduced to the system equation The measurement equation with the refraction height as the observation is established based on the spherically-layered atmosphere with the exponential density The computer simulation is processed after establishing the Extended Kalman Filter equation The detailed error analysis of the simulation result is presented The result illustrates that the higher precision can be obtained using satellite autonomous celestial navigation by sensing stellar horizon of atmospheric refraction based on the perturbative orbit