卫星自主轨道估计方法及其高阶非线性滤波器设计  

Satellite autonomous orbit estimation method and high order nonlinear filter design

作　　者：徐国栋[1] 李鹏飞[1] 董立珉[1] 侯天蕊[1] 

机构地区：[1]哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2014年第1期117-122,共6页Systems Engineering and Electronics

基　　金：国家高技术研究发展计划(863计划)(2008AA8051602)资助课题

摘　　要：卫星的自主轨道确定是卫星自主生存的必要条件。采用星载常用敏感器对自然天体进行观测,并对观测量进行适当转换,得出观测方程为线性化方程,计算量明显减小且具有更直观的物理意义;利用星光折射时星光矢量所处特殊位置计算地心距,增加观测方程信息量;二体轨道动力学模型的一阶递推近似引入系统模型误差是影响滤波器性能的关键因素之一,应用一阶导数函数值的线性组合替代高阶导数的函数值可以使微分方程的线性化误差大为降低。在滤波器的设计过程中,应用此方法对状态方程进行处理,极大提高了滤波器状态方程的递推精度。仿真结果表明,在相同条件下这种高阶非线性轨道估计器的滤波性能远优于扩展卡尔曼滤波技术的一阶轨道估计器。Satellite autonomous orbit estimation is the necessary condition for autonomous existence of the satellite. Observed quantities which are from the commonly used satellite borne sensors are conversed, so the observation equation is linearization, and the amount of calculation is decreased. Geocentric distance is calculated by using the starlight refraction when the star vector is at a special position, then the amount of information of observation equation is increased. One of the key factors that influence the performance of the filter is that the two body dynamic orbit model of first-order recursion approximation is introduced into the system model error. The Runge Kutta method is effectively combined into the orbit estimator, and the accuracy is greatly improved. The results of simulation prove that the performance of this high order nonlinear orbit estimation filter is far superior to that of the expansion of the Kalman orbital estimator.

关 键 词：自主导航 星敏感器 地球敏感器 高阶滤波器 

分 类 号：V529.1[航空宇航科学与技术—人机与环境工程]