拦截卫星相对导航算法研究  

Relative navigation research of intercepting satellite

作　　者：邓泓[1] 仲惟超[1] 孙兆伟[1] 张健[2] 

机构地区：[1]哈尔滨工业大学卫星技术研究所,哈尔滨150001 [2]北京空间飞行器总体设计部,北京100094

出　　处：《哈尔滨工业大学学报》2013年第2期83-87,共5页Journal of Harbin Institute of Technology

摘　　要：空间攻防中,拦截卫星相对目标卫星导航参数的确定,对拦截卫星的拦截轨道设计十分重要.本文针对目标卫星轨道为椭圆轨道且拦截卫星存在机动的情况,研究了拦截卫星的相对导航算法.首先,推导了目标卫星轨道为椭圆轨道时拦截卫星的相对运动方程,并根据星间测量几何关系推导了测量方程;其次,通过引入拦截卫星的机动加速度并考虑其控制误差,设计了改进的扩展卡尔曼滤波器,以提高拦截卫星的相对导航精度;最后,通过仿真验证了算法的有效性,并获得了较好的相对导航精度.In space attack-defense system, relative position and velocity estimation between intercepting satellite and target satellite is very important for orbit designing of intercepting satellite. In this paper, relative navigation is researched under the condition that orbit of target satellite is elliptical orbit and that the intercepting satellite has orbit maneuvering. Firstly, relative motion equations are derived with elliptical orbit of target satellite, and measurement equations are developed according to the geometric relation of measurement. Then the accelera-tion of intercepting satellite is introduced with its error, and the improved EKF algorithm is designed to increase navigation accuracy. Finally, the numerical simulation results verify the validity of this navigation method and show higher navigation accuracy.

关 键 词：空间攻防 轨道机动 相对导航 卡尔曼滤波 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]