基于拟平均根数之差的航天器相对导航UKF滤波算法  

Application of UKF in Spacecraft Relative Navigation Based on Quasi-Mean Element Differnces

作　　者：王功波[1] 郑伟[1] 汤国建[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2011年第5期1047-1053,共7页Journal of Astronautics

摘　　要：针对星载雷达数据(距离及其变率、角度及其变率),推导了以相对拟平均根数为状态变量的星间相对导航UKF滤波算法。建立了包含J2一阶长期项摄动的状态转移方程。推导了无奇点的相对拟平均根数与相对位置速度之间的转换矩阵,并分析了坐标变换中被忽略的二阶项的影响,对转换矩阵的精度进行了有效补偿。提出以相对位置速度为直接观测量,设计了具有自调整功能的测量误差协方差阵,避免了建立观测方程时状态量对直接观测量的繁琐偏导计算。仿真结果证明了该算法的有效性。A spacecraft relative navigation Unscented Kalman Filter（UKF） algorithm is presented in this paper,in which the desired orbit is prescribed in terms of quasi-mean element differences.This stategy is designed for spaceborne radar which can provide measurements including range,range rate,angle and angle rate.Taking the quasi-mean element differences as state variables the state transform equation is established with the J2 perturbation considered.The transformation matrix between local Cartesian coordinates and quasi-mean element differences including the mean anomaly difference is developed based on Kyle T.Alfriend＇s theory.The local Cartesian coordinates are treated as direct measurements instead of ranges and angles,and corresponding self-adjusted measurement error covariance is designed.In this case,the complex partial differentials of state variables with respect to measurement variables can be avoided.The validity of this method is proved by the simulation results.

关 键 词：相对拟平均根数 星载雷达 相对导航 J2摄动 UKF 

分 类 号：V448[航空宇航科学与技术—飞行器设计]