摘要
针对单星对卫星被动定轨时使用经典轨道根数作为状态变量可能存在奇点且测量方程变量及相应坐标转换缺乏物理意义等问题,提出一种新的基于J2000.0惯性系的单星对卫星扩展Kalman滤波仅测角被动定轨跟踪方法,并对测量方程中的变量及其坐标转换进行明确定义;同时对状态预测方程、状态转移矩阵及测量雅可比矩阵进行详细推导,最后通过STK6.0仿真场景产生的数据对算法在不同初始状态误差和测角精度下的性能进行对比分析和仿真验证。多次仿真结果表明:该算法实现了单颗高轨卫星(准同步轨道)通过仅测量角度对圆轨道(e=0)低轨卫星辐射源的被动定轨和跟踪,当测角精度优于平均角度变化量时,滤波收敛所需时间及估计误差都大大减小,且该算法对滤波初始误差也具有较好的适应性。
Regarding the problems of singularity while using classic orbital elements in satellite bearings-only passive tracking and the lack of physical meanings in measurement equation＇s variables and their corresponding coordinate transformations, a new satellite-to- satellite extended Kalman filtering （EKF） tracking method with bearings-only measurements in J2000.0 ECI frame is put forward. An expheit definition of the variables and their eoordinate transformations in measurement equation are submitted. Moreover, the state propagation stage, state transfer matrix and measurement Jacobi matrix are deducted in detail. Performanee is contrasted and validated through simulated data from STK6.0 with various initial state errors and angles measurement errors. Simulation indicates that it is possible to passively track low earth eirenlar orbit satellite （ e = 0） by a high earth orbit satellite （quasi-geosynehronous orbit satellite） with bearings-only measurements. When the angles measurement aceuraey exceeds the average angles ehanging magnitude, the convergence time and the tracking errors rapidly decrease. Moreover, the method also shows resilience to varying initial state errors.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2007年第2期70-75,共6页
Journal of National University of Defense Technology
基金
国家部委资助项目(11301030101)
国防科技大学资助项目
关键词
卫星
仅测角
被动跟踪
扩展卡尔曼滤波
satelllte
bearings-only
passive tracking
extended Kalman filtering
