基于Unscented卡尔曼滤波器的近地卫星磁测自主导航  

Autonomous Navigation of Low-Earth-Orbit Satellites Using Magnetic Measurements by Unscented Kalman Filter

作　　者：高长生[1] 荆武兴[1] 张燕[1] 黄翔宇[1] 

机构地区：[1]哈尔滨工业大学,哈尔滨150001

出　　处：《中国空间科学技术》2006年第1期27-32,共6页Chinese Space Science and Technology

摘　　要：建立了近地卫星高精度轨道动力学模型和10×10阶地磁场模型,分别以地磁场矢量和强度幅值作为观测量,通过Unscented卡尔曼滤波实现自主导航。在采样周期10s,磁强计测量噪声100nT情况下仿真,仿真结果显示以地磁场矢量为观测量时卫星导航误差在卫星前进方向(切向)、轨道法向、卫星径向的分量分别为1km、0.9km、0.3km,而以地磁场强度幅值为观测量时误差分别为1.6km、1.3km、0.5km。Autonomous navigation does not need any information from the land station, so it can satisfy some specific requirements. In order to describe the distribution of the geomagnetic field better, the high-accuracy dynamic model of orbit and the 10 × 10-order model of the geomagnetic field are established. Taking the vector and the magnitude of the geomagnetic field as the observed variable respectively, the autonomous navigation is realized by the Unscented Kalman Filter. Suppose that the sampling period is 10s, and the measurement noise of the magnetometer is 100nT, the results of the simulation show that the satellite navigation error is 1km. 0.9km. 0.3km. When the observed variable is the geomagnetic vector, otherwise it is 1.6km, 1.3km, 0.5km.

关 键 词：磁强计 地磁场 卡尔曼滤波 自主式导航 仿真 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术] TN713[自动化与计算机技术—计算机科学与技术]