考虑地球扁率误差的两步Kalman滤波星光导航方法  

A starlight navigation algorithm based on two-step Kalman filter method with earth oblateness correction

作　　者：林夏 林宝军[1,2,3,4,5] 刘迎春 白涛 武国强 LIN Xia;LIN Baojun;LIU Yingchun;BAI Tao;WU Guoqiang(Shanghai Engineering Center for Microsatellites,Shanghai 201210,China;Aerospace Information Research Institute,Chinese Academy of Sciences,Beijing 100094,China;University of Chinese Academy of Sciences,Beijing 100094,China;Shanghai Tech University,Shanghai 201210,China;Innovation Academy for Microsatellites of Chinese Academy of Sciences,Shanghai 201210,China)

机构地区：[1]上海微小卫星工程中心,上海201210 [2]中国科学院空天信息创新研究院,北京100094 [3]中国科学院大学,北京100094 [4]中国科学院微小卫星创新研究院,上海201210 [5]上海科技大学,上海201210

出　　处：《中国惯性技术学报》2021年第5期632-636,642,共6页Journal of Chinese Inertial Technology

基　　金：上海市青年科技英才扬帆计划项目基金(21yf1446000)。

摘　　要：为提升基于星敏感器和地球敏感器的卫星星光导航精度,提出了一种基于两步Kalman滤波的星光导航算法。通过一步星光导航滤波器预处理,得到了存在一定误差的卫星位置估计。将位置估计引入地球扁率误差修正算法,使地球敏感器地球扁率误差实现星上自主修正。而后,利用修正后的地球敏感器输出形成精确的星光角距观测信息,再次应用星光导航滤波器,得到了精度较高的卫星轨道信息。仿真结果表明,利用所提出的算法,地球敏感器敏感地心矢量精度为0.001°,卫星三轴位置精度为3000 m,卫星三轴速度精度为4 m/s。相比于传统无修正星光导航算法,精度提升了80%以上。To improve the accuracy of the starlight navigation algorithm,a two-step Kalman filter algorithm is proposed.Through first-step star navigation filter preprocessing,a rough satellite position estimation is obtained.The position estimation is introduced into the earth oblateness error correction algorithm and the earth oblateness error in the earth sensor is corrected effectively and autonomously.Then,using the corrected earth sensor outputs to form accurate star angular distance observation information,the starlight navigation algorithm is reused and the navigation messages are precisely determined.The simulation results show that by the two-step Kalman filter algorithm,the accuracy of the geocentric vector measured by the earth sensor is 0.001°,the three-axis position estimation errors of satellite are 3000 m,and the three-axis velocity estimation errors of the satellite are 4 m/s.Compared with the traditional uncorrected starlight navigation algorithm,the accuracy has been improved by more than 80%.

关 键 词：星光导航 地球敏感器 地球扁率 无迹Kalman滤波 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计] V448