超低轨道地球卫星脉冲星/星光折射/光谱组合导航  

Pulsar/Starlight Refraction/Spectrum Integrated Navigation of Ultra Low Orbit Satellite

作　　者：李君儒 马辛[1] 刘劲[2] 宁晓琳[1] LI Junru;MA Xin;LIU Jin;NING Xiaolin(Research Institute for Frontier Science,Beihang University,Beijing 100191;School of Information Science and Engineering,Wuhan University of Science and Technology,Wuhan 430081)

机构地区：[1]北京航空航天大学前沿科学技术创新研究院,北京100191 [2]武汉科技大学信息科学与工程学院,武汉430081

出　　处：《飞控与探测》2023年第4期26-35,共10页Flight Control & Detection

基　　金：国家自然科学基金(61703022,61873196,62373030);科技创新2030-“量子通信与量子计算机”重大项目(2021ZD0303400);国家重点大学基础研究经费(YWF-19-BJ-J-307,YWF-19-BJ-J-82);航天科学技术基金(2020-HT-BH-21)。

摘　　要：针对超低轨道地球卫星导航自主需求,提出了一种脉冲星/星光折射/光谱测速组合天文导航方法。首先根据地球超低轨道卫星运行轨道动力学方程建立导航系统状态模型;分别根据脉冲到达时间差和星光折射角与天体光谱频率建立导航系统量测模型;使用Unscented卡尔曼滤波方法,降低随机误差对导航精度的影响,使用基于UKF的信息融合方法,有效融合了三种天文导航方法结果数据。经计算机仿真分析,该组合导航方法位置导航误差均值为85.62m,速度误差均值0.190m/s,能够满足超低轨道地球卫星在轨运行导航需求。According to the autonomous requirements of earth ultra-low orbit satellite navigation,a combined astronomical navigation method of pulsar/stellar refraction/spectral velocimetry is proposed in this paper.Firstly,the state model of navigation system is established according to the dynamic equation of earth ultra-low orbit satellite.The measurement model of navigation system is established according to the pulse arrival time difference,star refraction angle and celestial spectral frequency.Unscented Kalman filter(UKF)is used to reduce the influence of random error on navigation accuracy.A UKF information fusion method is applied to effectively fuse the result data of three astronomical navigation methods.Through computer simulation analysis,the average position navigation error of the integrated navigation method is 85.62m and the average velocity error is 0.190m/s,which can meet the on orbit navigation requirements of earth ultra-low orbit satellites.

关 键 词：超低轨道地球卫星 星光折射导航 脉冲星导航 光谱测速导航 组合导航 天文导航 

分 类 号：TN911.73[电子电信—通信与信息系统] TP391.9[电子电信—信息与通信工程]