基于EKF/PI滤波的小推力轨控期间自主导航算法
Autonomous Navigation Algorithm During Continuous Low Thrust Orbit Control Based on EKF and PI Fiter
梁巨平 1孟其琛 1黄京梅 1刘笑 1陈银河1
作者信息
- 1. 上海航天控制技术研究所,上海 201109;空间智能控制技术重点实验室,上海 201109
- 折叠
摘要
研究了以电推小推力作为主要的轨控推力来源的高轨卫星在轨控期间的自主导航算法.针对GNSS接收机在高轨的测速精度相对较差,以及轨控期间电推产生的推力较小,常规加速度计无法准确测量,从而导致在轨控期间自主导航精度下降的问题,提出了基于EKF+PI滤波的一体化自主导航算法.通过结合EKF滤波和PI滤波算法,经EKF滤波抑制GNSS接收机定位数据的测量白噪声,然后通过PI滤波估计电推加速度并反馈给EKF滤波算法,提高电推工作期间EKF算法的导航精度.仿真结果表明,基于EKF+PI滤波的一体化自主导航算法可以准确估计出电推加速度大小,同时可有效提高连续小推力轨控期间的自主导航精度.
Abstract
The autonomous navigation algorithm during continuous low-thrust orbit control for high-orbit satellites with electric thruster is researched.In view of the relatively poor speed measurement precision of GNSS receivers in high orbit,and the small acceleration generated by electric thruster during orbit control can not be measured accurately by conventional accelerometers,which leads to the decline of autonomous navigation accuracy during orbit control,an integrated autonomous navigation algorithm based on EKF+PI filter is proposed.Firstly,the EKF filter is designed to suppress the high frequency noise of positioning data generated by the GNSS receiver.Then,the acceleration generated by the electric thruster is estimated by PI filter and fed back to the EKF algorithm.By combing the EKF filter with PI filter,the precision of the navigation algorithm is improved during the electric thruster's working.Lastly,the mathematical simu-lation is implemented,and the result shows that the integrated autonomous navigation algorithm based on EKF+PI filter can accurately estimate the acceleration magnitude generated by electric thruster.Mean-time,the integrated algorithm proposed can effectively improve the precision of autonomous navigation dur-ing continuous low-thrust orbit control.
关键词
自主导航/扩展卡尔曼滤波/PI滤波/加速度估计/小推力轨控/电推进Key words
Autonomous navigation/Extended Kalman filter/PI filter/Acceleration estimation/Low-thrust orbit control/Electric thruster引用本文复制引用
出版年
2024
NETL
NSTL
万方数据