摘要
空间态势感知活动中,航天器需要快速轨道机动对目标进行近距离观测,因燃料消耗快导致转动惯量较大改变.本文针对航天器快速轨道机动过程中转动惯量时变问题,改进了扩展卡尔曼滤波算法,提出了一种时变转动惯量实时辨识方法.首先,根据辨识算法需要,设计了线性状态观测器估计角加速度.然后,考虑转动惯量的时变特性,给出了含有参数时变信息的预测误差协方差矩阵,并以角加速度作为滤波所需的系统输出信息,对参数预测值进行修正,得到了辨识时变转动惯量的改进扩展卡尔曼滤波算法.最后,设置转动惯量以不同方式进行变化,使用传统类PD控制律进行状态跟踪仿真,实现了时变转动惯量的滤波辨识与姿态跟踪控制.
In mission of space situational awareness,the inertia matrix changes greatly due to the fast fuel consumption,while spacecraft maneuver fast to observe the target in close range.Extended Kalman Filter is modified to identify the time-varying inertia matrix in real time when spacecraft maneuver.Firstly,a linear state observer is designed to estimate the angular accelerations of spacecraft.Then,considering the variation of the moment of inertia of the spacecraft,the covariance matrix of prediction error is modified.A filter model is obtained with angular acceleration estimates for time-varying inertia matrix identification in real time.Finally,the traditional PD-like controller is used for attitude tracking with inertia matrix identification,and the attitude tracking and parameter identification are achieved.
作者
魏远明
王孟磊
耿云海
吴宝林
WEI Yuanming;WANG Menglei;GENG Yunhai;WU Baolin(National University of Defense Technology,College of Aerospace Science and Engineering,Changsha 410073,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;Research Center of Satellite Technology,Harbin Institute of Technology,Harbin 150001,China)
出处
《空间控制技术与应用》
CSCD
北大核心
2022年第3期93-101,共9页
Aerospace Control and Application
基金
国家自然科学基金资助项目(61873312)。
关键词
空间态势感知
时变转动惯量
扩展卡尔曼滤波
参数辨识
状态观测器
space situational awareness
time-varying moment of inertia
extended kalman filter
parameter identification
state observer
