On-Orbit Identification of the Moment of Inertia for a Spacecraft with Flexible Appendages during a Large-Angle Maneuver

被引：0
作者：
He X. [1 ]
Tan S.-J. [1 ]
Wu Z.-G. [1 ,2 ]
机构：
[1] School of Aeronautics and Astronautics, Dalian University of Technology, Dalian
[2] State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian
来源：
Tan, Shu-Jun (tansj@dlut.edu.cn) | 1600年 / China Spaceflight Society卷 / 38期
关键词：
Extended Kalman filter (EKF); Flexible appendages; Least square; Moment of inertia; On-orbit parameter identification;
D O I：
10.3873/j.issn.1000-1328.2017.09.005
中图分类号：
学科分类号：
摘要：
For the problem of the on-orbit identification of the moment of inertia for a spacecraft with flexible appendages during a large-angle maneuver, a concurrent recursive algorithm is proposed in this paper, which combines the estimation of the inertia parameters with the state estimation of the flexible appendages' vibration modes. The algorithm is based on the nonlinear dynamic model of a spacecraft with flexible appendages during a large-angle maneuver. The extended Kalman filter is used to estimate the states of the flexible appendages' vibration modes, and the least square method is used to estimate the parameters of the moment of inertia. Finally, the inertia parameters of the spacecraft are obtained by the concurrent recursive algorithm. In order to improve the efficiency of the algorithm, a recursive algorithm based on one-step least square method and multi-step extended Kalman filter is proposed. Simulation results show that the proposed algorithm not only improves the computational accuracy and efficiency, but also has the capability of anti-interference. © 2017, Editorial Dept. of JA. All right reserved.
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页码：927 / 935
页数：8
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