On-orbit Identification of Time-varying Moment of Inertia for Spacecraft Based on a Recursive Subspace Method

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• 英文论文题名：On-orbit Identification of Time-varying Moment of Inertia for Spacecraft Based on a Recursive Subspace Method
• 论文作者：Zhiyu Ni ; Zhigang Wu ; Jinguo Liu ; Xinhui Shen
• 英文论文作者：Zhiyu Ni ; Zhigang Wu ; Jinguo Liu ; Xinhui Shen ; Shenyang Institute of Automation ; Chinese Academy of Sciences ; Dalian University of Technology ; School of Aeronautics and Astronautics
• 年：2017
• 作者机构：Shenyang Institute of Automation,Chinese Academy of Sciences;Dalian University of Technology,School of Aeronautics and Astronautics;
• 英文论文关键词：Recursive subspace method ; time-varying system ; moment of inertia ; on-orbit identification ; state space model
• 会议召开时间：2017-07-26
• 会议录名称：第36届中国控制会议论文集（B）
• 英文会议录名称：Proceedings of the 36th Chinese Control Conference（B）
• 语种：英文
• 分类号：V448.2
• 学会代码：KZLL
• 会议名称：第36届中国控制会议
• 会议地点：中国辽宁大连
• 主办单位：中国自动化学会控制理论专业委员会
• 学会名称：中国自动化学会控制理论专业委员会
• 页数：6
• 文件大小：335k
• 原文格式：D
• 会议级别：全国

摘要

In this paper, a novel recursive method to identify the moment of inertia parameters of on-orbit spacecraft is proposed. Different from the frequently-used momentum conservation and least squares approach, the presented method is implemented based on the Projection Approximation Subspace Tracking(PAST), and the moment of inertia parameters can be determined recursively from the system state-space model by coordinate transformation. For a spacecraft with flexible appendages, three on-orbit cases that may cause the moment of inertia parameters to vary with time are investigated. In numerical simulations, comparing with the classical subspace method based on the singular value decomposition(SVD), the results illustrate that the proposed recursive algorithm can identify the time-varying moment of inertia parameters effectively. Moreover, the computational efficiency is also higher than that of the SVD-based method without the decomposition of the Hankel matrix.
In this paper, a novel recursive method to identify the moment of inertia parameters of on-orbit spacecraft is proposed. Different from the frequently-used momentum conservation and least squares approach, the presented method is implemented based on the Projection Approximation Subspace Tracking(PAST), and the moment of inertia parameters can be determined recursively from the system state-space model by coordinate transformation. For a spacecraft with flexible appendages, three on-orbit cases that may cause the moment of inertia parameters to vary with time are investigated. In numerical simulations, comparing with the classical subspace method based on the singular value decomposition(SVD), the results illustrate that the proposed recursive algorithm can identify the time-varying moment of inertia parameters effectively. Moreover, the computational efficiency is also higher than that of the SVD-based method without the decomposition of the Hankel matrix.

引文

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