非合作目标软捕获后的动力学参数无激励辨识

  • 徐升 ,
  • 褚明 ,
  • 蔺绍奇 ,
  • 常睿 ,
  • 孙汉旭
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  • 北京邮电大学

收稿日期: 2022-12-01

  修回日期: 2023-05-23

  网络出版日期: 2023-05-24

基金资助

国家自然科学基金资助项目

Dynamic Parameter Identification without Excitation for Non-cooperative Target Post Soft Capture

  • XU Sheng ,
  • CHU Ming ,
  • LIN Shao-Qi ,
  • CHANG Rui ,
  • SUN Han-Xu
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Received date: 2022-12-01

  Revised date: 2023-05-23

  Online published: 2023-05-24

摘要

针对非合作目标动力学参数的在轨辨识问题,提出一种基于软对接机构状态感知的无激励辨识方法。当非合作目标被捕获后,复合体进入冲量缓冲和卸载阶段,软对接机构则处于无激励运动响应状态。首先,分析搭载软对接机构的主航天器运动学,建立包含非合作目标动力学参数的复合体动量方程,进而完成复合体绝对动量增量方程的构建。其次,针对求解动力学参数时存在的奇异问题,设计一种矩阵连续增维的方法实现避奇异求解,并通过矩阵条件数求解完成终止条件的度量。最后,仅需在轨感知搭载软对接机构主航天器的广义坐标和广义速度,即可实现非合作目标动力学参数的辨识。数值仿真实验表明,提出的非合作目标动力学参数在轨无激励辨识方法,具有求解速度快、辨识周期短、对基座姿态影响小和辨识精度高的优点。

本文引用格式

徐升 , 褚明 , 蔺绍奇 , 常睿 , 孙汉旭 . 非合作目标软捕获后的动力学参数无激励辨识[J]. 航空学报, 0 : 0 -0 . DOI: 10.7527/1000-6893.2023.28342

Abstract

Aiming at the problem of dynamic parameter identification on orbit for non-cooperative target, a non-excitation identifica-tion method based on state perception of soft-docking mechanism is proposed. When the non-cooperative target is cap-tured, the compound system is in the phase of buffering and unloading impulse, and the soft-docking mechanism is in the state of non-excitation response. Firstly, the kinematics of the spacecraft with the soft-docking mechanism is analyzed, and the momentum equation of the compound system with the dynamics parameters of the non-cooperative target is established, and then an absolute momentum increment equation of the compound system is constructed. Secondly, aiming at the singularity problem in solving dynamic parameters, a method of continuous dimension increasing of matrix is designed to avoid singularity, and complete the measure of the termination condition through the solution of matrix condition number. Finally, based on the generalized coordinates and generalized velocities of the spacecraft with soft-docking mechanism through on-orbit perception, the dynamic parameters of the non-cooperative target can be identified. The numerical simulation results show that the proposed method has the advantages of faster solution, short identification period, small impact on the attitude of the base and high identification accuracy.

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