Nonlinear suboptimal tracking control of spacecraft approaching a tumbling target  

作　　者：Zhan-Peng Xu Xiao-Qian Che Yi-Yong Huang Yu-Zhu Bai Wen Yao 许展鹏;陈小前;黄奕勇;白玉铸;姚雯(College of Aerospace Science and Engineering, National University of Defense Technology;National Innovation Institute of Defense Technology, Chinese Academy of Military Science)

机构地区：[1]College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China [2]National Innovation Institute of Defense Technology,Chinese Academy of Military Science,Beifing 100091,China

出　　处：《Chinese Physics B》2018年第9期213-222,共10页中国物理B（英文版）

基　　金：Project supported by the Major Program of the National Natural Science Foundation of China(Grant Nos.61690210 and 61690213)

摘　　要：We investigate the close-range relative motion and control of a spacecraft approaching a tumbling target. Unlike the traditional rigid-body dynamics with translation and rotation about the center of mass（CM）, the kinematic coupling between translation and rotation is taken into consideration to directly describe the motion of the spacecraft＇s sensors or devices which are not coincident with the CM. Thus, a kinematically coupled 6 degrees-of-freedom（DOF） relative motion model for the instrument（feature point） is set up. To make the chaser spacecraft＇s feature point track the target＇s, an optimal tracking problem is defined and a control law with a feedback-feedforward structure is designed. With quasi-linearization of the nonlinear dynamical system, the feedforward term is computed from a specified constraint about the dynamical system and the reference model, and the feedback action is derived starting from the state-dependent Ricca equation（SDRE）. The proposed controller is compared with an existing suboptimal tracking controller, and numerical simulations are presented to illustrate the effectiveness and superiority of the proposed method.We investigate the close-range relative motion and control of a spacecraft approaching a tumbling target. Unlike the traditional rigid-body dynamics with translation and rotation about the center of mass（CM）, the kinematic coupling between translation and rotation is taken into consideration to directly describe the motion of the spacecraft＇s sensors or devices which are not coincident with the CM. Thus, a kinematically coupled 6 degrees-of-freedom（DOF） relative motion model for the instrument（feature point） is set up. To make the chaser spacecraft＇s feature point track the target＇s, an optimal tracking problem is defined and a control law with a feedback-feedforward structure is designed. With quasi-linearization of the nonlinear dynamical system, the feedforward term is computed from a specified constraint about the dynamical system and the reference model, and the feedback action is derived starting from the state-dependent Ricca equation（SDRE）. The proposed controller is compared with an existing suboptimal tracking controller, and numerical simulations are presented to illustrate the effectiveness and superiority of the proposed method.

关 键 词：tumbling target 6 degrees-of-freedom（DOF） relative motion suboptimal tracking control state-dependent Ricca equation（SDRE） method 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]