Fully actuated system approach to attitude control of flexible spacecraft with nonlinear time-varying inertia  

作　　者：Tianyi ZHAO Guang-Ren DUAN 

机构地区：[1]Center for Control Theory and Guidance Technology,Harbin Institute of Technology,Harbin 150o0l,China

出　　处：《Science China(Information Sciences)》2022年第11期144-158,共15页中国科学（信息科学）（英文版）

基　　金：supported by Major Program of National Natural Science Foundation of China(Grant Nos.62188101,61690210,61690212);Self-planned Task of State Key Laboratory of Robotics and System(HIT)(Grant No.SKLRS201716A);National Natural Science Foundation of China(Grant No.61333003)。

摘　　要：A high-order fully actuated(HOFA)system approach is proposed for the attitude control problem of a flexible spacecraft with nonlinear and time-varying inertia.Different from most existing results,the proposed method guarantees a linear time-invariant closed-loop system with arbitrarily assignable eigenvalues.Firstly,the HOFA model for the attitude system is derived from the original dynamic equations of the system by using state transformation and variable elimination.Then,by using the full-actuation characteristics of the obtained HOFA system,the nonlinearity in the system is completely canceled and a linear time-invariant system with arbitrarily assignable eigenvalues is derived.Finally,the control laws are designed for both problems of attitude stabilization and attitude maneuvering,and simulations are carried out based on practical engineering parameters,which demonstrate the effects of the proposed method.

关 键 词：high-order fully actuated system flexible spacecraft time-varying nonlinear systems attitude stabilization attitude maneuvering 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]