Design of an Attitude and Disturbance Rejection Controller for Spacecraft  

作　　者：JIA Fujin JIANG Yuan DAI Jiyang 贾付金;蒋沅;代冀阳(Key Laboratory of Nondestructive Testing,Ministry of Education;School of Information Engineering,Nanchang Hangkong University)

机构地区：[1]Key Laboratory of Nondestructive Testing,Ministry of Education,Nanchang 330063,China [2]School of Information Engineering,Nanchang Hangkong University,Nanchang 330063,China

出　　处：《Journal of Donghua University(English Edition)》2018年第3期232-236,共5页东华大学学报（英文版）

基　　金：National Natural Science Foundation of China(No.61663030,No.61663032);Natural Science Foundation of Jiangxi Province,China(No.20142BAB207021);the Innovation Fund Designated for Graduate Students of Jiangxi Province(YC2016-S350);the Foundation of Jiangxi Educational Committee,China(No.GJJ150753);the Open Fund of Key Laboratory of Image Processing and Pattern Recognition of Jiangxi Province,China(Nanchang Hangkong University)(No.TX201404003);Key Laboratory of Nondestructive Testing(Nanchang Hangkong University),Ministry of Education,China(No.ZD29529005);The Twelfth "Sanxiao" College Students Extracurricular Innovation and Entrepreneurship Practice and Training Project of Nanchang Hangkong University,China(No.2017ZD021)

摘　　要：According to the Rodrigues parameter and the internal model principle,an adaptive state feedback control law is proposed for a rigid spacecraft with inertia uncertainty and exotic disturbances generated by an unknown nonlinear exosystem.The uncertainty of parameters is treated by an adaptive control law.And a new internal model is proposed to estimate the exotic disturbances.By using the Lyapunov analysis method,the control law is designed to ensure that the system's state variables asymptotically converge to stable,and the disturbances can be completely rejected.Finally,numerical simulations are included to demonstrate the performance of the presented controller.According to the Rodrigues parameter and the internal model principle,an adaptive state feedback control law is proposed for a rigid spacecraft with inertia uncertainty and exotic disturbances generated by an unknown nonlinear exosystem.The uncertainty of parameters is treated by an adaptive control law.And a new internal model is proposed to estimate the exotic disturbances.By using the Lyapunov analysis method,the control law is designed to ensure that the system＇s state variables asymptotically converge to stable,and the disturbances can be completely rejected.Finally,numerical simulations are included to demonstrate the performance of the presented controller.

关 键 词：Rodrigues parameter rigid spacecraft parametric uncertainties exotic disturbances internal model Lyapunov analysis 

分 类 号：TP301.6[自动化与计算机技术—计算机系统结构]