南京理工大学学报（自然科学版）2016，Vol.40Issue(6)：635-642,8.DOI:10.14177/j.cnki.32-1397n.2016.40.06.001
带有非线性内模补偿的挠性航天器姿态控制
Attitude control for flexible spacecraft with nonlinear internal model compensation
摘要
Abstract
A novel robust attitude controller with nonlinear internal model compensation is proposed for the disturbance rejection and vibration suppression problems of flexible spacecraft attitude control. A novel nonlinear dynamic disturbance compensator is designed via internal model principle aiming at achieving asymptotic rejection to the time-varying disturbances generated by a nonlinear exosystem. A robust attitude controller is proposed to stabilize flexible modes based on angular velocity feedback control by analyzing the characteristic of the interconnected structure of rigid-flex system and using Lyapunov technique,and the convergence of the system state variables including flexible modal variables is guaranteed. The proposed controller is easy to be implemented because <br> only the attitude angle and angular velocity other than modal variables are applied. The effectiveness and robustness of the controller are demonstrated by numerical simulation for flexible spacecraft attitude control.关键词
非线性内模补偿/挠性航天器/姿态控制/干扰抑制/振动抑制/内模原理Key words
nonlinear internal model compensation/flexible spacecrafts/attitude control/disturbance rejection/vibration suppression/internal model principle分类
信息技术与安全科学引用本文复制引用
钟晨星,郭毓,郭健,朱志浩..带有非线性内模补偿的挠性航天器姿态控制[J].南京理工大学学报（自然科学版）,2016,40(6):635-642,8.基金项目
国家自然科学基金(61473152 （）
61673219) （）
南京理工大学优秀博士培养基金 （）
