Vibration control of flexible spacecraft actuated by piezoceramics via variable structure strategy

作     者：胡庆雷 马广富 

作者机构：Dept. of Control Science & Engineering Harbin Institute of Technology 

基　　金：Sponsored by Program for Young Excellent Talents in Harbin Institute of Technology(Grant No.HITQNJS.2007.001) National Natural Science Founda-tion of China(Grant No.60674101) Research Fund for the Doctoral Program of Higher Education of China(Grant No.20050213010) 

出 版 物：《Journal of Harbin Institute of Technology(New Series)》 (哈尔滨工业大学学报（英文版）)

年 卷 期：2007年第14卷第5期

页      码：604-608页

摘      要：This paper presented a hybrid control scheme to vibration reduction of flexible spacecraft during rotational maneuver by using variable structure output feedback control (VSOFC) and piezoelectric materials. The control configuration included the attitude controller based on VSOFC method and vibration attenuator designed by constant-gain negative velocity feedback control. The attitude controller consisted of a linear feedback term and a discontinuous feedback term. With the presence of this attitude controller, an additional flexible control system acting on the flexible parts can be designed for vibration control. Compared with conventional proportional-derivative (PD) control, the developed control scheme guarantees not only the stability of the closed-loop system, but also yields better performance and robustness in the presence of parametric uncertainties and external disturbance. Simulation results are presented for the spacecraft model to show the effectiveness of the proposed control techniques.

主 题 词：航天器 控制系统 设计方案 制导系统 

学科分类：0810[工学-土木类] 08[工学] 081105[081105] 0805[工学-能源动力学] 0811[工学-水利类] 0812[工学-测绘类] 

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