[1]马广富,胡庆雷,石忠.基于动态输出反馈的挠性航天器主动振动抑制[J].南京理工大学学报(自然科学版),2005,(04):394-398.
 MA Guang-fu,HU Qing-lei,SHI Zhong.Active Vibration Suppression of Flexible Spacecraft Based on Dynamic Output Feedback[J].Journal of Nanjing University of Science and Technology,2005,(04):394-398.
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基于动态输出反馈的挠性航天器主动振动抑制
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
期数:
2005年04期
页码:
394-398
栏目:
出版日期:
2005-08-30

文章信息/Info

Title:
Active Vibration Suppression of Flexible Spacecraft Based on Dynamic Output Feedback
作者:
马广富胡庆雷石忠
哈尔滨工业大学航天学院, 黑龙江哈尔滨150001
Author(s):
MA Guang-fuHU Qing-leiSHI Zhong
School of Astronautics, Harbin Institute of Technology,Harbin 150001,China
关键词:
挠性航天器 姿态机动 主动振动抑制 压电作动器
Keywords:
flexible spacecrafts attitude maneuver active vibration suppression piezoelectric actuat
分类号:
V415
摘要:
针对航天器三轴同时姿态机动时挠性附件的振动抑制问题,提出了基于动态输出反馈控制的主动振动抑制方法。采用拉格朗日方法和四元数参数化建立了挠性航天器的非线性模型。利用航天器姿态控制问题固有的无源性,设计了1种仅利用姿态四元数而无需以角速度测量、挠性变形位移及速率测量作为反馈的动态控制规律,并采用压电作动器来抑制挠性结构的振动。基于Lyapunov方法证明了所设计的动态控制器保证了姿态的渐近稳定和模态的振动的衰减。仿真结果表明了所提出的控制方法的可行性和有效性。
Abstract:
A dynamic controller is presented for res-t to-rest flexible spacecraft attitude maneuver with the active vibration suppression. On the basis of the Lagrangian approach and quaternion parameterization, the nonlinear model of the flexible spacecraft is obtained. This controller does not need the knowledge of modal variables and spacecraft angular velocity. The unavailable measurements of these variables are compensated by appropriate dynamics of the controller, which supplies their estimates. The Lyapunov technique is applied to design this dynamic controller, that ensures the stability of the system. Possible source of instability of the controlled system in real cases are the influence of the flexibility on the rigid motion and the presence of disturbances acting on the structure. In order to attenuate their effects and to damp out the undesirable vibrations affecting the spacecraft att-i tude, distributed piezoelectric actuators are employed. The simulation results reveal the interest and the pract ical feasibility of such a control scheme.

参考文献/References:

[ 1] Baz A, Poh S. Performance of an active control system with piezoelectric actuators [ J] . Journal of Sound and Vibration, 1988, 126 ( 2) : 327- 343.
[ 2] Li Z, Bainum P M. Vibration control of flex ible spacecraft integrating a momentum exchange controller and a distributed piezoelectric actuator [ J] . Journal of Sound and Vibration, 1994, 177 ( 4) : 539- 553.
[ 3] Hu Q, Ma G, Li C. Active vibration control of a flexible plate structure using LMI- based H ] output feedback control law [ A] . Proceedings of IEEE the 5th World Congress on Intell-i gent Control and Automation [ C] . Hangzhou, China: IEEE Inc. , 2004. 738- 742.
[ 4] di Gennaro S. Output stabilization of flex ible spacecraft with active vibration suppression [ J ] . IEEE Transactions on Aerospace and Electronic systems, 2003, 39 ( 3) : 747- 759.
[ 5] Lizarralde F, Wen J T. Attitude control without angular velocity measurement: a passivity Approach [ J] . IEEE transactions on Automatic Control, 1996, 41( 3) : 468- 472.
[ 6] di Gennaro S. Passive attitude control of flex ible spacecraft from quaternion measures [ J] . Journal of Optimization Theory and Applications, 2003, 116 ( 1) : 41- 60.
[ 7] Khalil H K. Nonlinear system [M] . New York: Macmillan, 1992.

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备注/Memo

备注/Memo:
作者简介: 马广富( 1963- ) , 男, 河北唐山人, 教授, 博士生导师, 博士, 主要研究方向: 卫星姿态控制、最优控制、H∞ 控制, E-mail: magf@hit. edu. cn。
更新日期/Last Update: 2013-03-03