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Active Vibration Suppression of Flexible Spacecraft Based on Dynamic Output Feedback

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2005年04期
Page:
394-398
Research Field:
Publishing date:

Info

Title:
Active Vibration Suppression of Flexible Spacecraft Based on Dynamic Output Feedback
Author(s):
MA Guang-fuHU Qing-leiSHI Zhong
School of Astronautics, Harbin Institute of Technology,Harbin 150001,China
Keywords:
flexible spacecrafts attitude maneuver active vibration suppression piezoelectric actuat
PACS:
V415
DOI:
-
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.

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.

Memo

Memo:
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Last Update: 2013-03-03