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TECHNICAL PAPERS

Spacecraft Vibration Suppression Using Variable Structure Output Feedback Control and Smart Materials

[+] Author and Article Information
Qinglei Hu

Department of Control Science and Engineering, Harbin Institute of Technology, P.O. Box 327, No. 92 West Da-zhi Street, Harbin, 150001, Chinahuqinglei@hit.edu.cn; huqinglei@126.com

Guangfu Ma

Department of Control Science and Engineering, Harbin Institute of Technology, P.O. Box 327, No. 92 West Da-zhi Street, Harbin, 150001, Chinamagf@hit.edu.cn

J. Vib. Acoust 128(2), 221-230 (Nov 03, 2005) (10 pages) doi:10.1115/1.2159039 History: Received January 18, 2005; Revised November 03, 2005

A hybrid control scheme for vibration reduction of flexible spacecraft during rotational maneuvers is investigated by using variable structure output feedback control (VSOFC) for attitude control and smart materials for active vibration suppression. The proposed control design process is twofold: design of the attitude controller using VSOFC theory acting on the hub and design of an independent flexible vibration controller acting on the flexible part using piezoceramics as sensors and actuators to actively suppress certain flexible modes. The attitude controller, using only the attitude and angular rate measurement, consists of a linear feedback term and a discontinuous feedback term, which are designed so that the sliding surface exists and is globally reachable. With the presence of this attitude controller, an additional independent flexible control system acting on the flexible parts is designed for further vibration suppression. Using the piezoelectric materials as actuator/sensor, both single-mode vibration suppression and multimode vibration suppression are studied and compared for the different active vibration control algorithms, constant-gain negative velocity feedback (CGNVF) control, positive position feedback (PPF) control, and linear-quadratic Gaussian (LQG) control. Numerical simulations demonstrate that the proposed approach can significantly reduce the vibration of the flexible appendages and further greatly improve the precision during and after the maneuver operations.

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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 1

Model of spacecraft with flexible appendages with bonded piezoelectric material

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Figure 2

A block-diagram of the proposed control algorithm for flexible spacecraft attitude control and vibration reduction

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Figure 12

(a) and (b) Time response for the VSOFC integrated with LQG

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Figure 11

(a) and (b) Time response for the VSOFC integrated with PPF compensator on multimode

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Figure 10

(a) and (b) Time response for the VSOFC integrated with PPF compensator on second mode

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Figure 9

(a) and (b) Time response for the VSOFC integrated with PPF compensator on first mode

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Figure 8

(a) and (b) Time response for the VSOFC integrated with CGNVF

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Figure 7

Time response for only using VSOFC

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Figure 6

Bode plot with ςc=0.5

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Figure 5

Bode plot with ςc=0.1

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Figure 4

Frequency response of system to PPF compensator

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Figure 3

Positive position feedback block diagram

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