Fuzzy Adaptive Variable Structure Active Attitude Control of Flexible Spacecraft

Abstract:

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This paper presents a novel control system design method for the three-axis-rotational tracking and vibration stabilization of a spacecraft with flexible appendages. Based on the sliding control theory, a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, both fuzzy methods and strain rate feedback (SRF) control methods are presented. Numerical simulations are performed to show the feasibility and effeteness of the proposed methods.

Info:

Periodical:

Edited by:

Ran Chen

Pages:

2070-2074

DOI:

10.4028/www.scientific.net/AMM.44-47.2070

Citation:

F. Y. Qu et al., "Fuzzy Adaptive Variable Structure Active Attitude Control of Flexible Spacecraft", Applied Mechanics and Materials, Vols. 44-47, pp. 2070-2074, 2011

Online since:

December 2010

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$35.00

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