Sliding Mode Reconfigurable Control Using Information on the Control Effectiveness of Actuators
Publication: Journal of Aerospace Engineering
Volume 27, Issue 3
Abstract
In this paper, a sliding mode reconfigurable control algorithm is developed to deal with nonlinear aircraft system with partial loss fault or total loss failure of actuators. Sliding mode controllers for redundant actuators are combined with those for regular actuators to reconfigure the control system autonomously with the effectiveness information of the regular actuators. The tolerability of the sliding mode control system for faults is defined as the limit of regular actuators under fault conditions. The stability of the control algorithm is proved with Lyapunov method. The effectiveness of the developed control system has been validated on simulation of the longitudinal control of a nonlinear Boeing airplane model.
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Acknowledgments
This work was supported in part by Ministère du Développement économique, de l’innovation et de l’exportation (MDEIE), Quebec, Canada, and Natural Sciences and Engineering Research Council of Canada (NSERC). The third author thanks Dr. J.-Y. Shin and Dr. A. Marcos for providing the simulation platform of Boeing for the possibility to develop and evaluate this work on the high-fidelity nonlinear simulation environment.
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Information & Authors
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Published In
Journal of Aerospace Engineering
Volume 27 • Issue 3 • May 2014
Pages: 587 - 596
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Dec 2, 2011
Accepted: Apr 10, 2012
Published online: Apr 12, 2012
Published in print: May 1, 2014
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