Sliding Mode Reconfigurable Fault Tolerant Control for Nonlinear Aircraft Systems
Publication: Journal of Aerospace Engineering
Volume 28, Issue 3
Abstract
In this paper, a sliding mode reconfigurable control algorithm without dedicated fault detection and identification module is developed for nonlinear aircraft systems with partial loss fault or total failure such as stuck or floating. The redundant actuators are integrated with the regular actuators in the controller seamlessly when faults or failures occur in the regular actuators. This method monitors the sliding surface to decide if the redundant actuator should be activated. The stability of the control system was proved by using Lyapunov method, and the effectiveness of the control system is validated by the simulation results of longitudinal control of a nonlinear model of Boeing 747.
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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).
Thanks to Dr. J.-Y. Shin and Dr. A. Marcos for providing the FTLAB747 simulation platform.
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Published In
Journal of Aerospace Engineering
Volume 28 • Issue 3 • May 2015
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Jul 4, 2013
Accepted: Mar 6, 2014
Published online: Mar 10, 2014
Discussion open until: Dec 21, 2014
Published in print: May 1, 2015
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