Reliable automatic landing control against actuator stuck faults

Abstract

This paper presents a new LMI-based approach for developing reliable automatic landing controllers which can tolerate actuator stuck faults. The H 2 control technique is used to guarantee tracking performance with respect to a given glide slope trajectory. A realistic fighter aircraft model is studied to illustrate the proposed approach. Nonlinear simulation under various faults and wind disturbances are included in this study. Simulation results show that the proposed reliable controller design approach can achieve zero steady-state tracking error, robustness against wind disturbances and reliability against actuator stuck faults. Copyright © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.