Reconfigurable flight control law based on model following scheme and parameter estimation

Abstract

In this paper, a reconfigurable model following flight control method is proposed based on direct adaptive scheme using parameter estimation. Proposed method possesses fault detection and isolation capabilities as well as fault tolerance property. Adaptive control scheme updates the control gains to make the system output follow the reference output even when fault occurs. By adopting the parameter estimation method in frequency domain, system model changes due to fault can be estimated. The Fourier transformation and recursive Fourier transformation are used for system identification. With the help of Fourier transform, the proposed adaptive control algorithm guarantees the system stability and improves the system characteristics. To evaluate the performance of the proposed control method, numerical simulation is performed. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.