The paper presents a new actuator fault estimation scheme based on the augmented error method that estimates the actuator effectiveness on-line. The proposed scheme is applied to a fault-tolerant flight control system design for an F4-E fighter aircraft. The output of a nominal controller is continuously reconfigured to compensate for any loss of actuator effectiveness. Simulation results demonstrate good fault estimation and flying qualities obtained using the proposed scheme under the actuator fault conditions.
Actuator Fault Estimation Scheme for Flight Applications
Contributed by the Dynamic Systems and Control Division of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received by the ASME Dynamic Systems and Control Division, September 2000; final revision, May 2002. Associate Editor: Y. Chait.
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Yee , J., Liang Wang , J., and Jiang , B. (December 16, 2002). "Actuator Fault Estimation Scheme for Flight Applications ." ASME. J. Dyn. Sys., Meas., Control. December 2002; 124(4): 701–704. https://doi.org/10.1115/1.1515331
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