What is it about?
In this paper, a sliding mode control algorithm is developed to synthesize a nonlinear control system for aircraft systems with actuator faults. Two design parameters are used to deal with uncertainty caused by actuator faults and uncertainty in system dynamics separately. An adaptive algorithm is developed to accommodate these uncertainties without knowing exactly the bounds of these uncertainties. The stability of the overall control system is proved by using the Lyapunov function. The effectiveness of the developed algorithms has been verified on the platform FTLAB747.
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Why is it important?
A retrofit of the controller of the aircraft will help the pilot when there are faults in actuators of the aircraft, which will help save lives and aircraft from a crash.
Read the Original
This page is a summary of: Adaptive Sliding Mode Fault Tolerant Control of Civil Aircraft with Separated Uncertainties, January 2010, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2010-945.
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