Adaptive Sliding Mode Fault Tolerant Control of Civil Aircraft with Separated Uncertainties
نویسندگان
چکیده
In this paper, a sliding mode control algorithm is developed to synthesize 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 accomodate these uncertainties without knowing exactly the bounds of these uncertainties. The stability of the overall control system is proved by using Lyapunov function. The effectiveness of the developed algorithms has been verified on the platform FTLAB747.
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