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Aircraft actuator damage is one of the main causes of the loss of control during the flight. The Aircraft dynamic are severely affected by the faults and failures and if the corrective command signals are not supplied immediately, damages will lead aircraft to catastrophic consequences such as instability and system performance degradation and deadly plane crashes will be occurred. This paper presents a fault-tolerant control technique based on nonlinear optimal control method using State-Dependent Riccati Equation. Two fault and failure scenarios including loss of elevator effectiveness and aileron hard-over for a large transport aircraft is considered and the performance of State-Dependent Riccati Equation method is evaluated in comparison with its linear counterpart (Linear Quadratic Regulator). For the first time this technique as a fault-tolerant flight control method has used in the internal investigations. Simulation results demonstrate the effectiveness of the proposed nonlinear approach in restoring stability and maintaining the flight path.

Keywords: Fault-tolerant control, nonlinear optimal control, State-Dependent Riccati equation, Actuator fault, Actuator failure

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