Abstract
This paper presents an approach to obtain fault tolerance in the nonlinear longitudinal motion of an aircraft. The approach uses a Sliding Mode Controller and Control Allocation to obtain fault tolerance. In the nominal fault free case only a primary control will be active. A Sliding Mode Controller provides some robustness to the system and this property is utilized for fault accommodation if a partial fault has occurred. Control Allocation is added to redistribute control to available healthy actuators to make the system fault tolerant against more severe faults and even to total loss of a control surface. Simulations have been conducted on a model of a Cessna 182 and have shown good results for both the nominal and faulty scenarios.
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