Application of Fault Tolerant Control Using Sliding Modes With On-line Control Allocation on a Large Civil Aircraft

This paper describes an on-line sliding mode control allocation scheme for fault tolerant control of the lateral and longitudinal axes of the non-linear B747 aircraft. The effectiveness level of the actuators is used by the control allocation scheme to redistribute the control signals to the functioning actuators when a fault or failure occurs. The simulation results on the non-linear B747 model show good performance when tested on different fault and even certain total actuator failure scenarios without reconfiguring the controller.