Scheduled Fault Tolerant Integral Sliding Mode Control for BWB Aircraft

Due to the unconventional layout of a Blended Wing Body aircraft the available actuators provide little control authority: this situation is exacerbated in situations where the actuators are subject to actuator faults and failures. This paper proposes an optimised integral sliding mode scheme, with control allocation, to ensure that the actuators provide the best possible system performance without producing infeasible input signals in the presence of faults and failures. This is predominantly achieved through a novel form of Sliding Mode Control. The scheme is tested on the lateral dynamics of a 6 DoF non-linear model of a Blended Wing Body aircraft in the presence of severe actuator faults and failures.