Non-homogeneous disturbance observer-based second order sliding mode control for a tailless aircraft

The paper presents a control scheme for a multi-input multi-output military tailless aircraft fault tolerant control system design. The control scheme consists of an outer-loop controller, and inner-loop controller and an actuator controller. The outer-loop controller and inner-loop controller are designed using a non-homogeneous disturbance observer(DO)-based finite-time convergent second order sliding mode (SOSM) control. The actuator controller is designed by dynamic boundary layer sliding mode, which takes control input saturation into account. Simulation results using the Innovative Control Effectors (ICE) fighter aircraft model show good performance in actuator failure scenarios which validate the effectiveness of the proposed control scheme.