Compound Control System Design for Asymmetric Morphing-Wing Aircraft

Aiming at the attitude control of an asymmetric morphing-wing aircraft, a compound control system is proposed. Based on the dynamic model of the asymmetric morphing-wing aircraft, the morphing wing is regarded as a new active control mechanism and the condition of using the asymmetric morphing wing is determined. A control strategy for the allocation of the control commands is designed by the logic function. The disturbance caused by the morphing wing is estimated by the extended disturbance observer and the variable structure control method with global sliding mode is used to design the compound control system which restrains the violent changes in parameters and disturbance during the process of morphing. According to the simulation, compared to the fixed-wing aircraft, the effectiveness of the asymmetric morphing wing is assessed and the robustness of the controller is also evaluated by the perturbation of the parameters.