Aerodynamic analysis and roll control allocation for asymmetric variable sweep aircraft with flexible trailing edge

The maneuverability of aircraft can be enhanced by changing the sweep angle and camber of wings separately. Using the method of computational fluid dynamics, the feasibility of the combined differential deflection of the generalized control surfaces for rolling maneuver is verified firstly. In addition, roll efficiency functions of redundant lateral control surfaces under different working conditions are established. After that, the dynamics equations of ideal rolling maneuver subsystem are established by using Kane's methods. Based on the aerodynamic analysis results and dynamics equations, the control allocation weights of asymmetric sweep aircraft with flexible trailing edge under the framework of Supervisory-Main Controller are determined. In the end, control laws of main and supervisory controllers are derived. Analysis results show that using redundant control surfaces can effectively increasing roll moment and avoid controller turning into saturation state, which will improve the control efficiency inside the whole flight envelope.