非对称变后掠柔性后缘飞机滚转控制分配研究

Previous studies have shown that the maneuverability of aircraft can be enhanced by changing the sweepback and wing camber separately. The convergence characteristics of aircraft roll control with sweep angle as a new redundant controller are investigated. Firstly, the method of computational fluid dynamics is used to establish roll efficiency functions for both general control surfaces under different working conditions, and Kane's method is used for the dynamics equations of stable roll subsystem. Then, on the basis of dynamic model of the stable roll subsystem established by Kane's method, the control laws of the main and supervisory controller are determined under supervisory-main control architecture by considering the influence of the damping moment. Finally, with asymmetric change of sweep as the redundant input of the system, the convergence characteristics of the stable roll motion of the aircraft under different working conditions are analyzed by introducing the deflection rate of generalized control surfaces as characteristics quantity. Analysis results show that using redundant control surfaces can effectively increase rolling moment and prevent controllers from turning into saturation state, which will improve the control efficiency inside the whole flight envelope. Simulation results under two working conditions show that using sweepback generalized control surface can enhance system's fault tolerance capability and improve the performance of aircraft under high lift, but will increase the time required to stabilize the system.