Rapid Optimization Design of Hinge Moment for V-Tail Layout Unmanned Aircraft During Complex Maneuver

In response to the problem of excessive hinge moment caused by high-speed deflection of control surfaces during complex maneuvers of unmanned combat aircraft, a rapid optimization design method for hinge moment based on particle swarm optimization algorithm is proposed for a V-tail layout unmanned aerial vehicle. Firstly, the six-degree-of-freedom model of the unmanned aircraft is established. Secondly, for the characteristics of barrel roll maneuvers, a control law is designed using the active disturbance rejection method to improve the response speed and robustness of complex maneuvers. Finally, by minimizing the hinge moment and integral time absolute error (ITAE) criteria, the controller parameters are optimized using the particle swarm optimization algorithm. Simulation results show that the optimized parameters obtained by this method make the aircraft controller have better control performance, can accurately realize barrel roll maneuvers, and significantly reduce the servo power consumption caused by hinge moment.