飞翼无人机非线性控制设计方法

Flying wing UAV control design study of nonlinear method and flight validation

为实现飞翼无人机的机动飞行,以带有流体矢量方向舵的飞翼无人机为设计对象,采用非线性设计方法设计了控制器,并进行飞行验证.针对飞翼无人机的机动飞行控制存在各种耦合和扰动的特点,设计内环线性化解耦以消除已知不利的耦合项,外环反步跟踪方法进行航迹跟踪的控制律结构,证明了该控制结构的稳定性.同传统反步控制方法相比,该控制器增加了内环解耦结构,并在控制结构中保留气动阻尼项,使得线性化后的系统为弱非线性系统.该结构不仅可以降低外环控制器设计的保守性,而且便于工程实现.仿真和飞行试验表明,该控制方案是有效的.

For realization of the flying wing UAV maneuvering flight,a fluid vector rudder flying wing UAV as study object,the controller is designed by using the nonlinear design method and carried out flight validation. As the existence of various coupling and disturbance in the maneuvering flight control of flying wing UAV,a novel control scheme that the inner loop use linearization decoupling methods to eliminate the known negative coupling and the outer loop use backstepping methods for trajectory tracking control is used. Compared with the traditional backstepping control method, the controller increases the inner loop decoupling structure, and retains the aerodynamic damping term in the control structure,which makes the linearized system as a weak nonlinear system.The proposed contro structure not only can reduce the conservatism of the outer loop controller design,but also is convenient in practical engineering realization. Finally,Simulation and flight results show that the proposed control scheme is effective.