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针对吸气式高超声速飞行器的航迹角动态中由于升降舵控制面与升力耦合所引起的非最小相位问题,提出了非线性等效控制方法,设计了高度和速度稳定跟踪控制器。将高度跟踪系统划分为高度-航迹角子系统与攻角-俯仰率子系统,分别设计了关于航迹角和攻角的虚拟控制输入,另将升降舵和鸭翼偏转角等真实控制量设计为等效控制矢量,并利用坐标变换,将两个子系统构成一个输入状态稳定的互联子系统。对于速度跟踪系统,则采用了动态逆方法进行控制。并利用Matlab对带弹性的高超声速飞行器进行了仿真验证,仿真结果说明了该控制方法的有效性。
Aiming at the problem of non-minimum phase caused by the coupling between elevator control plane and lift in the track-angle dynamics of the aspirated hypersonic vehicle, a nonlinear equivalent control method is proposed and a height and velocity stable tracking controller is designed. The altitude tracking system is divided into altitude-track subsystem and pitch-pitch subsystem. The virtual control inputs for track angle and angle of attack are designed respectively. The actual control volume of elevator and duck wing deflection angle is designed as Equivalent control vectors and using coordinate transformation, the two subsystems form an interconnected subsystem with stable input states. For speed tracking system, the dynamic inverse method is used to control. The simulation of the hypersonic vehicle with elasticity is carried out by Matlab. The simulation results show the effectiveness of the control method.