研究存在参数不确定和非最小相位特性的吸气式高超声速飞行器的控制律设计问题. 通过深入分析被控对象的动力学特点, 提出了一种新型设计思想. 将系统分为速度子系统和俯仰动力学子系统分别进行设计. 针对速度子系统, 设计自适应动态逆控制; 针对非最小相位俯仰动力学子系统, 设计高增益自适应动态面控制. 稳定性分析表明, 系统的跟踪误差是一致最终有界的, 其它状态是有界的. 最后的数值仿真验证了该方法的有效性.

In this paper, the control design problem is investigated for air-breathing hypersonic flight vehicle with uncertain parameters and nonminimum phase characteristic. Based on analysis of the plant's dynamics, a novel design philosophy is presented. Firstly, this model is separated as velocity subsystem and pitch dynamics subsystem. For the former, an adaptive dynamic inversion controller is derived. For the latter, a high-gain adaptive dynamic surface controller is designed. Furthermore, the stability analysis shows the tracking errors are ultimately uniformly bounded and other states are bounded. Finally, simulation results validate the proposed method.