状态/输入约束下飞-推一体化的保性能安全控制

基于飞行-推力一体化思想提出了一种针对搭载超燃冲压发动机的吸气式高超声速飞行器速度通道的状态/输入约束自适应鲁棒保性能安全控制方案。首先根据超燃冲压发动机的机理分析与计算流体动力模型数据，建立了安全子系统与性能子系统面向控制的仿射非线性模型。之后基于障碍Lyapunov理论与动态面设计方法设计了一套安全子系统状态约束控制器，从理论上保证了飞行器在跟踪指令的全过程中，发动机相关状态不会触碰安全边界，并结合自适应技术与辅助系统提高了该控制系统的鲁棒性。针对性能子系统设计了一套鲁棒自抗扰控制器，达到“保证安全的前提下不折损性能”的目的。仿真结果表明所设计的控制系统可以在保障安全的同时达到预想的性能，并显著放宽了超燃冲压发动机对飞行器飞行姿态的约束，保证了高超声速飞行器的机动灵活性。

Integrated Flight propulsion Performance guaranteed Safety Control with State/Input Constraints

In this paper, a robust adaptive controller with state/input constraints is designed for the velocity channel of an air breathing hypersonic vehicle equipped with a scramjet based on the idea of flight propulsion integration. According to the mechanistic analysis and computation fluid dynamics model data of the scramjet, a control oriented affine nonlinear model is established for the safety and performance subsystems. Then, based on the barrier Lyapunov theory and the dynamic surface design method, a state constrained controller is designed for the safety subsystem, which theoretically ensures that the relevant states of the scramjet will not touch the security boundary. Adaptive techniques and auxiliary systems are used to improve the robustness of the control system. A robust active disturbance rejection controller is designed for the performance subsystem, achieving the objective of ensuring safety without compromising performance. Simulation results show that the control system designed in this paper can achieve the desired performance and greatly relax the constraints of the attitude imposed by the scramjet, which ensures the maneuvrability of the air breathing hypersonic vehicle.