基于非仿射模型的高超声速飞行器预设性能控制器

针对高超声速飞行器非仿射模型提出预设性能控制方法，设计了一种新型预设性能函数来保证控制器的动态性能和稳态性能，通过构造误差转化函数将最初的受限系统转化为等效的不受限系统来简化控制器设计.将高超声速飞行器纵向动力学模型分解为速度和高度子系统并分别设计控制律.对于高度子系统，使用高阶跟踪微分器对误差进行估计，引入模糊函数对未知项进行逼近，避免了反演控制中的反复求导；对于速度子系统，直接根据预设性能函数设计比例积分控制器.所设计的控制律在参数不确定和干扰的情况下保证了期望的动态性能和稳态精度，同时降低了计算量.最后，通过仿真实验验证了控制器的有效性. 

Prescribed Performance Control for Hypersonic Flight Vehicles Based on Non-Affine Models

A prescribed performance control method was proposed for the hypersonic flight vehicle non-affine model. A new performance function was designed to ensure the transient performance and steady state performance of the controller. The initial constricted system was transformed into the equivalent unrestricted system by constructing the transformed error function to simplify controller design. The longitudinal dynamics model of the hypersonic flight vehicle was decomposed into velocity and altitude subsystems and the control laws were designed separately. For the altitude subsystem, a high-order tracking differentiator was used to estimate the error, and the fuzzy function was introduced to approximate the unknown, avoiding the repeated derivation in the back-stepping control. For the velocity subsystem, the proportional integral controller was directly designed according to the prescribed performance function. Finally, the effectiveness of the controller was verified by simulation experiments. Results show that, the designed control laws can improve the transient performance and steady-state accuracy under the condition of parameter uncertainty and disturbance, and reduce the computational load.