高超声速飞行器非线性控制系统设计

Nonlinear control system design for hypersonic vehicle

针对高超声速飞行器非线性强且参数快时变、不确定的特点,提出基于状态相关的Riccati方程(SDRE)模型参考跟踪控制系统设计方法。对于高超声速三通道强耦合非线性模型,引入参考模型建立类线性增广系统。针对此类线性增广系统,采用SDRE方法设计了模型参考跟踪控制器,并采用改进的Newton法进行求解。最后,在高超声速滑翔条件下进行了数学仿真,通过与LQR线性控制方法的仿真效果比较,验证了该方法的有效性和优越性。

In allusion to the nonlinear coupled feature of hypersonic vehicle with fast varying uncertain model parameters, a state-dependent Riccati equation （SDRE） model reference following control system design method is presented. The augmented system is established by introducing the referenced model and transferring to a similar linear structure with state dependent coefficient （SDC）. For this kind of line- ar augmentation system, a model reference following controller is designed with the method of SDRE. In order to enhance the accuracy, the improved Newton method is adopted to solve the equation. The de- signed controller is used to simulate in the hypersonic gliding condition. Simulation results verify the ef- fectiveness and superiority of the proposed control strategy by comparing with the results using the LQR method.