弹性高超声速飞行器自适应极点配置控制

本文针对乘波体外形的高超声速飞行器存在的结构/推进/气动强耦合特性，利用鲁棒极点配置方法设计了自适应控制器，实现了对高超声速飞行器的速度和高度指令跟踪控制。控制器采用了Proportional-Integral-Filter(PIF)结构，该结构的控制器不仅能够使系统具备良好的稳态特性而且能够对控制信号进行滤波平滑，从而能够有效地抑制高超声速飞行器的弹性振动对控制系统的影响。基于弹性高超声速飞行器模型CSUAL_GHV，分别采用自适应鲁棒极点配置控制方法和自适应非鲁棒极点配置控制方法进行了数值仿真。结果表明，与非鲁棒极点配置控制方法相比，采用自适应鲁棒极点配置控制方法的控制系统不仅使飞行器能够很快地跟踪上速度和高度指令，跟踪误差小于1%，而且高超声速飞行器的弹性振动也得到了有效地抑制。飞行器在整个飞行过程中的飞行攻角均处于±2°范围内，满足超燃冲压发动机的工作要求。

Adaptive Pole Assignment Control of an Elastic Hypersonic Vehicle

This paper uses robust pole assignment method to design an adaptive velocity and altitude tracking control algorithm for the longitudinal model of a wave rider configuration air-breathing hypersonic vehicle, which has strong coupling between structure, propulsion and aerodynamics. The controller uses the Proportional-Integral-Filter structure, which not only can make the system to have good steady-state characteristics, but also can smooth the control inputs with low-pass filters, thus can suppress the effect of structure vibration on the control system effectively. Base on the elastic hypersonic vehicle model CSUAL_GHV, the simulations using adaptive robust pole assignment control method and adaptive non-robust pole assignment control method are carried out respectively. The results show that, compared with the non-robust pole assignment control method, control system using adaptive robust pole assignment control method not only achieves the velocity and altitude tracking goal with tracking error less than 1%, but also the vibration motion of the hypersonic vehicle is suppressed sufficiently. The angle of attack of the hypersonic vehicle stays in the range of ±2°, which satisfies the working requirements of the scramjet.