航空发动机LQG/LTR多变量控制器实验验证

Experimental Verification of LQG/LTR Method For Aeroengine Control System

针对航空发动机这一具有耦合和强非线性被控对象,引入了LQG/LTR多变量控制器设计方法,在介绍其原理的基础上利用该方法设计了某型航空涡扇发动机的LQG/LTR控制器;为了检验所设计控制器的性能,设计了硬件在回路仿真系统,从软件编程和硬件选型构建两方面介绍了仿真系统的设计方法,并利用构建的仿真系统验证了所设计的LQG/LTR控制器具有良好的鲁棒性和抗干扰性,表明LQG/LTR方法适合用于航空发动机多变量控制器设计,所设计的硬件仿真系统能较好的再现发动机及其控制系统的工作过程。

A method of LQG/LTR was introduced, in accordance with the LQG/LTR design step, the LQG/LTR controller has been designed for the turbofan aeroengine with strong nonlinearity. The hardware-in-the-loop simulation system was designed in order to validate the performance of the cnotroller and the simulation process have been performed. Excellent robustness and antidisturbance are obtained, and demands of multivariable control of aeroengine are reached.