飞机发动机逼喘实验器液压控制系统研究

Research on Hydraulic Control System of Aircraft Engine Surge Tester

为了获得发动机的喘振工作点,降低由喘振引起的飞行风险,通过对军工行业中飞机发动机逼喘进行实验,设计了一台满足实验要求的实验器。在设计该实验器液压控制原理图的同时,着重分析了其闭环位置控制系统,并建立AMESim模型。最终通过仿真分析速度前馈、加速度前馈对系统响应时间的影响,证明了该方法可显著提高系统控制效果和实现较高的系统稳定性。

In order to obtain the surge operating point of the engine and reduce the flight risk caused by the surge,an experimental device that meets the experimental requirements was designed through experiments on the surge of aircraft engines in the military industry.While designing the hydraulic control schematic diagram of the experimental device,the closed-loop position control system was analyzed and the AMEsim model was established.Finally,the influence of speed feedforward and acceleration feedforward on system response time is analyzed through simulation,which proves that the method can significantly improve the system control effect and achieve higher system stability.