某型发动机燃油控制执行机构仿真与验证试验

Simulation and Validation of Turbojet Fuel Control Actuator

某型飞行验证机采用巡航弹用涡喷发动机为动力,由于飞行包线大大扩展,且发动机工作状态增多,需对燃油调控系统进行仿真,研究发动机控制系统特性。基于质量连续与力平衡方程在MSC EASY5仿真平台框架下建立了燃油调节执行机构的动力学模型,进行了开环控制结构下执行机构系统稳态和动态特性仿真,并在半物理动态模拟实验台上进行了验证试验。研究结果表明,调节器执行机构系统满足发动机工况范围技术指标要求,为发动机控制系统改型研制打下了基础;采用的建模与仿真方法用于工程设计是可行的,为发动机燃油控制系统的设计与仿真研究提供了一种便捷的技术手段。

A test flight vehicle is powered by a certain type turbojet which was originally developed for a cruise missile. Hence the performance of the fuel control system has to be examined because the flight envelope of the test flight vehicle is wider and more operating states have to be controlled. The performance of the fuel control actuator unit was studied under MSC EASY5 soRware platform. The hydrodynamic model was built under EASY5 based on mass, momentum and energy conservations. Then the steady-state and dynamic performance were simulated under an open loop control. Finally, the actuator unit was constructed and tested under a hardware-in-loop dynamic simulation test platform for the validation. The results show that the actuator unit meets the performance requirements and can be used further in the design of the engine control system. The method is shown feasible for simulation of mechanical and hydraulic fuel control actuators in the engineering applications.