摘要
航空推进系统仿真技术在发动机预研和型号研制中具有重要的作用。某型现役飞机飞行高度增加,需对其燃油调节器进行改型设计,而关于航空发动机燃油调节仿真的问题,大多数是以传递函数及插值表等形式来描述的,计算量大,物理意义不直观,仿真效果不明显。针对以上不足,在对某型发动机燃油调节器的组成、功能、工作原理进行了详细分析的基础上,以流量连续方程及力平衡方程为基础,结合Adaptive Simpson积分方法,基于AMEsim仿真软件,采用图形化时域仿真建模方式建立了相关部件的数学模型,对其高空工作特性进行了仿真分析。结果表明,保证了发动机的正常工作,为燃油调节器的设计与改进提供了依据。
In the field of aviation propulsion system, simulation technologies are becoming more and more impor- tant in the processes of advanced research and model research project. As the plane flight level increases, the fuel controller needs to be modified. However, the aero - engine fuel regulating simulation is mostly expressed as transfer function and interpolation table. It needs large amount of calculation, the physical significance is ambiguous and the simulation results are inferior. In order to solve the above problems, on the basis of analysing the composing, functio- ning and operating principle of the aero - engine fuel controller in detail, and by utilizing flow continuous equation and force equilibrium equation, combining with Adaptive Simpson integration method, and using AMEsim simulation software and schematize time domain simulation modeling methods, we set up the mathematical model and simulate the aloft working characteristics. The simulation results show that it can not only ensure the normal work of the aero - engine, but also provide the basis for design and improvement of the fuel controller.
出处
《计算机仿真》
CSCD
北大核心
2012年第8期81-84,共4页
Computer Simulation
关键词
燃油调节器
改型
建模
仿真
Fuel controller
Modified
Modeling
Simulation
