介绍了飞机环境控制系统中发动机引气、热交换器、管道、文氏管以及阀门等部件的数学模型。
The mathematical model for aircraft engine, heat exchanger, duct, venturi, valve and other components in aircraft environment control system (AECS) is described in this paper.
通过模块化编程，建立了新一代高性能补燃发动机启动过程的部件模型。
The dynamic models of engine parts in a new high-performance staged combustion cycle liquid propellant rocket through the module codified were built.
首先采用集中参数法，建立了挤压式供应系统的液体火箭发动机各部件的静态及动态数学模型。
Firstly, the static and dynamic mathematic model of the Liquid Propellant Rocket Engine of pressure-fed providing system was established in centralized parameter method.
建立了单组元发动机推力室系统（包括结构部件如隔热框、催化床、喷管等）的传热模型。
Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame, catalyst bed, nozzle etc.
采用部件建模技术，建立了某型发动机核心机实时动态数学模型。
The real-time dynamic mathematical model for an core engine is established using component modeling technology.
然后，利用建立的数学模型分析部件材料温升对燃气涡轮轴发动机起动性能的影响。
Then, the model was used to analyze component material warm-up effect on the turboshaft engine starting characteristics.
利用模型辅助模式搜索方法(MAPS方法)，研究了某型涡扇发动机基于部件级非线性实时数学模型的性能寻优控制。
Model-Assisted Pattern Search method (MAPS) was applied to the study of performance seeking control using an aircraft engine nonlinear component level model.
基于各部件特性进行涡扇发动机小偏差模型研究时，需用到风扇和压气机的通用特性图。
The general characteristic maps of fan and Compressor is necessary for turbofan engine little deviation modeling which based on component characteristics.
基于各部件特性进行涡扇发动机小偏差模型研究时，需用到风扇和压气机的通用特性图。
The general characteristic maps of fan and Compressor is necessary for turbofan engine little deviation modeling which based on component characteristics.
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