基于SIMULINK的超声速进气道仿真方法  

A simulation method based on SIMULINK for a supersonic inlet

作　　者：何保成[1] 姚照辉[1] 鲍文[1] 常军涛[1] 

机构地区：[1]哈尔滨工业大学先进动力控制及可靠性研究所

出　　处：《推进技术》2007年第2期199-203,共5页Journal of Propulsion Technology

摘　　要：将进气道一维流动的偏微分方程离散为一系列可积分的线性常微分方程,基于此创建了超声速进气道仿真模型,提出了一种基于SIMULINK的进气道仿真方法,模拟了来流参数和燃烧室反压扰动时流场内各个参数的变化规律。对一个一维变几何超声速进气道进行仿真,获得了结尾正激波的稳态特性及动态特性。该模型定义并输出了激波位置,有效地将一维超声速进气道的分布参数问题转换为零维问题,解决了系统分析与控制系统设计中无法实现集总参数的困难。A computational platform of a supersonic inlet with variable geometry was devewped using MATLAB/SIMULINK. A method based on the platform for simulation of a complicated model has been presented. The correctness and reliability of the new method have been testified by simulating the stationary flow fields of an inlet under back pressure vibration and vibration parameters of incoming air flow. Based on the method, the dy-namic behavior of the terminal normal shock wave in the inlet has been obtained by carrying out a simulation of the object model of an inlet, and the dynamic and stationary characteristics have also been obtained. A complicated distributed parameter problem of an one-dimensional supersonic inlet has been transformed to a zero dimensional problem which overcomes concentrative-parameter difficulty.

关 键 词：超声速进气道 正激波 起动 动态仿真^+ 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]