超声速进气道及冲压发动机动态特性分析  

Analysis of supersonic air inlet and ramjet dynamic characteristics

作　　者：刘华[1] 雍雪君[1] 梁俊龙[1] 吴宝元[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2012年第3期17-22,共6页Journal of Rocket Propulsion

基　　金：国家"863"项目(2007AA705302)

摘　　要：基于小偏差线性化思想,利用超声速进气道动力学模型计算得到,进气道激波位置和波后压力的响应幅值随频率增大整体趋于减小,但在各阶纵向谐振频率上存在谐振峰。并进一步考虑了燃烧室加质燃烧,分析了冲压发动机气路动态特性,推导出适用于冲压发动机的集中燃烧模型,研究表明在燃油喷注流量的扰动下,冲压发动机幅频响应谐振峰显著。A result, in which the air inlet shock wave position and the wave downstream pressure amplitude decreased with the frequency increase, but there was a harmonic peak on the longitudinal harmonic frequency, was obtained by calculation of supersonic air inlet dynamics model based on a linearization method. The fuel addition in the combustion chamber was farther considered. The dy- namic characteristics of ramjet air path were analyzed. A combustion model applying to the ramjet was deduced out for the ramjet dynamics analysis. The research indicates that the harmonic peak of ramjet amplitude-fxequency response is obvious under the perturbation of fuel jet flow.

关 键 词：超声速进气道 冲压发动机 动态特性 燃烧模型 燃油扰动 

分 类 号：V439-34[航空宇航科学与技术—航空宇航推进理论与工程]