固体燃料冲压发动机内旁路分气流场数值模拟  

Numerical simulation on the flow field of solid fuel ramjet with inner bypass

作　　者：刘巍[1] 杨涛[1] 程兴华[1] 李理[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2010年第3期257-260,275,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(50376072)

摘　　要：为了调节固体燃料冲压发动机推力,提出了一种内旁路分气结构型式,采用数值模拟方法对该结构的流场进行了分析。研究发现,可以通过改变旁路进气量调节发动机推力,而且旁路进气使补燃室头部出现对称旋涡,对增强燃烧较为有利。内旁路分气结构不需要采用后置旁侧进气道,可有效减小导弹体积、质量与阻力,在中小型发动机上具有较好的应用前景。In order to regulate the thrust of solid fuel ramjet,a new inner bypass structure was presented,and the flow field characteristic of the structure was numerically studied.It was concluded that the thrust can be regulated with regulated bypass air mass flow rate.A symmetrical vortex was found in the head of afterburning chamber which could enhance the combustion.The inner bypass structure is attractive because it does not require the aft bypass supersonic inlet and the mass and drag of the missile can be reduced.

关 键 词：固体燃料冲压发动机 旁路+ 推力调节 数值仿真 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]