冲压发动机超声速进气道研究进展  

Development of supersonic scramjet inlet

作　　者：侯早[1] 王福民[1] 旷武岳[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》2008年第5期31-34,58,共5页Journal of Rocket Propulsion

摘　　要：超声速进气道是冲压发动机的关键部件之一。简要介绍了冲压发动机常用的典型进气道。重点叙述了进气道的最新研究成果,主要包括等溢流角弯曲前缘侧壁压缩进气道设计概念、支板引射压缩进气道、双模态超燃冲压发动机变几何进气道、全外压缩式超声速"参数进气道"、固定型面方转椭圆形超声速进气道(REST)等的设计概念与方案。最后概括了先进进气道的发展趋势。Supersonic inlet is the key part of a supersonic air-breath engine. In this paper, typical inlets used for supersonic engine are simply introduced, and recent achievements of inlets are described, including hypersonic sidewall compression inlet with constant spillage angle design at non-uniform incoming flow, strutjet compression scramjet inlets, a variable geometry inlet for dual mode ramjet, entirely outside compress supersonic ＂parameters inlet＂ , a fixed-geometry hypersonic inlet with rectangular-to-elliptical shape transition （REST） . Before an inlet design , it is suggested that the design conception of inlet should be innovated, near and far scheming also should be designed. Multicipital point of view together design is especially important.

关 键 词：冲压发动机 超声速进气道 概念创新 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]