高超声速进气道发展研究  

Research on Development of Hypersonic Inlet

作　　者：徐锦[1] 罗金玲 戴梧叶 

机构地区：[1]北京机电工程研究所,北京100074 [2]北京空天技术研究所,北京100074

出　　处：《战术导弹技术》2016年第5期25-32,共8页Tactical Missile Technology

摘　　要：论述了国内外高超声速进气道的最新研究动态,概括阐述了轴对称进气道、二维进气道、三维侧压式进气道和三维内收缩进气道的典型特点与性能,重点展开分析了三维内收缩进气道的设计原理与种类,包括基于流线追踪的内乘波进气道、几何变截面过渡的进气道和气动变截面过渡的进气道,介绍了该类进气道的优缺点与应用前景,最后对高超声速进气道研究应用方向进行了展望,指出三维内收缩进气道是目前新型高超声速飞行器研究与应用的热点,但其与机体一体化设计带来的内外流强耦合问题,值得深入研究。The development of airbreathing vehicles is one of the focuses in international completion for near space flight. The latest research on hypersonic inlet at home and abroad is presented,the typical characteristics and performances of axial symmetry inlet,two-dimensional inlet,sidewall compression inlet and three-dimensional inward turning inlet are summarized. Moreover the design principle and varieties of three-dimensional inward turning inlet are particularly proposed in detail,including streamtraced inlet,geometrical section-controllable internal waverider inlet and aerodynamic section-controllable internal waverider inlet etc. The relative merits and application of three-dimensional inward turning inlet are introduced. Finally the future development trend of the hypersonic inlet research and application is suggested and the study of three-dimensional inward turning inlet is the focus issue,but the inner-out flow problem caused by integrated design is definitely worth exploring.

关 键 词：高超声速 轴对称进气道 二维进气道 侧压式进气道 三维内收缩进气道 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]