加速型高超飞行器变几何进气道设计分析  

Study on variable geometry inlet of acceleration hypersonic vehicle

作　　者：陈兵[1] 谷良贤[1] 龚春林[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2013年第4期431-436,共6页Journal of Solid Rocket Technology

摘　　要：针对适用于加速型宽速域高超声速飞行器的变几何进气道进行了设计，采用了可动唇口和可变压缩面，为了几何实现简单，采用分级可调方式，在Ma≈4进行几何调节。这种结构保证了飞行器在低速段的正常起动和流量系数，同时也保证了飞行器在高速条件下的压缩性能，能保证在Ma=2．5-8之间进气道的正常高效工作。对该进气道进行了性能计算，计算结果显示了适用于低马赫数的进气道构型无法满足高马赫数条件下的压缩性，而适用于高马赫数条件的进气道构型低马赫数下的起动问题严重，流量系数较低。因此，对于速域较宽的吸气式飞行器，固定结构进气道很难满足任务需求，采用变结构进气道是一种趋势。The variable geometry inlet used on acceleration hypersonic vehicles was designed. Containing movable cowl and ramps ,the structure could realize variable geometry adjustment at Mach 4. The geometry has good restart characteristic and high flux coefficient. At the same time the compressed property is good at high speed. The inlet can work normally and efficiently between Mach 2.5 and Mach 8. The performance of the inlet was calculated. The results show that the configuration used in low mach number cant meet the compressed property requirement at high Mach number,while the configuration used in high Mach number cant satisfy the restart character and the flux coefficient is low at low speed. The fixed inlet cant fulfil the task requirement for the air-breathing vehicle working in wide speed. It＇s a tendency to adopt the variable geometry inlet.

关 键 词：加速型 高超飞行器 变几何进气道 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]