摘要
本文设计了由等截面段、扩张段和等截面段构成的超音速燃烧室，并进行了燃烧实验。用一维计算分析实验结果，表明由等截面段、扩张段和等截面段构成的超音速燃烧室，通过一定的喷油方式，能按飞行状态可分别实现超音速燃烧和亚音速燃烧，从而达到把超燃冲压发动机的工作范围下限扩大到飞行马赫数为３。
In this paper,a supersonic combustor formed of a segment with constant cross section,a divergent segment and a segment with constant cross section is designed,and do combustion tests with it It is indicated by one dimensional calculation that supersonic combustion or subsonic combustion can be realized as flight speeds with the supersonic combustor formed of a segment with constant cross section,and by different fuel supplied ways,which makes the flight lower limit of Scramjet engine extended up to flight Mach number 3
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1998年第2期55-60,共6页
Journal of Astronautics
基金
国家自然科学基金
关键词
双模态
超燃
冲压发动机
超音速燃烧
燃烧室
Dual mode scramjet engine Supersonic combustion Subsonic combustion Test research
