摘要
为研究一种高频脉冲爆震火箭发动机(Pulse Detonation Rocket Engine,简称PDRE)的排气及推力特性,开展了相关实验和数值模拟研究。利用高速摄影拍摄了PDRE高频工作下的排气阴影图和尾焰图。构建了PDRE单次工作过程的数值模型,得到了发动机的排气过程和推力特性。结果表明:PDRE在靠近出口端点火,形成向封闭端传播的爆震波。回爆波向出口传播,形成第一次排气;在封闭端反射的压力波传出爆震管,形成第二次排气;两次排气贡献的冲量大小相近。
To investigate the exhaust and thrust properties of a high frequency pulse detonation rocket engine(PDRE),experimental and numerical investigations were carried out.High speed camera was utilized to capture the shadowgraph and flame graph of the exhaust process.A numerical model of a single cycle PDRE was designed to study the exhaust process and thrust of the engine.The results indicated that the PDRE was ignited near the open end and the detonation wave propagated to the closed end.The detonation wave propagated to the open end and started the first exhaust process.The compression wave which reflected from the closed end propagated to the open end and started the second exhaust process.The impulses obtained from each exhaust process were nearly the same.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2017年第2期428-434,共7页
Journal of Engineering Thermophysics
基金
国家自然科学基金资助项目(No.91441201
No.91641101
No.51176158)
关键词
脉冲爆震
高速摄影
排气
推力
pulse detonation
high speed camera
exhaust
thrust