摘要
为实现脉冲爆震火箭发动机(PDRE)引射模态下主爆震室的起爆,采用航空煤油和氧气作为推进剂,设计了PDRE引射模态的模型机,采用压电传感器测量主爆震室中爆震波的压力和速度。在主爆震室中成功实现了5～8Hz稳定连续的爆震,爆震波的峰值压力能够达到3MPa,爆震波以1600～2000m/s左右的速度在主爆震室中传播。实验结果表明:PDRE引射模态下主爆震室的DDT距离,远低于常规高能电喷起爆下的两相PDRE的DDT距离;高频PDRE引射模态下主爆震室的起爆难度加大;加长主爆震室、末端增加收敛段可以提高引射模态的爆震性能。
To achieve the initiation in the main detonation chamber at the ejector mode of a pulse deto- nation rocket engine（PDRE） , a model engine was designed using kerosene as fuel and oxygen as oxidizer. The model engine was designed and the peak pressure and the velocity of detonation waves were measured in the main detonation chamber utilizing piezoelectric sensors. The detonation was formed at a frequency ran- ging from 5Hz to 8Hz with a peak pressure of 3MPa in the main detonation chamber, and propagated at a speed of 1600 - 2000m/s. The experimental results indicate that the distance of DDT in the main detonation chamber at the ejector mode of a PDRE is much shorter than that in a conventional two-phase PDRE ignited by a spark plug. With the increase of frequency, it will be more difficult to achieve an ejector mode of PDRE. The ejector mode performance may be improved by increasing the length of the main detonation chamber and employing the convergent nozzle at the end of the ejector.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第8期1147-1152,共6页
Journal of Propulsion Technology
基金
国家自然科学基金项目(50976094
51176158)
教育部博士点基金项目(20096102110022)
基础研究基金(JC201142)
关键词
脉冲爆震火箭发动机
引射模态
主爆震室
实验研究
峰值压力
Pulse detonation rocket engine
Ejector mode
Main detonation chamber
Experimentinvestigation
Peak pressure
