电磁阀式两相脉冲爆震火箭发动机试验
Investigation on two-phase pulse detonation rocket engine with solenoid valve
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摘要: 为了提高脉冲爆震火箭发动机的工作频率,设计了一台内径30mm,长度1000mm的电磁阀式脉冲爆震火箭发动机模型.脉冲爆震火箭发动机模型采用航空煤油为燃料,压缩氧气为氧化剂,压缩氮气为隔离气体,通过选用高速大流量电磁阀,加热燃料,安装Shchelkin螺旋等方法,使得该模型能够在20~30Hz频率下多循环稳定工作.工作频率为30Hz时,爆震波峰值压力达到2.2MPa.脉冲爆震火箭发动机的时均推力随着工作频率的提高接近线性增大.Abstract: In order to increase the operation frequency of a pulse detonation rocket engine(PDRE),a PDRE model with solenoid valve was designed whose diameter and length was 30 mm and 1 000 mm respectively.The model was operated with kerosene as fuel,compressed oxygen as oxidizer and nitrogen as purge gas.The PDRE model could steadily operate at the frequency of 20~30 Hz after taking such measures as selecting high-speed large flow solenoids,heating the fuel and assembling Shchelkin spiral.While the operation frequency is 30 Hz,the peak valuable of detonation wave pressure is 2.2 MPa.The time-averaged thrust of PDRE increases almost linearly with the operation frequency.
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Key words:
- pulse detonation rocket engine /
- operation frequency /
- solenoid valve
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