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

作　　者：王育虔[1] 范玮[1] 严传俊[1] 李强[1] 李建玲[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2008年第11期2119-2123,共5页Journal of Aerospace Power

基　　金：国家自然科学基金(50106012;50336030);教育部新世纪优秀人才计划(NCET-04-0960)

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30 mm,长度1 000 mm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20－30 Hz频率下多循环稳定工作.工作频率为30 Hz时,爆震波峰值压力达到2.2 MPa.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.In order to increase the operation frequency of a pulse detonation rocket en gine （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 fre queney is 30 Hz, the peak valuable of detonation wave pressure is 2.2 MPa. The time-aver aged thrust of PDRE increases almost linearly with the operation frequency .

关 键 词：脉冲爆震火箭发动机 工作频率 电磁阀 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]