当量比对脉冲爆震火箭发动机爆震特性影响的实验研究  

Experimental Investigations of the Effect of Equivalence Ratio on Detonation Characteristic Parameters of Pulse Detonation Rocket Engines

作　　者：丁永强[1] 范玮[1] 李强[1] 万兴[1] 严传俊[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《机械科学与技术》2005年第11期1371-1373,共3页Mechanical Science and Technology for Aerospace Engineering

基　　金：国家自然科学基金项目(50106012;50336030);教育部优秀青年教师资助计划的资助

摘　　要：简述了脉冲爆震火箭发动机的实验系统,利用电磁阀控制煤油,氧气和隔离气体,避免了连续燃烧.分析了实验结果,总结出爆震波压力、传播速度和爆燃向爆震转变(DTD)距离与当量比的关系,指出在当量比为1.2～1.8时爆震特性较好,与理论计算结果趋势一致.研究表明:本实验系统能够成功地进行煤油/氧气脉冲爆震火箭发动机原理试验,能产生频率可控的、充分发展的两相爆震波.A prototype of pulse detonation rocket engine（PDRE） is introduced to solenoid valves for the control of oxygen, kerosene and isolation gas; thus continuous combustion is avoided. Detonation wave pressure, velocity and deflagration-to-detonation distance vs. equivalence ratio in experiments are meas- ured and analyzed, and the results show that detonation characteristics are better when equivalence ratio is between 1.2 to 1.8. The comparison of these results with theoretical ones reveals that they are in good ac- cordance. The research demonstrates that the prototype operates well and can produce frequency-controlla- ble, fully-developed, kerosene/oxygen detonation waves.

关 键 词：脉冲爆震火箭发动机 电磁阀 氧气/煤油 爆震波 特性参数 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]