脉冲爆震火箭发动机高频实验研究  

Experiments on high frequency pulse detonation rocket engine

作　　者：陈巍[1] 范玮[1] 李建玲[1] 王可[1] 严传俊[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2011年第3期443-446,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金(50976094);教育部博士点基金(20096102110022);西北工业大学研究生创新实验中心资助项目(10006)

摘　　要：为了研究脉冲爆震发动机的高频工作特性,以航空煤油和压缩氧气为推进剂,采用爆震增强装置,增大推进剂供给压力以及增大电磁阀控制气压力等措施,在脉冲爆震火箭发动机模型上进行了实验,成功获得45Hz时的爆震压力波形。实验结果表明,频率增高,爆震波峰值压力下降,有利于加速缓燃向爆震的转变(Defla-gration to Detonation Transition,DDT)。当爆震充分发展时,爆震波波速基本不变,峰值压力上升时间趋于定值。工作频率为45 Hz时,爆震波峰值的压力为3.2 MPa,爆震波的波速为1 715.5m/s。In order to study the high frequency pulse detonation rocket engine performance characteristics,aviation kerosene and compressed oxygen were chosen as propellants.A series of measurments were taken to improve the frequency,such as by increasing the propellants supply pressure and valve control pressure.Experiments were conducted on the pulse detonation rocket engine model and a maximum operation frequency of 45 Hz was realized.Experimental results show that the increasing of operation frequency benefits for deflagration to detonation transition while the detonation peak pressure reduces.When the detonation was well developed,both the velocity and the peak pressure tended to be fixed values.When PDRE worked at frequency of 45 Hz,the peak pressure was of 3.2 MPa and the velocity was of 1 715.5 m/s.

关 键 词：脉冲爆震火箭发动机 高频 波峰压力 波速 上升时间 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]