煤油氧气脉冲爆震火箭发动机爆震特性  

DETONATION CHARACTERISTIC ON KEROSENE/OXYGEN PULSE DETONATION ROCKET ENGINE

作　　者：李强[1] 范玮[1] 严传俊[1] 胡承启[1] 李建玲[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：《工程热物理学报》2008年第1期168-170,共3页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.503336030);教育部优秀青年教师资助计划和新世纪优秀人才计划(No.NCET-04-0960)

摘　　要：脉冲爆震火箭发动机(PDRE)是一种利用脉冲式爆震波产生高温、高压燃气发出的冲量来产生推力的推进系统。与常规液体火箭发动机相比,脉冲爆震火箭发动机具有更高的性能,并且结构更简单。本文以航空煤油为燃料、氧气为氧化剂、压缩氮气为隔离气体,并利用电磁阀控制燃料、氧化剂和隔离气体的间歇式供给。利用低的点火能量(50 mJ),在内径50mm,长度1.1m的爆震管内进行了大量的多循环爆震试验,研究煤油氧气电磁阀脉冲爆震火箭发动机的爆震波特性。研究结果为进一步研究气液两相多次爆震燃烧机理提供了依据,为研制工程应用的PDRE提供理论和实践基础。Unlike conventional steady-state rocket engines, which use constant pressure combustion, PDREs utilize the high-energy release rate and thermodynamic characteristics of detonation waves to produce thrust. This enables PDREs to operate at higher thermodynamic efficiencies. In this paper, the PDRE test model utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. Solenoid valves were employed to control intermittent supplies of kerosene, oxygen, and purge gas. The spark plug igniter used in these experiments had ignition energy of only around 50 mJ. Solenoid valves and spark plug are controlled by the control and ignition system. DDT enhancement device Shchelkin spiral was used in the test model. Six pressure transducers placed on the detonation tube at different locations from the thrust wall were used to measure pressure trace. Detonation characteristic on kerosene/oxygen PDRE was experimentally investigated.

关 键 词：煤油 氧气 脉冲爆震 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]