应用气动谐振的气氧、煤油点火器的方案研究  

Investigation on methods of kerosene/oxygen ignition using gas dynamic resonance technique

作　　者：俞南嘉[1] 张国舟[1] 马彬[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《北京航空航天大学学报》2003年第9期759-762,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航天科技创新基金 2 0 0 0年资助项目

摘　　要：为了实现液体推进剂火箭发动机的多次可靠起动 ,将气动谐振点火技术应用于气氧煤油的点火 .提出了两种应用气动谐振的气氧煤油点火器方案 :直接点火方案和间接点火方案 .在直接点火方案中对气氧与煤油同轴喷入和煤油由顶部喷入两种不同的点火方式进行了分析比较 .在间接点火方案中对点火火炬为富燃和富氧两种情况进行了对比分析 .试验研究表明两种方案均实现了多次可靠的点火并生成了稳定的点火火炬 .通过对两种方案的优缺点、工程上应用的技术可行性和存在的技术难点的分析 。In order to realize the multiple ignitions of liquid rocket engines reliably, gas dynamic resonance ignition was applied to ignite kerosene/oxygen. Two ignition methods of kerosene/oxygen igniter, direct ignition and indirect ignition, were discussed. For direct ignition method, the differences between co-axial injection of kerosene/oxygen and top injection of kerosene were compared. For indirect ignition method, the condition of fuel-rich ignition torch was studied in contrast with the condition of fuel-lean ignition torch. According to the analysis of technical feasibility and difficulty, it can be concluded from experiments that both methods are valid for ignition, while indirect ignition method with fuel-rich torch has more advantages and is prospective to realize in engineering application within a short term.

关 键 词：点火装置 谐振腔 液体推进剂火箭发动机 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]