同轴氢氧谐振点火器试验研究  

Experimental investigation for coaxial hydrogen/oxygen resonance ignitor

作　　者：俞南嘉[1] 张国舟[1] 宋雅娜[1] 马彬[1] 童晓艳[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2004年第3期267-270,共4页Journal of Propulsion Technology

基　　金：国家"八六三"项目(863 2 3 4 10(4);863 2 3 4 7);航天科技创新基金2000年资助项目。

摘　　要：在环形喷嘴气动谐振加热的试验研究基础上,对同轴氢氧谐振点火器进行了点火性能试验和反压试验研究,结果表明:点火器能为液体火箭发动机可靠点火提供强大热流;能重复多次点火,寿命长;点火器抗系统干扰能力强,点火器出口反压快速增长时,点火器不会熄火,仍能持续提供稳定的氢氧火炬。非电钝感的同轴氢氧谐振点火器可作为正在研究发展中的可重复使用液体火箭发动机多次点火的优选方案之一。Gas-dynamic resonance heating tests for coaxial ring injector are performed for investigating coaxial hydrogen/oxygen resonance ignitor to validate the performance of resonance ignitor.It can be concluded from experiments that resonance ignitor can supply steady strong torch for liquid rocket engine ignition,multi-ignition,and with long life-span. The ignitor can work reliably when inlet pressure of hydrogen and oxygen changed and even when back pressure rise up quickly. Coaxial hydrogen/oxygen resonance ignitor is non-electric and bluntly sensible,which is good ignition scheme for the developing reusable liquid rocket engine.

关 键 词：液体推进剂火箭发动机 点火器 点火试验 性能测试 

分 类 号：V434.24[航空宇航科学与技术—航空宇航推进理论与工程]