液体火箭发动机气动谐振点火技术的研究  

INVESTIGATION ON GAS DYNAMIC RESONANCE IGNITION TECHNOLOGY FOR LIQUID PROPELLANT ROCKET ENGINE

作　　者：张国舟[1] 童晓艳[1] 梁国柱[1] 马彬[1] 程显辰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2001年第4期81-84,共4页Journal of Astronautics

基　　金：863基金资助项目

摘　　要：基于对液体火箭发动机重复多次可靠起动的要求 ,气动谐振管的热效应可用来形成高温高能的点火源 ,对氢氧液体火箭发动机 ,研制了同轴氢氧谐振点火器 ,对包括氢氧推进剂的所有非自燃液体火箭发动机研究了氦气谐振热表面点火器。研究结果表明这种新型的气动谐振点火技术是结构简单、高可靠性、无毒、无污染的非电钝感点火技术 。Based on the requirement of repeating multiplicity ignition for Liquid Propellant Rocket Engine (LPRE) and gas dynamic resonance heating results can be used to obtain high temperature,high energetic ignition source,for hydrogen oxygen LPRE Coaxial Hydrogen Oxygen Resonance Igniter has been investigated,for all nonspantaneous combustion propellants,which include hydrogen oxygen,Helium Resonance Heating Surface Igniter also has been investigated.Investigative results indicate that Gas Dynamic Resonance Ignition technology is simple construct,high reliability,non poison,non electric and bluntly sensible ignition technology.This new ignition technology has excellent apply prospects for LPRE which require repeating multiplicity ignition.

关 键 词：液体火箭发动机 点火 气动谐振 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]