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.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2001年第4期81-84,共4页
Journal of Astronautics
基金
863基金资助项目
