液体火箭发动机气动谐振点火初步研究  

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

作　　者：梁国柱[1] 张国舟[1] 程显辰[1] 马彬[1] 张振鹏[1] 

机构地区：[1]北京航空航天大学宇航学院

出　　处：《推进技术》1999年第4期13-16,共4页Journal of Propulsion Technology

基　　金：国家"八六三"基金

摘　　要：气动谐振点火是基于气动谐振加热现象的一种新型的点火方式。在特定的气动谐振条件下，高速喷流与谐振管内流相互作用形成周期性运动的激波和膨胀波，将压缩气体的能量不可逆地转化为热能，形成高温高能的点火源，从而点燃推进剂组元。建立了简化的理论分析模型，对可能获得的最高温度进行了预测，探讨了在液体火箭发动机上实现气动谐振点火的方案。Gas dynamic resonance ignition(GDRI),based on the gas dynamic resonance heating phenomenon,is a new type of gas dynamic ignition method.The ignition device consists of a resonance tube which is a hollow cylinder closed at one end and an excitation nozzle.Under particular resonance conditions,the interaction of the high velocity jet and the intemal cavity flow in the resonance tube generates periodic traveling shock and expansion waves which convert the flow energy of compressed gas into thermal energy irreversibly.Hence,a high temperature and high energetic ignition source which is used to ignite rocket propellants can be obtained.This paper presents a simplified theoretical model to predict the maximum attainable temperature of this heating process,and discusses possible conceptual schemes that may be applied to liquid propellant rocket engines .

关 键 词：液体火箭发动机 点火系统 气动加热 方案研究 

分 类 号：V434.11[航空宇航科学与技术—航空宇航推进理论与工程]