摘要
对液体火箭发动机各种点火技术优缺点进行了对比分析,探讨了各种点火技术方案应用于未来先进推进系统的多管多次点火系统的可行性,讨论了各种点火技术应用方案的结构形式.对爆震波点火技术进行了初步研究,建立了气氢气氧爆震波点火的简化理论分析模型,对其在实际液氢液氧发动机中应用的具体方案进行了分析.分析结果表明,爆震波点火技术可以由低压混合气体产生高温高压的爆震产物,爆震波以高马赫数速度传播,迅速到达各点火位置.爆震波点火技术具备良好的同步性能和简单的结构方案形式,适用于液体火箭发动机多管多次同步点火.
The relative merits of several ignition techniques of liquid propellant rocket engine were analyzed. The feasibility of each ignition technique applicable to multi-chamber multi-run ignition system of future advanced propulsion system was discussed. The structural configurations of application scenarios of ignition techniques were considered. Preliminary investigation on detonation wave ignition technique was made and a simplified theoretically analytical model for the mixture of gaseous hydrogen and gaseous oxygen was established. The applicable schemes of the detonation wave ignition for liquid rocket engine were analyzed. The analysis results show that the detonation wave technique can product high pressure ratio and high temperature ratio by low pressure premix detonative gases. The detonation wave propagates with high mach number, and the detonation wave ignition source arrives each ignition place immediately. The detonation wave ignition technique has unique synchronic characteristic and simple structural configuration. It is suitable to multi-chamber multi-run synchronic ignition of liquid propellant rocket engine.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2005年第4期375-380,共6页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家高技术 863计划资助项目 (2 0 0 2AA72 60 2 1)
关键词
火箭发动机
爆震
点火
点火系统
Detonation
Hydrogen
Ignition
Ignition systems
Liquid propellants
Oxygen
Propulsion
