某高能推进剂激光点火特性研究  

Study on Laser Ignition Characteristics of A High Energy Propellant

作　　者：平丽[1] 南宝江[1] 吴平[1] 马喜梅[1] 

机构地区：[1]中国航天科技集团公司第4研究院第41所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,陕西西安710025

出　　处：《火炮发射与控制学报》2009年第2期28-31,共4页Journal of Gun Launch & Control

摘　　要：采用CO2激光点火系统,研究了某高能推进剂的点火延迟时间与环境压强、初温、热流密度等因素的关系。研究结果表明,随着环境压强、点火热流密度的增加,推进剂的点火延迟时间缩短,且存在着能够点燃推进剂的压强阈值,其值与点火热流密度有关,当压强高于20.26MPa时,推进剂能被点燃,而低于该值时,则不能被点燃;初温对点火延迟时间的影响程度也取决于热流密度的大小,存在着所谓"拉平效应"。最后给出了该高能推进剂点火延迟时间的经验公式。The effect of ambient pressure, initial temperature and heat fluxes on the ignition delay time of a kind of high energy propellant was examined in detail by use of a COz laser ignition system. The studied results showed that the ignition delay time of propellant was decreased along with the increase of ambient pressure and heat fluxes. There existed pressure thresholds to ignite propellant, its value was affected by heat fluxes. The high energy propellant can be ignited when the ambient pressure is higher than 0.2 atm, while this propellant can＇ t be ignited when the ambient pressure is below 0.2 atm. The effect of initial temperature on ignition delay time also depends on heat fluxes, and this effect is more significant at the lower heat fluxes. The experiential expression of the ignition delay time was given in the end.

关 键 词：流体力学 推进剂点火 激光点火 点火延迟 压强阈值 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]