铝镁贫氧推进剂激光点火特性  

Laser Ignition Characteristics of Aluminium-Magnesium Fuel-rich Propellant

作　　者：朱国强[1] 薛谈顺 周长省[1] 陈雄[1] 成红刚[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]淮海工业集团有限公司,山西长治046012

出　　处：《弹道学报》2013年第1期85-88,共4页Journal of Ballistics

基　　金：国防预研基金项目;南京理工大学自主科研专项计划资助项目(2011XQTR13)

摘　　要：为研究铝镁贫氧推进剂的点火特性,采用激光点火系统对推进剂在不同激光热流密度下进行了多组点火实验,结果表明:铝镁贫氧推进剂点火机理为凝聚相点火,激光热流密度在点火过程中起主导作用;在激光热流密度为176～646W/cm2的范围内,铝镁贫氧推进剂的点火延迟时间随着热流密度的增加而递减,且点火延迟时间变化趋缓。依据实验结果拟合出了不同热流密度下计算铝镁贫氧推进剂点火延迟时间的经验公式,该公式可计算激光热流密度在176～646W/cm2范围内铝镁贫氧推进剂的点火延迟时间。To study the ignition characteristics of aluminium-magnesium fuel-rich propellant, many groups of ignition experiments were carried out under various laser heat flux by using a laser ignition system. The results show that the ignition mechanism of aluminium-magnesium fuel-rich propellant is condensed-phase ignition, and laser heat flux density plays a leading role in the ignition process. When the laser heat flux density is in the range of 176;646 W/cm2 ,the ignition delay time of aluminium-magnesium fuel-rich propellant increases with the increase of heat flux density, and the ignition delay time changes slowly under high heat flux density. The calculation formula of aluminum-magnesium fuel-rich propellant ignition delay time under various laser heat flux density was given according to experimental results. Under laser heat flux density in the range of 176;646 W/cm2, the ignition delay time of aluminium-magnesium fuel-rich propellant can be calculated by the formula.

关 键 词：铝镁贫氧推进剂 点火延迟 激光点火 热流密度 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]