端燃药柱药面点火引燃过程试验  

Experiment on surface ignition process of the end-burning grains

作　　者：吴敏[1] 王小波[1] 何君 王文博[1] 占明明 WU Min;WANG Xiaobo;HE Jun;WANG Wenbo;ZHAN Mingming(Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China)

机构地区：[1]湖北航天化学技术研究所

出　　处：《固体火箭技术》2019年第5期580-584,共5页Journal of Solid Rocket Technology

摘　　要：复合固体推进剂的点火引燃过程一直受到广泛关注。为了提高发动机设计质量,减少点火试验次数,以及更好地揭示燃面的引燃着火机理,本文在大气条件下对端燃药柱的点火试验进行研究,观测到了药柱点火引燃和燃面扩展的瞬时变化情况。通过进一步分析具体燃烧过程,获得了药面单点引燃的燃面扩展方式,并结合传热仿真分析、内弹道计算结果解释了药面点火源数量是影响点火延迟差异、建压时间较长的机理,以及喷管堵塞的主要作用是控制炽热颗粒落在药面上,进而增强燃面着火效率,提升发动机点火可靠性。The lighting mechanism of solid propellant grains has long been attached much importance.In order to clearly understand the ignition process on the burning surface of the typical solid propellant,the ignition experiments of the end-burning grains are made in the general air environment.Through the video monitoring system,we obtained the real-time pictures and burning surface expansion mode of the grains in the single-point ignition,combined with the analytical results from the thermal simulation and the interior ballistic calculation,it demonstrated that the number of ignition sources determines the ignition delay,and the pressure rise rate.The function of the nozzle closure is to make the hot particles locate at the grain surface more effectively,which can improve the ignition performance substantially.

关 键 词：固体火箭发动机 点火 燃面 火焰 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]