固体火箭发动机点火装置安装位置对点火性能的影响研究  

Effect of Installation Position on Ignition Performance of Ignition Device in Solid Rocket Motor

作　　者：林飒[1] 彭瑾[1] 

机构地区：[1]海军驻航天三院军事代表室,北京100074

出　　处：《火工品》2012年第5期9-13,共5页Initiators & Pyrotechnics

摘　　要：为实现某小型固体火箭发动机的可靠点火启动,设计了尾部和头部两种点火方案,进行了发动机的地面点火试验,分析了点火装置安装位置对点火性能的影响。试验结果表明,点火装置安装在喷管堵盖上的尾部点火方案不利于发动机的点火启动;相比于尾部点火方案,点火装置安装在发动机前封头上的头部点火方案所需点火药量减少50%,且各项技术指标满足设计要求,点火性能明显提高。To realize reliably ignition for a small-scale solid rocket motor（SRM）, a aft-ignition manner and a fore-ignition manner were designed and worked in SRM ground tests respectively, and the effect of installation position on ignition performance of ignition device was analyzed. The test result indicated that the aft-ignition manner in which the ignition device was mounted on nozzle closure, was not in favour of igniting for the motor. Compared with the aft-ignition manner, ignition charge mass needed in the fore-ignition manner, in which the ignition device was mounted on forward dome of SRM, was reduced 50%. The ignition performance of fore-ignition manner was increased efficiently and every performance can meet the requirements of the SRM ignition.

关 键 词：固体火箭发动机 点火装置 点火性能 安装位置 

分 类 号：TJ450.2[兵器科学与技术—火炮、自动武器与弹药工程]