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.
出处
《火工品》
CAS
CSCD
北大核心
2012年第5期9-13,共5页
Initiators & Pyrotechnics
关键词
固体火箭发动机
点火装置
点火性能
安装位置
Solid rocket motor
Ignition device
Ignition performance
Installation position
