使用缓燃推进剂的小型点火器点火技术研究  

Study on the Ignition Technique of Small Type Igniter Using Slow Burning Propellant

作　　者：谷丰[1] 马友林 乔桂玉[1] 陶瑞峰[1] 

机构地区：[1]北京航天动力研究所,北京100076 [2]中国兵器工业第213所,陕西西安710061

出　　处：《火工品》2005年第1期1-4,共4页Initiators & Pyrotechnics

摘　　要：为可靠点燃某运载火箭芯级发动机的主装药(缓燃双基推进剂),并满足低温(-40℃)可靠点火和高温(50℃)点火压力峰值不高的设计要求,通过设计点火方式、选择点火药、设计点火药盒结构及试验,确定了点火药为高能药与双基药片,点火方式为逐级点火,点火药盒结构采用多个排气孔的设计方案。经验证表明,该方案满足技术要求。In order to reliably igniting the main charge (slow burning double base propellant) of core engine in one launch vehicle, and meet with the requirements such as igniting at -40℃ and pressure peek value being not so high , the ignition pattern and the structure of igniter cartridge were designed, and the ignition powder was selected by tests. The proposal of using high energy powder and double base powder as ignition powder, step by step igniting pattern , and igniter cartridge with multi-exhaust gas holes were determined. Test results showed that the proposal was satisfied with the technique needs.

关 键 词：点火技术 点火器 点火方式 点火药盒 双基推进剂 运载火箭 设计要求 压力峰值 设计方案 技术要求 主装药 发动机 排气孔 可靠 结构 

分 类 号：U483[交通运输工程—载运工具运用工程] TK229.66[交通运输工程—道路与铁道工程]