小型固体火箭发动机尾部点火器设计方法  

Design method for aft-end igniter of small-scale solid rocket motor

作　　者：张秋芳[1] 王宁飞[2] 田维平[3] 

机构地区：[1]西安近代化学研究所,西安710065 [2]北京理工大学,北京100081 [3]中国航天科技集团公司第四研究院第四十一所,西安710025

出　　处：《固体火箭技术》2006年第5期341-345,共5页Journal of Solid Rocket Technology

摘　　要：以尾部点火装置安装位置为分类方法,以点火装置燃烧产物与发动机装药的不同换热方式为基础,对典型的小型固体火箭发动机的尾部点火设计方法和设计中需要重点考虑的问题作了较为全面的介绍。以某型号发动机尾部点火设计为研究对象,对点火序列设计、点火药量的估算、喷管堵片的设计方法进行了阐述。通过调整点火药量、喷管堵片设计状态,使点火压强逐步提高,解决了发动机研制初期出现的点火延迟、不点火等技术问题。Taking installation location of aft-end igniter as classification method and different heat transfer mode between the igniter combustion gas and motor grain as investigation basis, design method for aft-end ignition of some typical rocket motors and the key problems were discussed comprehensively. Taking aft-end igniter design for a rocket motor for example, design methods for ignition sequence, amorce quantity estimation and nozzle closure were described respectively. Ignition pressure can be improved gradually and some technology problems such as ignition delay and ignition failure at the preliminary stage were solved by adjusting amorce quantity and nozzle closure design state.

关 键 词：固体火箭发动机 尾部点火 点火延迟 喷管堵片 

分 类 号：V435.3[航空宇航科学与技术—航空宇航推进理论与工程]