摘要
本研究以多款小型固体火箭发动机研制为基础,通过点火药量经验计算公式,点火器单项试验,发动机点火试验等方式设计满足发动机应用要求的点火器,并分析自由容积,推进剂燃速,点火压强,点火药剂选择等主要参数对点火药量的影响;结果表明:发动机初始自由容积越大,推进剂燃速越低,燃面越大需要的点火能量越高;小型固体火箭发动机可根据参数对比,考虑选择成熟点火器,以降低研制成本,缩短研制周期。
The igniter design was made for the development of a variety of small solid rocket motors by empirical formulas for ignition charge mass calculation, single igniter test, motor firing test and successfully applied to active motor. The analysis was made with regard to influence of main design parameters such as free volume,propellant burning rate,ignition pressure,ignition charge selection on ignition charge mass. It is shown that ignition charge mass increases with greater initial free volume of motor,higher propellant burning rate and larger burning surface area; and well-developed igniter can be chosen for small solid rocket motors based on parameter comparison to reduce development cost and shorten development cycle.
作者
官鹏
王峰
李天祥
张斐
蒙鹤
郭峰
GUAN Peng;WANG Feng;LI Tianxiang;ZHANG Fei;MENG He;GUO Feng(Xi'an Aerospace Chemical Propulsion Co.,Ltd.,Xi'an 710025,China)
出处
《兵器装备工程学报》
CAS
北大核心
2018年第8期21-25,共5页
Journal of Ordnance Equipment Engineering