大推力速燃火箭发动机蜂巢状装药的设计与理论分析

推进技术 ›› 1998, Vol. 19 ›› Issue (3): 5-7.

大推力速燃火箭发动机蜂巢状装药的设计与理论分析

黄广奇

中国兵器工业总公司第二○三所

发布日期:2021-08-15

THEORETICAL DESIGN AND ANALYSES OF BEE NESTPROPELLANT GRAIN USED IN THE LARGE THRUSTAND RAPID BURNING ROCKET MOTOR

The 203rd Inst, Ordnance Industry of China,Chang′an,710111

Published:2021-08-15

摘要/Abstract

摘要： 针对速燃火箭发动机大推力短燃时的特点，提出一种满足此要求的新型装药——蜂巢状装药，并对该药型的内弹道特性、燃面规律和力学特点作出了定性和定量分析，对速燃发动机的装药设计有一定的借鉴意义。

关键词: 固体火箭推进;推进剂药柱;火箭弹;装药结构

Abstract: According to the property of the large thrust and rapid burning rocket motor,a new type of propellant grain,bee nest propellant grain was put forwardThe quantitative or qualitative analyses were done the internal ballistic properties,burning surface change laws and mechanical charactersThis scheme is referable to the rapid burning rocket motor

Key words: Solid rocket propulsion;Propellant grain;Rocket projectile;Charge structure

黄广奇. 大推力速燃火箭发动机蜂巢状装药的设计与理论分析[J]. 推进技术, 1998, 19(3): 5-7.