固体火箭发动机特征间隙分析

推进技术 ›› 2005, Vol. 26 ›› Issue (3): 206-208.

固体火箭发动机特征间隙分析

钟涛,张为华,王中伟,青龙

防科技大学航天与材料工程学院湖南长沙410073;防科技大学航天与材料工程学院湖南长沙410073;防科技大学航天与材料工程学院湖南长沙410073;防科技大学航天与材料工程学院湖南长沙410073

发布日期:2021-08-15
基金资助:
国家“八六三”项目资助(2002AA765030)。

Analysis of characteristic gap of solid rocket motors

Inst.of Aerospace and Material Engineering,National Univ. of Defence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ. of Defence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ. of Defence Technology,Changsha 410073,China;Inst.of Aerospace and Material Engineering,National Univ. of Defence Technology,Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 为了分析大长径比固体火箭发动机点火瞬态过程性能散布的主要原因,引入特征间隙概念,分析了其性质,并验证其适用性,将其作为设计准则,分析了两台发动机点火瞬态过程,认为大长径比发动机点火瞬态过程性能散布主要原因不是加工精度,而是点火装置性能散布,并用数值计算验证了这一结论。

关键词: 固体火箭发动机;特征间隙;点火瞬态过程;性能散布

Abstract: To investigate the ignition transient performance distribution of large L/D solid rocket motors,the characteristic gap as a new design criterion for SRM is introduced.It is used on large aspect ratio motors and verified.The main cause of ignition transient performance distribution of large L/D motors is found to be the distribution of igniter mass rate,not the geometric precision. The numerical simulation result is consistent with this conclusion.

Key words: Solid propellant rocket engine;Characteristic gap;Ignition transient;Performance distribution

钟涛,张为华,王中伟,青龙. 固体火箭发动机特征间隙分析[J]. 推进技术, 2005, 26(3): 206-208.