固体火箭发动机药柱伞盘结构应力应变分析

推进技术 ›› 2008, Vol. 29 ›› Issue (4): 477-480.

固体火箭发动机药柱伞盘结构应力应变分析

李磊,唐国金,雷勇军,申志彬

国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院;国防科技大学航天与材料工程学院

发布日期:2021-08-15
基金资助:
国防科技大学科研计划项目(JC06-01-01);高等学校博士学科点专项科研基金(20069998002);“十一五”武器装备预研项目

Stress and strain analysis for the umbrella slot configuration of solid rocket motor grain

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： 应用三维粘弹性有限元分析方法,分析了某固体火箭发动机药柱在低温载荷作用下的应力应变场,讨论了前伞盘曲面形式、宽度和深度对该部位最大Von Mises应变值的影响。在此基础上,通过调整前伞盘顶端双圆弧曲面结构的半径比,在基本不减少装药量的前提下,有效降低了该处最大Von Mises应变值,并初步确定了最佳半径比的范围,所得结论可为固体火箭发动机装药设计提供定量参考。

关键词: 固体推进剂火箭发动机;粘弹性;有限元法;应力应变分析

Abstract: Based on three-dimensional viscoelastic finite element method,and taking into account of the low temperature condition,the stress and strain of a solid rocket motor grain were studied.The effect of the surface shape,width and depth of front umbrella slot on the maximum Von Mises strain was discussed.In order to reduce the maximum Von Mises strain,the radius ratio of the dual arc surface of front umbrella slot was adjusted with few propellant mass losses.The range of the optimal radius ratio was elementary confirmed.The conclusions are available for designing solid rocked motor grain configuration.

Key words: Solid propellant rocket engine;Viscoelasticity;Finite element method;Stress and strain analysis

李磊,唐国金,雷勇军,申志彬. 固体火箭发动机药柱伞盘结构应力应变分析[J]. 推进技术, 2008, 29(4): 477-480.