固体火箭发动机人工脱粘层最佳深度的获取方法  

A Method of Obtaining the Suitable Debonded Length of the Stress Release Boot of Solid Rocket Motor

作　　者：蒙上阳[1,2] 唐国金[1] 雷勇军[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院 [2]桂林陆军学院广西桂林541002

出　　处：《广西科学》2004年第2期106-108,112,共4页Guangxi Sciences

基　　金：国防科技大学预研基金 ( JC0 2 -0 1-0 0 4);湖南省自然科学基金( 0 2 JJY2 0 0 9)资助项目

摘　　要：基于三维线性粘弹性有限元方法 ,利用 MSC/ NASTRAN有限元分析软件 ,以某含伞盘的星形与圆柱形组合药型的发动机为例 ,对温度载荷作用下发动机前人工脱粘层的深度进行调整 .通过建立各种脱粘层深度发动机的三维有限元模型 ,计算在温度载荷作用下脱粘层不同深度时伞盘最大 Von Mises应变值 .根据最大 VonMises应变变化的规律 。The stress release boot is always used in the solid rocket motor grain to relieve stress strain concentration under thermal loading Determining the debonded length of the release boot is one of the important problems in the grain design In this paper,a method of obtaining the suitable debonded length is present The three dimension viscoelastic finite element models of the motor grain with different debonded length are established Under thermal loading,the strain field of the umbrella slot is studied The results show that serious stress strain concentrates in the umbrella slot tip The maximum Von Mises strain of umbrella slot tip variation with the debonded release boot is obtained Then the suitable debonded length of the release boot could be determined This analytical method and these conclusions are useful in designing solid rocket motor

关 键 词：固体火箭发动机 人工脱粘层 最佳深度 粘弹性 有限元法 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]