固化降温过程中推进剂药柱的瞬态响应分析  

Transient temperature and stress analysis of propellant grains during cooling process after curing

作　　者：徐新琦[1] 于胜春[1] 

机构地区：[1]海军航空工程学院,烟台264001

出　　处：《固体火箭技术》2004年第3期180-183,共4页Journal of Solid Rocket Technology

基　　金：总装备部预研项目(41328010502)。

摘　　要：应用有限元法,对固体火箭发动机药柱在固化降温过程中的三维瞬态温度场进行了数值模拟,并基于药柱的粘弹性本构关系,计算了由瞬态温度场引起的应力应变响应。给出了危险点的应力应变随时间的变化规律,可供结构整体分析参考。The 3D transient temperature distribution during the cooling process after curing of solid rocket motor grain is numerically simulated with finite element method. Based on the viscoelastic integral constitutive relation, the thermal stress and strain response is calculated. The variation curve of stress and strain with time for danger nodes is presented. It is avaliable for reference in structural integrity analysis.

关 键 词：推进剂药柱 固体火箭发动机 瞬态响应 瞬态温度场 数值模拟 三维 粘弹性 固化 应力应变 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] V512