固体火箭发动机药柱热粘弹性瞬态响应分析  

Transient Temperature and Stress Analysis for Thermo-viscoelastic SRM Grains

作　　者：徐新琦[1] 胡明勇[1] 

机构地区：[1]海军航空工程学院,烟台264001

出　　处：《机械设计与研究》2004年第2期69-71,共3页Machine Design And Research

基　　金：总装备部预研项目 ( 4 13 2 80 10 5 0 2 )

摘　　要：应用有限元法对固体火箭发动机药柱在环境温度作用下的瞬态温度场进行了数值模拟 ,并基于药柱的热粘弹性本构关系 ,计算了由瞬态温度场引起的应力应变响应。The transient temperature distribution in a solid rocket motor grain due to the effect of environment temperature is calculated with finite element method.Based on the viscoelastic integral constitutive relation,the thermal stress and strain distribution is also calculated.The variation curve of stresses and strains with time for dangerous node on the interface of insulating layer and the SRM grams is presented.It provides scientific basis for structural integrity analysis.

关 键 词：固体火箭发动机 药柱 温度场 应力 应变 有限元 热粘弹性 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]