固体火箭发动机外防热涂层应力应变随温度变化的数值研究  

Numerical Study on Stress and Strain of Heat-preventing Coating of SRM

作　　者：王春光[1] 田维平[2] 陈聪 

机构地区：[1]中国航天科技集团公司第四研究院第41所,西安710025 [2]中国航天科技集团公司第四研究院,西安710025 [3]西安航天化学动力厂,西安710025

出　　处：《弹箭与制导学报》2013年第3期98-101,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：弹(箭)常用的外防热涂料在贮存过程中经常出现裂纹、开裂、脱落等现象。为了研究在不同温度下,外防热涂层的应力应变变化情况,为强度分析提供参考依据,建立了某发动机壳体及涂层的三维有限元模型,研究了随温度变化涂层应力应变的变化特点。计算发现,常温向高温转化时,涂层的各向应力均为负值即压应力,此时应该用最大主应变准则来判断材料是否破坏;常温向低温转化时,各向应变都为负值即压应变,此时应该用Mises应力或者最大拉应力准则来判断结构的安全性。The outside heat-preventing coating of missile（rocket） often cracks,peels off and so on.In order to research the change of stress and strain of outside heat-preventing coating with different temperature,providing a reference for strength analysis,a 3D finite element model was established to study the change characteristics of stress and strain with different temperature.The result shows that the strain of coating will be negative value when the temperature increases,the maximum principal strain criterion should be used to judge whether the material is damaged.The strain of coating will be negative value when the temperature decreases,the Mises stress or maximum principal stress criterion should be used to judge whether the material is damaged.

关 键 词：防热涂层 应力应变 数值研究 强度分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]