摘要
基于描述粘弹性材料特性的Burgers模型的本构关系以及基于该本构关系下的有限元方法 ,根据温度载荷和内压载荷的特点 ,分别建立了分析某固体发动机材料性能参数对结构完整性影响的有限元模型。应用MSC/NAS TRAN结构分析软件 ,详细分析了在温度和内压载荷作用下固体发动机材料性能参数对结构完整性的影响。在温度载荷的作用下 ,主要影响结构完整性的是推进剂的泊松比与热膨胀系数 ;在内压载荷作用下 ,主要影响结构完整性的是包覆层和推进剂的泊松比以及推进剂的初始模量。
Based on the constitutive relationship of viscoelastic material using the Burgers model and the corresponding viscoelastic finite element method, the finite computational models are established to value the effects of solid rocket motor material parameters on the structure integrity. They include the three dimension model and the plane strain model. In the case of thermal loading, the three dimension model is necessary, but the plane strain model is accurate enough in the case of internal pressure. Then, the effects of solid rocket motor material parameters on its structure integrity are respectively compared and analyzed under internal pressure and thermal loading by the use of MSC/NASTRAN software system. Under thermal loading, the main factors affecting the motor structure integrity are the propellant Poission's ratio and thermal expansion coefficient. Under the internal pressure, the main factors are the motor liner Poission's ratio, propellant initial elastic modulus and Poission's ratio. These conclusions would be useful for to the design of solid rocket motors.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2002年第5期10-15,共6页
Journal of National University of Defense Technology
基金
国防科技大学基础研究资助项目 (JC0 2 -0 1-0 0 4)
