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针对高超声速飞行器结构应力损伤问题,采用有限元子模型法对高超声速飞行器结构强度进行分析研究。有限元分析依据模型复杂情况分为3个层次进行:第1层次采用较为稀疏的网格,获得二级子模型边界上各点的位移和力分布;第2层次将二级子模型网格划分细密,并用Fastener单元模拟群钉连接结构,获得较为准确的应力计算结果及钉载分配;第3层次选取钉载最大的部位建立三级子模型,引入渐进损伤子程序对危险部位进行损伤分析。文中采用ABAQUS子模型法,结合Fastener单元及UMAT(User-defined Material Mechanical Behavior)对高超声速飞行器结构强度由整体到局部进行了有限元分析,解决了常规有限元分析法网格多、计算困难等难题。
Aiming at the stress damage of hypersonic vehicle structure, finite element model is used to analyze the structural strength of hypersonic vehicle. The finite element analysis is divided into three levels according to the complexity of the model: the first level uses a sparse grid to obtain the displacement and force distribution of each point on the boundary of the second-level sub-model; the second level sub-model grid In the third level, the third-level sub-model was built by selecting the largest part of the load, and the progressive damage subroutine was introduced to analyze the damage of the dangerous part. In this paper, ABAQUS sub-model method is used in combination with Fastener element and UMAT (User-defined Material Mechanical Behavior) to analyze the structural strength of hypersonic vehicle from the whole to the part. The method solves the problems of multi-grid and difficult calculation in conventional finite element analysis .