【摘要】 随着复合材料在航空工程中的广泛应用,需要对复合材料结构的强度问题进行探究,而国内对复合材料层压厚板接头的失效模拟与分析方法研究较少。为此,以复合材料厚板接头为研究对象,基于三维渐进失效分析方法,选取合理的本构关系、失效准则、材料退化模式,并利用Fortran语言编写Umat子程序完成渐进失效方法的应用实现。通过对比复合材料层压厚板接头静强度试验和计算结果,表明本文所采用的三维渐进失效分析方法计算得到的应变-载荷数据与试验结果基本相符,即本文方法能够较好地模拟层压厚板接头的拉伸破坏过程,且可实现变参迭代计算,可为复合材料厚板接头结构的优化设计提供参考。更多还原

【Abstract】 The wide application of composite materials in aerospace engineering makes it critical to evaluate the strength of the composite structures,especially for the simulation of thick laminate joint failure.Based on 3D continuum damage mechanics approach,a study on modeling the damage mechanisms in a thick composite joint structure is presented.Meanwhile,a user-defined Fortran subroutine(Umat)is written to import the constitutive relation,failure criteria and stiffness degradation model.The substantiation test of the thick laminate joint is also conducted.Results show that both the calculation and test are basically consistent,and the model could exactly simulate the progressive failure process subjected to tension load,which demonstrates the validity of this inner-laminar damage model for variable parameter iterative calculation and optimization design for thick composite joint structure.更多还原