A new progressive damage model for the three-dimensional (3 D) woven carbon/carbon (C/C) composites is developed at fiber-matrix level using the micromechanics method. A woven architecture based Representative Volume Element (RVE) model composed of yarns, matrix and yarn/matrix interface is constructed, in which the manufacturing void defects are accounted for. The fiber-matrix concentric cylinder model is employed as a repeating unit cell to represent the yarn, and the matrix micro strain field is computed analytically by the micromechanics method. The maximum stain criteria is utilized for fiber longitudinal breakage, and the Von-Mises criterion is applied for the damage initiation of matrix in both intra-yarns and inter-yarns. The damaged fiber and matrix are modeled by the stiffness degradation method combined with exponential damage evolution equations. The zero thickness cohesive elements governed by bilinear traction-separation constitutive are adopted for yarn/matrix interfacial debonding behavior. The micro progressive damage and failure behavior of the 3 D woven C/C composites subjected to tension is implemented through a developed user-defined material subroutine in commercial software ABAQUS. The predicted stress-strain response is in a good agreement with experimental results. In addition, the effect of manufacturing void defects is also examined by the developed model.

三维 (3D) 编织碳/碳 (C/C) 复合材料的新渐进式损伤模型是使用微力学方法在纤维基质级别开发的。构建了由纱线、基体和纱线/基体界面组成的基于编织结构的代表性体积元素 (RVE) 模型，其中考虑了制造空隙缺陷。采用纤维-基体同心圆柱模型作为重复单元来表示纱线，并通过微观力学方法解析计算基体微应变场。最大染色标准用于纤维纵向断裂，Von-Mises 标准用于纱线内和纱线间基质的损伤起始。损伤纤维和基体采用刚度退化方法结合指数损伤演化方程建模。由双线性牵引分离本构控制的零厚度内聚元件用于纱线/基质界面脱粘行为。通过在商业软件 ABAQUS 中开发的用户定义材料子程序，可以实现 3D 编织 C/C 复合材料在张力下的微观渐进损坏和失效行为。预测的应力应变响应与实验结果非常吻合。此外，开发的模型还检查了制造空洞缺陷的影响。通过在商业软件 ABAQUS 中开发的用户定义材料子程序，可以实现 3D 编织 C/C 复合材料在张力下的微观渐进损坏和失效行为。预测的应力应变响应与实验结果非常吻合。此外，开发的模型还检查了制造空洞缺陷的影响。通过在商业软件 ABAQUS 中开发的用户定义材料子程序，可以实现 3D 编织 C/C 复合材料在张力下的微观渐进损坏和失效行为。预测的应力应变响应与实验结果非常吻合。此外，开发的模型还检查了制造空洞缺陷的影响。