Abstract The progressive failure of a 0o/90o laminated carbon fiber reinforced epoxy composite was modelled in LS-DYNA using the MAT_162 material model, including the strain rate, damage progression and anisotropy effects. In addition to conventional standard and non-standard tests, double-shear and Brazilian tests were applied to determine the through-thickness shear modulus and the through-thickness tensile strength of the composite, respectively. The modulus reduction and strain softening for shear and delamination parameters were calibrated by low velocity drop-weight impact tests. The rate sensitivities of the modulus and strength of in-plane and through-thickness direction were determined by the compression tests at quasi-static and high strain rates. The fidelity of the determined model parameters was finally verified in the in-plane and through-thickness direction by the 3D numerical models of the Split Hopkinson Pressure Bar compression tests. The numerical bar stresses and damage progressions modes showed acceptable correlations with those of the experiments in both directions. The composite failed both numerically and experimentally by the fiber buckling induced fiber-matrix axial splitting in the in-plane and the matrix shear fracture in the through-thickness direction.

中文翻译：

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用于高应变率平面压缩的碳纤维增强层压环氧树脂复合材料的材料模型和损伤​​参数的确定

摘要 在 LS-DYNA 中使用 MAT_162 材料模型对 0o/90o 层压碳纤维增强环氧树脂复合材料的渐进破坏进行了建模，包括应变率、损伤进展和各向异性效应。除了常规的标准和非标准试验外，还应用双剪切和巴西试验分别测定了复合材料的全厚度剪切模量和全厚度拉伸强度。剪切和分层参数的模量减少和应变软化通过低速落锤冲击试验进行校准。通过准静态和高应变率下的压缩试验确定了面内和厚度方向的模量和强度的速率敏感性。通过拆分霍普金森压力棒压缩测试的 3D 数值模型，最终在平面内和厚度方向上验证了所确定模型参数的保真度。数值杆应力和损伤进展模式与两个方向的实验结果显示出可接受的相关性。由于纤维屈曲引起的平面内纤维-基体轴向分裂和全厚度方向的基体剪切断裂，复合材料在数值和实验上都失败了。