The evaluation of Compression-After-Impact (CAI) strength is of great significance in the design of composite aerostructures. This paper presents a model for the numerical simulation of Compression-After-Impact (CAI) of hybrid unidirectional (UD)/woven carbon-fibre reinforced composite laminates. This three-dimensional damage model is based on Continuum Damage Mechanics (CDM) and Linear Elastic Fracture Mechanics (LEFM), implemented as a user defined material subroutine (VUMAT) in Abaqus/Explicit. This model, which accounts for interlaminar and intralaminar damage, and load reversal, incorporates a non-linear shear profile to account for matrix plasticity. Two different composite laminate lay-ups with varying extent of initial impact damage were tested to validate the computational model and enable a quantitative study of the influence of using woven plies on the surfaces of a laminate. Woven surface plies are often used in composite aerostructures to mitigate damage during drilling and constrain the extent of damage during low velocity impact. Good correlation was obtained between physical testing and simulation results, which establishes the capability of this damage model in predicting the structural response of composite laminates. The fully validated model was used to compare the CAI strength of an equivalent UD-only carbon-fibre reinforced composite laminate. The results showed that the hybrid unidirectional (UD)/woven laminate had a marginally higher strength (+3.3%) than the equivalent unidirectional (UD)-only laminate.

冲击后压缩强度（CAI）的评估在复合材料航空结构的设计中具有重要意义。本文提出了一种模型，用于混合单向（UD）/编织碳纤维增强复合材料层压板的冲击后压缩（CAI）数值模拟。此三维损伤模型基于连续损伤力学（CDM）和线性弹性断裂力学（LEFM），以Abaqus / Explicit中用户定义的材料子例程（VUMAT）的形式实现。该模型考虑了层间和层内损坏以及载荷反向，并结合了非线性剪切剖面来说明基体的可塑性。测试了具有不同程度的初始冲击损伤的两种不同的复合层压板铺层，以验证计算模型，并能够定量研究使用编织层对层压板表面的影响。编织表面帘布层通常用于复合材料航空结构中，以减轻钻孔过程中的损坏并限制低速冲击时的损坏程度。在物理测试和仿真结果之间获得了良好的相关性，从而建立了这种损伤模型预测复合材料层板结构响应的能力。经过完全验证的模型用于比较等效的仅UD碳纤维增强复合材料层压板的CAI强度。结果表明，混合单向（UD）/机织层压板的强度略高（+3）。