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An efficient numerical approach to the prediction of laminate tolerance to Barely Visible Impact Damage

机译：一种有效的数值方法来预测层压板对几乎可见的冲击损伤的耐受性

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摘要

An efficient numerical approach for the prediction of the Compression After Impact (CAI) strength of aerospace-grade CFRP laminates when exposed to Barely Visible Impact Damage (BVID) is proposed. The approach is based on mapping relevant BVID features, i.e. delaminations, onto an efficient CAI finite element model based on continuum shell discretization, and can be used on Low-Velocity Impact (LVI) results obtained experimentally or by means of high-fidelity virtual tests. It is proposed that delaminations may be represented by simplified shapes, and only the ones at critical through-thickness locations need to be mapped, allowing the clustering of several plies in a single shell layer. General guidelines, that are potentially valid for a wide range of unidirectional CFRP laminates, are proposed to identify relevant and critical BVID features to be mapped onto the efficient CAI modelling. The approach was validated for five laminates of AS4/8552 material, covering a range of different thicknesses, overall achieving CAI strength predictions within 5% of the experimental results. In comparison with the alternative high-fidelity CAI virtual testing approach, this method leads to computational efficiency gains of an order of magnitude. Moreover, the full simulation of the sequence LVI plus CAI steps can be accelerated by a factor of four.
机译：提出了一种有效的数值方法，用于预测航空级CFRP层压板在暴露于几乎可见的冲击损伤（BVID）时的冲击后压缩（CAI）强度。该方法基于将相关的BVID特征（即分层）映射到基于连续壳离散化的有效CAI有限元模型上，并且可以用于通过实验或通过高保真虚拟测试获得的低速撞击（LVI）结果。提出可以用简化的形状来表示分层，并且仅需要映射关键厚度范围内的分层，从而允许在单个壳层中将多个层聚集在一起。提出了对广泛的单向CFRP层压板潜在有效的通用准则，以识别相关和关键的BVID特征，以将其映射到有效的CAI建模中。该方法已针对5种AS4 / 8552材料的层压板进行了验证，覆盖了一系列不同的厚度，总体上在实验结果的5％范围内实现了CAI强度预测。与替代的高保真CAI虚拟测试方法相比，此方法可带来一个数量级的计算效率提升。此外，序列LVI和CAI步骤的完全仿真可以提高4倍。

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