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首页> 外文会议>AIAA/ASCE/AHS/ASC structures, structural dynamics and materials conference;AIAA SciTech Forum >Prediction of Low-Velocity Face-on Impact Response and Compression after Impact (CAI) of Composite Laminates using EST and Cohesive Modeling (DCZM)
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Prediction of Low-Velocity Face-on Impact Response and Compression after Impact (CAI) of Composite Laminates using EST and Cohesive Modeling (DCZM)

机译：利用EST和内聚模型（DCZM）预测复合材料层压板低速面对冲击的响应和压缩后的压缩（CAI）

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摘要

In this paper a shell based finite element (FE) modeling technique is introduced for predicting the low-velocity impact response and compressive strength after impact (CSAI) of fiber reinforced polymer matrix composite (FRPC) laminates. The model combines the Enhanced Schapery Theory (EST) in-plane material model with discrete cohesive zone elements to model the important damage and failure mechanics of a laminate subject to impact and compression after impact (CAI). The model is shown to successfully capture the important failure modes observed in a variety of laminates with different lay-ups subjected to face-on impact. The shell modeling method is able to capture the global effects of through-the-thickness (or 3D) damage through the use of individual shell layers coupled with discrete cohesive elements. The model is compared against experimental results for both impact and CAI for a variety of laminates including traditional and non-traditional ply angles. The computational results were found to be in excellent agreement with experimental data. The virtual testing approach presented in this paper is most useful for sizing and selecting material in the preliminary design stage of aircraft structures because of its computational efficiency, yet being of sufficient fidelity.
机译：本文介绍了一种基于壳的有限元（FE）建模技术，用于预测纤维增强聚合物基复合材料（FRPC）层压板的低速冲击响应和冲击后抗压强度（CSAI）。该模型将增强的Schapery理论（EST）面内材料模型与离散的粘合区域元素相结合，以对层压板在遭受冲击和撞击后压缩（CAI）的重要损伤和破坏机理进行建模。该模型显示成功捕获了在面对正面冲击的不同叠层的各种层压板中观察到的重要破坏模式。壳建模方法能够通过使用单独的壳层以及离散的内聚元素来捕获整个厚度（或3D）损坏的整体效果。将该模型与各种层压板（包括传统和非传统帘布层角度）的冲击和CAI的实验结果进行了比较。计算结果与实验数据非常吻合。本文提出的虚拟测试方法对飞机结构的初步设计阶段的尺寸和材料选择最有用，因为它的计算效率很高，但具有足够的保真度。

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