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压缩载荷下夹层复合材料的面损伤扩展：实验、分析与有限元建模

Face Damage Growth of Sandwich Composites under Compressive Loading: Experiments, Analytical and Finite Element Modeling.

作者信息

Kinawy Moustafa, Rubino Felice, Canale Giacomo, Citarella Roberto, Butler Richard

机构信息

Independent Researcher, Derby DE23 6PT, UK.

Department of Chemical, Energetic and Mechanical Technology, University Rey Juan Carlos, Calle Tulipan, 28933 Mostoles, Spain.

出版信息

Materials (Basel). 2021 Sep 24;14(19):5553. doi: 10.3390/ma14195553.

DOI:10.3390/ma14195553
PMID:34639950
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC8509323/
Abstract

Sandwich panels with composite laminate skins having [(±45),(0,0),(±45)] stacking sequence (subscript C for carbon fibers, G for glass) and containing barely visible impact damage (BVID) induced on the whole sandwich structure impacted at low energy, were tested in edge after-impact-compression with load direction parallel and transversal to the fibers direction (0-dir.). The morphology of impact damage on the sandwich structure was determined by using ultrasonic C-Scan and visual observation of laminate cross section. A Digital Image Correlation (DIC) system was used to measure the delamination evolution during the test. Two different failure behaviors were observed in two different impacted panels. Panel with fibers oriented transversally to the compressive load showed an opening (Mode-I) propagation of a delamination, while the panel with fibers parallel to the load showed shear (Mode-II) propagation. The static load such to determine local buckling of the composite face and failure was experimentally measured. An analytical model was implemented to predict the static strength of laminate with Mode-I opening. An FE model was instead built to predict the local buckling failure mode of the laminate with BVID, which is the first phenomenon to appear. The results of the analytical model and the numerical simulation correlate well with the test.

摘要

具有[(±45),(0,0),(±45)]堆叠顺序（下标C代表碳纤维，G代表玻璃纤维）且包含在低能量冲击下整个夹层结构产生的几乎不可见冲击损伤（BVID）的复合层压板蒙皮夹层板，在冲击后边缘压缩试验中进行了测试，加载方向与纤维方向（0方向）平行和横向。通过超声C扫描和层压板横截面的目视观察来确定夹层结构上冲击损伤的形态。使用数字图像相关（DIC）系统来测量试验过程中的分层扩展。在两个不同的冲击面板中观察到了两种不同的失效行为。纤维方向与压缩载荷横向的面板显示出分层的张开（I型）扩展，而纤维与载荷平行的面板显示出剪切（II型）扩展。通过实验测量了确定复合材料面板局部屈曲和失效的静载荷。建立了一个分析模型来预测具有I型张开的层压板的静态强度。相反，建立了一个有限元模型来预测具有BVID的层压板的局部屈曲失效模式，这是首先出现的现象。分析模型和数值模拟的结果与试验结果相关性良好。

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