A novel fabrication miniature composite fuselage structure consisted of a woven composite laminated with an adhesively bonded butt joint under axial compression loading is numerically simulated in this research. A Finite Element Analysis (FEA) via ABAQUS/Explicit was utilized to capture the complete compressive response that predicts the crushing behaviour and its mechanical strength from initial compression loading until its final failure mode. A woven C-glass fibre/epoxy 200 g/m2 composite laminated (908) with the orthotropic elastic material properties is modelled as a continuum composite layup in the proposed numerical model. The adhesively bonded joint progression is considered using cohesive element technology that allows the correct accounting for the energy involved in the crushing process. The capability of the bonded joint to withstand axial crushing impact from debonding failure was examined. This proposed model was used to observe the crushing load and collapse modes under axial compression impact. The results that were extracted and computed from the FE modelling have shown a good agreement with the experimental test.
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机译：在本研究中，对一种新型的微型复合机身结构进行了数值模拟，该结构由机织复合材料层压而成，该复合材料在轴向压缩载荷下层压有粘合对接接头。通过ABAQUS / Explicit进行的有限元分析（FEA）用于捕获完整的压缩响应，该响应可预测从初始压缩载荷到最终破坏模式的破碎行为及其机械强度。在提出的数值模型中，将具有正交各向异性弹性材料特性的机织C玻璃纤维/环氧树脂200 g / m2复合层压板（908）建模为连续复合铺层。考虑使用粘合元件技术来考虑粘合连接的进展，该技术可以正确考虑压碎过程中涉及的能量。检验了粘合接头承受脱胶失败引起的轴向挤压冲击的能力。该模型被用来观察轴向压缩冲击下的破碎载荷和破坏模式。从有限元建模中提取和计算的结果与实验测试显示出良好的一致性。
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