The existing literature extensively explores the influence of stacking sequences on symmetric flat laminates subjected to low-velocity impacts. However, this is not true in the case of curved laminates. Therefore, the main goal of this study is to analyse the effect of stacking sequences on the impact response of semicylindrical woven composite shells. For this purpose laminates with [0], [45], [＋15,−15], [＋22.5,−22.5], and [＋30,−30], were considered in order to evaluate the impact response of layer orientations. Additionally, laminates with [0, 45], [0,45], [0,45, 0], and [45, 0] were employed to analyse the effects of changing the positioning of the layers in relation to the laminate mid-plane. The FE model was validated with the experimental results obtained for [0] laminates, where good numerical–experimental correlation was obtained. The findings suggest that an increase in impact bending stiffness (IBS) leads to a rise in maximum force, accompanied by a decrease in maximum displacement, contact time, and dissipated energy. The primary mechanism responsible for dissipating the majority of impact energy is intralaminar damage, followed by delaminations and friction. Importantly, changing the layer positions has a significant impact on how each layer within the semicylindrical quasi-isotropic composite shell distributes and dissipates energy during the impact event.

中文翻译：

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半圆柱形编织复合材料壳体的冲击响应：堆叠顺序的影响

现有文献广泛探讨了堆叠顺序对受到低速冲击的对称平面层压板的影响。然而，对于弯曲层压板而言，情况并非如此。因此，本研究的主要目标是分析堆叠顺序对半圆柱形编织复合材料壳体冲击响应的影响。为此，考虑了[0]、[45]、[+15,−15]、[+22.5,−22.5]和[+30,−30]层压板，以评估层方向的冲击响应。此外，采用 [0, 45]、[0,45]、[0,45, 0] 和 [45, 0] 的层压板来分析改变层相对于层压板中间的位置的影响。飞机。有限元模型通过 [0] 层压板获得的实验结果进行了验证，获得了良好的数值实验相关性。研究结果表明，冲击弯曲刚度（IBS）的增加会导致最大力的增加，同时最大位移、接触时间和耗散能量的减少。耗散大部分冲击能量的主要机制是层内损伤，其次是分层和摩擦。重要的是，改变层位置对半圆柱形准各向同性复合材料壳内的每一层在撞击事件期间如何分布和耗散能量具有重大影响。