Laminated composite structures have attracted the interest of the modern industry due to their high performances and reduced weight when compared to traditional structural materials. However, they are very sensitive towards out-of-plane dynamic loading that can generate Barely Visible Impact Damage (BVID) within the structure and cause a drastic detriment of mechanical properties. One solution is proposed to overcome this problem by the hybridisation of the laminate stacking sequence using Shear Thickening Fluids (STFs) for absorption of large fractions of impact energy with a minimal damage generation. This work numerically investigated the impact response of Carbon Fibre Reinforced Polymers (CFRP) when a silica-based STF is embedded within the lamination sequence utilising an innovative Ls-Dyna-based Finite-Element Model (FEM). This was developed using an Arbitrary Lagrangian Element (ALE) approach in a fluid-structure interaction (FSI) analysis and calibrated with an experimental impact campaign to determine the best impact resistance as a function of the STF position along the thickness of the laminate. The results showed an improvement in impact resistance for all the hybrid configurations identifying the optimal STF location in the upper portion of the laminate with a reduction in absorbed energy of ~ 42%, damaged area of ~ 35% alongside an increase in contact force (~ 36%) with respect to conventional laminate with same stacking sequence and number of plies. The results showed that STF/CFRP structures can be successfully employed for applications in several advanced sectors including aerospace, automotive and energy (wind blades) representing an important step-up in the development of high-impact resistant hybrid composite structures.

与传统结构材料相比，层压复合结构的高性能和轻量化吸引了现代工业的兴趣。但是，它们对平面外动态载荷非常敏感，这种动态载荷会在结构内产生几乎可见的冲击损伤（BVID），并严重损害机械性能。为了解决该问题，提出了一种解决方案，该解决方案是通过使用剪切增稠流体（STF）进行层压堆叠顺序的混合，以吸收大部分冲击能量，而产生的损伤最小。这项工作使用创新的基于Ls-Dyna的有限元模型（FEM）对基于二氧化硅的STF嵌入层压序列中进行了数值研究，研究了碳纤维增强聚合物（CFRP）的冲击响应。这是在流体-结构相互作用（FSI）分析中使用任意拉格朗日元素（ALE）方法开发的，并通过实验性冲击运动进行了校准，以确定最佳的抗冲击性，它是沿着层压板厚度的STF位置的函数。结果表明，所有混合结构的耐冲击性均得到改善，从而确定了层压板上部的最佳STF位置，吸收能降低了约42％，受损区域降低了约35％，同时接触力也增加了（〜相对于具有相同堆叠顺序和层数的常规层压材料而言，该比例为36％）。结果表明，STF / CFRP结构可以成功地用于航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天，航空航天等领域的先进应用中。