An experimental impact study has been conducted on sandwich structures to identify and improve armour solutions for aeronautical applications. The objectives are to find the best configurations, i.e. the non-perforated targets with the minimal weight and back deformations. Medium-velocity impacts (120 m/s) have been conducted using a 127 g spherical projectile. The targets are simply supported at the rear of the structure. Two potential choices of front skin have been identified for the sandwich structure: 3 mm thick AA5086-H111 aluminium plates and dry aramid stitched fabrics (between 8 and 18 plies). The dry stitched fabrics appear to be an original solution, which associates a lightweight structure and a good perforation resistance. Moreover, a strong coupling has been found between the front skin and the core. The impact tests indicate that aluminium honeycomb core associated with aluminium skins show mitigated results. However, the combination of dry fabric front skin and aluminium honeycomb show better performances than aluminium sandwiches, with a global weight decrease.
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机译：已经对夹层结构进行了实验性冲击研究，以识别和改进航空应用的装甲解决方案。目的是找到最佳构型，即具有最小重量和向后变形的无孔目标。使用127 g球形弹丸进行了中速撞击（120 m / s）。目标仅支撑在结构的后部。对于夹层结构，已经确定了两种可能的前皮选择：3毫米厚的AA5086-H111铝板和干的芳纶缝合织物（介于8到18层之间）。干缝织物似乎是一种原始解决方案，具有轻巧的结构和良好的抗穿孔性。此外，在前蒙皮与芯之间发现了牢固的耦合。冲击试验表明，与铝皮有关的铝蜂窝芯显示出缓和的结果。然而，干织物前表皮和铝蜂窝的结合表现出比铝三明治更好的性能，并且整体重量有所减轻。
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