Abstract Carbon/glass hybrid composite (CGHC) laminates are some of the most promising composites for lightweight applications. Sometimes these laminates are used in warm environment, such as aircraft frame structures, and this may affect their performance. In order to investigate this issue, the present research aims to study the effect of temperatures on the impact behavior and pseudo-ductile behaviour of CGHC in presence of different types of thermosets “epoxy” and thermoplastic “acrylic poly-methyl methacrylate-PMMA”. The experiments were started with making of CGHC laminates from different stacking sequences of unidirectional carbon and woven glass fibre layers, using a vacuum-assisted resin transfer method followed by curing treatment. In addition to CGHC laminates, four other neat batches (Carbon/epoxy, Carbon/PMMA, Glass/epoxy, Glass/PMMA) were prepared for comparison. The low velocity impact behaviour of the fabricated panels was evaluated at high temperatures (60 °C and 80 °C) according to ISO 6603-2 standard, using drop tower, while pseudo-ductile behaviour and ductility index (DI) of the specimens were estimated based on the measured total energy and elastic energy. Also, the low-velocity impact response was modeled mathematically based on a modified energy-balance model to predict the absorbed energies. Finally, the failure mechanisms were examined using optical microscope to determine the influence of these damage growth on DI of the composites under different temperatures. The results showed that the impact energy response of both hybrid composites i.e. epoxy and PMMA was stable even as the temperature rose, however, carbon/glass/PMMA exhibited better performance compared with carbon/glass/epoxy with an increase in impact energy response estimated at 50% (25 °C) and 53% (80 °C). Also, the pseudo-ductile phenomenon was strongly evident, which facilitates the predictablility of failure.

中文翻译：

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用于飞机应用的碳/玻璃/环氧树脂和碳/玻璃/PMMA混合复合材料层压板在服役温度下的低速冲击和假延展行为

摘要 碳/玻璃混合复合材料 (CGHC) 层压板是一些最有前途的轻质应用复合材料。有时这些层压板用于温暖的环境，例如飞机框架结构，这可能会影响它们的性能。为了研究这个问题，本研究旨在研究在不同类型的热固性“环氧树脂”和热塑性“丙烯酸聚甲基丙烯酸甲酯-PMMA”存在下，温度对 CGHC 冲击行为和伪延性行为的影响。实验开始于使用真空辅助树脂转移方法和固化处理从单向碳和编织玻璃纤维层的不同堆叠顺序制造 CGHC 层压板。除了 CGHC 层压板外，还有其他四个整齐的批次（碳/环氧树脂、碳/PMMA、玻璃/环氧树脂、玻璃/PMMA）进行比较。根据 ISO 6603-2 标准，使用落塔在高温（60°C 和 80°C）下评估制造面板的低速冲击行为，而试样的伪延性行为和延展性指数 (DI) 为根据测得的总能量和弹性能量估算。此外，低速冲击响应是基于改进的能量平衡模型以数学方式建模的，以预测吸收的能量。最后，使用光学显微镜检查失效机制，以确定这些损伤增长对不同温度下复合材料 DI 的影响。结果表明，即使温度升高，环氧树脂和 PMMA 等混合复合材料的冲击能量响应也很稳定，然而，与碳/玻璃/环氧树脂相比，碳/玻璃/PMMA 表现出更好的性能，冲击能量响应增加估计为 50% (25 °C) 和 53% (80 °C)。此外，伪延性现象非常明显，这有助于故障的可预测性。