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Energy absorption in carbon fiber honeycomb structures manufactured using a liquid thermoplastic resin

材料科学 复合材料 热塑性塑料 蜂窝结构 蜂巢 抗弯强度 环氧树脂 复合数 抗压强度 芯(光纤) 纤维
作者
Tayyab Khan,Alia Ruzanna Aziz,Muhammad Irfan,W.J. Cantwell,Rehan Umer
出处
期刊:Journal of Composite Materials [SAGE Publishing]
卷期号:56 (9): 1335-1348 被引量:20
标识
DOI:10.1177/00219983221073985
摘要

In this study, carbon fiber/thermoplastic (Elium ® ) honeycombs were manufactured using the resin infusion process in a customized metallic mold. Honeycomb cores, based on different carbon fiber layers, were manufactured to achieve four different fiber weight fraction composites. Two different types of specimens, based on a single honeycomb cell and five honeycomb cells, were prepared and subjected to compression loading. The results of these tests were compared with data from similar honeycomb structures based on carbon fiber–reinforced epoxy composite. It has been shown that the compressive strength and the specific energy absorption capacity of the honeycombs increase rapidly with increasing fiber weight fraction. The specific energy absorption capability of the novel thermoplastic honeycomb structures has been shown to be as high as 50 kJ/kg which compares favorably with other energy-absorbing core materials. The thermoplastic honeycomb specimens exhibited a similar specific energy absorption capability and an improved compressive strength compared to their epoxy counterparts. Furthermore, the CF/thermoplastic honeycombs exhibited enhanced structural stability and displayed a more uniform and progressive core failure mode than the longitudinal splitting observed in the CF/epoxy honeycombs. The honeycomb core that exhibited the best performance was then used to manufacture thermoplastic sandwich specimens based on CF/thermoplastic face sheets. Three point bend tests were conducted to determine the flexural strength of the sandwich samples and to identify the failure modes. Optical micrographs revealed that the flexural damage was primarily due to the core crushing and adhesive failure between the core and the composite skins.
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