Fracture mechanism of carbon fiber-reinforced thermoplastic composite laminates under compression after impact

IF 2.3 3区 材料科学 Q3 MATERIALS SCIENCE, COMPOSITES Journal of Composite Materials Pub Date : 2024-03-13 DOI:10.1177/00219983241240622
Yoshiko Nagumo, Miyu Hamanaka, Keiichi Shirasu, Kazuki Ryuzono, Akinori Yoshimura, Hironori Tohmyoh, Tomonaga Okabe
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Abstract

Thermoplastic carbon fiber-reinforced plastics (CFRPs) are increasingly utilized in the aerospace industry owing to their beneficial properties and enhanced formability relative to thermoset CFRPs. Despite the extensive use of these materials, studies focusing on compression after impact (CAI) tests with impact energies exceeding 20 J for thermoplastic CFRPs remain scarce. This study examines CAI tests on quasi-isotropic laminates of thermoplastic CFRP, subjected to a low-velocity impact energy of 27.04 J. For comparison, quasi-isotropic laminates of thermoset CFRP were subjected to a low-velocity impact energy of 36.5 J. These tests reveal that the CAI strength of both materials is comparable, notwithstanding the lower fiber volume fraction in the thermoplastic CFRP. Further, this research incorporates a finite element (FE) analysis to investigate the damage mechanisms in thermoplastic CFRP. The FE model, integrating interlaminar damage observed during the impact tests, accurately predicted the relationship between compressive stress and strain, correlating closely with the experimental outcomes. It was observed that both interlaminar and intralaminar damage propagation were constrained until the point of maximum compressive stress. Prior to reaching this maximum, a region of elevated compressive stress in the fiber direction was noted in the 0° layer near the non-impacted side. These findings indicate that the compressive stress in the fiber direction in the 0° layer adjacent to the non-impacted side is pivotal in dictating the final failure, which determines the CAI strength of thermoplastic CFRP laminates.
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碳纤维增强热塑性复合材料层压板在冲击后压缩条件下的断裂机理
与热固性碳纤维增强塑料相比,热塑性碳纤维增强塑料(CFRP)具有良好的性能和更强的可成形性,因此越来越多地应用于航空航天工业。尽管这些材料得到了广泛应用,但针对热塑性碳纤维增强塑料冲击能量超过 20 J 的压缩后冲击(CAI)试验的研究仍然很少。本研究对热塑性 CFRP 的准各向同性层压材料进行了 CAI 试验,并对其进行了 27.04 J 的低速冲击能量试验;作为对比,还对热固性 CFRP 的准各向同性层压材料进行了 36.5 J 的低速冲击能量试验。此外,这项研究还采用了有限元(FE)分析方法来研究热塑性 CFRP 的损坏机制。有限元模型综合了冲击试验中观察到的层间损伤,准确预测了压缩应力和应变之间的关系,与实验结果密切相关。据观察,层间和层内损伤的扩展都受到限制,直到压缩应力达到最大值。在达到最大压应力点之前,在靠近非撞击侧的 0° 层中发现了纤维方向的压应力升高区域。这些研究结果表明,在靠近非撞击侧的 0° 层中,纤维方向的压缩应力是决定最终破坏的关键,它决定了热塑性 CFRP 层压板的 CAI 强度。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
Journal of Composite Materials
Journal of Composite Materials 工程技术-材料科学:复合
CiteScore
5.40
自引率
6.90%
发文量
274
审稿时长
6.8 months
期刊介绍: Consistently ranked in the top 10 of the Thomson Scientific JCR, the Journal of Composite Materials publishes peer reviewed, original research papers from internationally renowned composite materials specialists from industry, universities and research organizations, featuring new advances in materials, processing, design, analysis, testing, performance and applications. This journal is a member of the Committee on Publication Ethics (COPE).
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