4.7 Article

Thermoreversible Bonds and Graphene Oxide Additives Enhance the Flexural and Interlaminar Shear Strength of Self-Healing Epoxy/Carbon Fiber Laminates

期刊

ACS APPLIED NANO MATERIALS
卷 4, 期 7, 页码 6821-6831

出版社

AMER CHEMICAL SOC
DOI: 10.1021/acsanm.1c00888

关键词

carbon fiber; epoxy; graphene oxide; interface; thermoreversible bonds; self-healing

资金

  1. SERB [(IISc) 0161, PMRF 29-0620-6012-01433]
  2. [CRG/2020/004050]

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The study significantly improved the mechanical properties and introduced self-healing ability in CFRP laminates by incorporating thermoreversible bonds and graphene oxide. By establishing thermoreversible bonds between fibers and matrix, the flexural strength and interlaminar shear strength were effectively enhanced.
In the current era of high-strength, lightweight, and durable aircraft components, the need for carbon fiber-reinforced epoxy (CFRP) laminates is highly desired owing to their high specific strength and modulus, low coefficient of thermal expansion, and tunable properties that are unmatched by other materials. However, such components' catastrophic failure occurs due to the interfacial defects and debonding, thereby reducing service life and economic viability. Therefore, there is a pressing need to enhance the mechanical properties of CFRPs through matrix and fiber modifications and introduce the components' self-healing ability under a natural trigger. This study assessed the crucial role of thermoreversible bonds and graphene oxide (GO) interconnects, which worked in tandem toward significantly improving the mechanical properties and imparting self-healing properties in CFRP laminates. The laminates were fabricated with varying percentages of GO-modified epoxy matrix via vacuum-assisted resin transfer molding (VARTM) method. The carbon fibers were covalently modified with bis-maleimide (BMI) to establish a thermoreversible bond with GO at the fiber matrix interface to make interconnects. Flexural strength and interlaminar shear strength (ILSS) values for the optimized GO-modified epoxy laminates with BMI-deposited carbon fibers exhibited a significant increase of 30 and 47%, respectively. After a self-healing cycle triggered at 60 degrees C, they exhibited a recovery in their ILSS values up to 70%. These improvements are particularly useful for aircraft wings made up of CFRP laminates.

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