PREPARATION OF NOVEL CARBON FIBER/EPOXY RESIN-BASED COMPOSITES AND RESEARCH ON THEIR MECHANICAL PROPERTIES AND APPLICATIONS IN AEROSPACE STRUCTURAL COMPONENTS.

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Τίτλος:	PREPARATION OF NOVEL CARBON FIBER/EPOXY RESIN-BASED COMPOSITES AND RESEARCH ON THEIR MECHANICAL PROPERTIES AND APPLICATIONS IN AEROSPACE STRUCTURAL COMPONENTS.
Συγγραφείς:	ZHANG, JINMING¹ (AUTHOR) zhangjm1224@mails.jlu.edu.cn
Πηγή:	Surface Review & Letters. Sep2026, Vol. 33 Issue 10, p1-13. 13p.
Θεματικοί όροι:	Carbon composites, Composite material manufacturing, Thermal stability, Epoxy resins, Aerospace technology, Materials testing, Fiber-matrix interfaces, Mechanical behavior of materials
Περίληψη:	Carbon fibers that are reinforced by epoxy resin have gained popularity among the aerospace industry due to their low-weight properties, stiffness, mechanical strength. However, the techniques employed in the manufacturing process have limitations in terms of producing reliable mechanical strength and heat resistance because of differences in the curing process, fiber dispersion, and fiber-matrix interaction. The primary objective of this work is to develop novel carbon fiber/epoxy resin-based composites and systematically evaluate their mechanical behavior for structural applications. Experimental datasets were generated through controlled layup configurations, varying fiber volume fraction, curing temperature, and hybrid interlaminar architectures. Mechanical characterization employed standardized tensile, compressive, flexural, and interlaminar shear testing, fracture toughness testing, impact testing, supported by dynamic mechanical analysis and thermogravimetric profiling. Statistical validation enabled the identification of dominant processing parameters influencing performance variability. The fabrication process combines staged heat curing with vacuum-assisted resin infusion to minimize void formation and enhance fiber-matrix adhesion. According to the findings, the composites have better impact energy (18–27 J), tensile strength (620–750 MPa), and thermal stability (degradation temperature rising from 310∘C to 355∘C). Flexural rigidity and thermal stability also demonstrate consistent gains, confirming suitability for load-bearing aerospace components such as panels and secondary structures. Microstructural analysis scanning electron microscopy (SEM) shows consistent fiber dispersion and decreased interfacial debonding, which are directly related to improved load transmission mechanisms. These outcomes provide a robust framework for scalable manufacturing and future high-performance aerospace material development strategies. [ABSTRACT FROM AUTHOR]
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