Experimental observation and FEM analysis of initial fractures in quasi-isotropic CFRP laminates subjected to compressive loading

Matsuda, Naoki; Wakayama, Kazuo; Nishikawa, Masaaki; Hojo, Masaki; Arai, Masahiro; Goto, Keita; Katoh, Hisaya

doi:10.1080/09243046.2020.1802543

Cited by 3 publications

(1 citation statement)

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“…The results showed that the out-of-plane shear stress was prone to cause the microbuckling and control the initial fracture of the laminate. 32,33 D. Wilhelmssona et al accurately predicted the effect of off-axial angle on the orientation of the kinking plane based on the numerical value of the LaRC05 kinking criterion. 34 Digital simulations by Anton Shipsha et al based on the LARC04 failure criterion indicated that the fiber waviness reduces the initial stress of fiber kinking and delamination.…”

Section: Introductionmentioning

confidence: 99%

Analysis of in-plane compression failure mechanism in carbon fiber braided composite with different off-axial angles

Xiao

Pan

et al. 2022

Journal of Composite Materials

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This paper focuses on the in-plane compression mechanism of two-dimensional biaxial braided composite laminates under quasi-static compression and dynamic compression. Three types of specimens with different off-axial angles in respect of OA00, OA60, and OA90 were employed for compression experiments. The surface damage process of the specimen was recorded using optical camera and infrared thermal imaging technology. The internal damage morphology of the tested specimens was analyzed by X-ray computed tomography. The progressive damage behavior of braiding yarns and matrix resin was simulated by a three-dimensional meso-level finite element model. Experimental and simulation results revealed that the off-axial angle significantly affects mechanical properties and damage mechanisms. The stress distribution and compression deformation of braiding yarns are affected by the boundary conditions of load-bearing yarn, which relies on the off-axial angle. The stress of OA00 specimen is concentrated at the interface of yarn and matrix resin. The failure mode of OA00 specimen is dominated by the shear band, which is induced by the interface microcracks between yarn and matrix resin. The stress of OA60 and OA90 specimens are concentrated at the undulation position of the braiding yarn. The critical failure mode of OA60 and OA90 specimens is delamination induced by interlaminar microcracks. The OA60 specimen achieves a better compression response with respect to bearing the load and absorbing the fracture energy because the sub-laminate that is formed after delamination can continue to bear the load until its intralaminar fracture occurs.

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Section: Introductionmentioning

confidence: 99%