Studies have shown that the angle of fiber orientation significantly affects the mechanical properties of a composite laminate. Although investigations on the properties of the composite material have been conducted, there is still a lack of studies related to Kevlar/Epoxy laminate. Therefore, this study aims to investigate the effects of the angle of fiber orientation to woven Kevlar/Epoxy laminates under a compression state. The study was conducted in two stages comprising of numerical validation and failure analysis. Maximum Stress Theory and Tsai-Wu Failure criteria were selected for the failure prediction. The laminates were made of 24 layers woven Kevlar/epoxy and the stacking sequence was (θ4/0<4-θ4)s. The angle of fiber orientation, θ, was varied from 0° to 90° and failure loads for both flat plate and flat plate with circular hole were determined. The trend of displacement and failure behaviour for both type of plates were compared. From the results, it is found that the effects of the fiber angle on the plate with circular hole are more significant than the flat. Therefore, it can be reasoned that the current study is useful in contributing significant knowledge to better understand the failure behaviour of composite plate.
Studies have shown that the angle of fiber orientation significantly affects the mechanical properties of a composite laminate. Due to this, accurate prediction of the laminate response because of the loading effect is crucial. Many investigations on the properties of composite materials have been conducted. However, there is still the lack of study related to Kevlar/Epoxy laminate. Therefore, this study aims to investigate the effect of the angle of fiber orientation to woven and unidirectional (UD) Kevlar/Epoxy laminates under compression state. The study was conducted in two stages comprising of numerical validation and failure analysis. For the failure analysis, a flat plate and flat plate with circular hole under compression were modelled using ANSYS. Two of the most common failure models, Maximum Stress Theory and Tsai-Wu Failure criteria were selected for the failure prediction. The laminates were made of 24 layers woven Kevlar/Epoxy and the stacking sequence was (θ4 /04 /-θ4 )s. The angle of fiber orientations, θ, have been varied from 0° to 90° and failure loads for both flat plate and flat plate with circular hole were determined. The trend of displacement and failure behaviour for both types of plate were compared. The results show that the angle of fiber orientation affects significantly the trend of the displacement and failure curves of UD and woven Kevlar/Epoxy. The curves for UD and woven; flat plate and flat plate with circular hole are different and unique in nature; and thus should be treated individually. These analysis and findings are important in aiding the engineers at designing a stronger woven Kevlar/Epoxy composite laminate. Therefore, it can be concluded that the current study has contributed towards enhancing knowledge about the compressive failure behaviour of unidirectional and woven Kevlar/Epoxy composite laminates
The increasing trendof constructing componentsmade of composite laminates is due tothe flexibility intailoring their properties and high strength-to-weight ratio. Nevertheless, most practical components involve cutout features for fastening and these cutouts could significantly reduce the strength of the laminate. Due to its importance, many studies were conducted to study the effect of circular cutouts however, there is lack of information regarding the effect of various cutout shapes. Therefore, this study aims to investigate the compressive failure behaviour of Kevlar Epoxy and Glass Epoxy composite laminates due to different cutout shapes and sizes with variation in fiber orientations. Finite element software, ANSYS were used to simulate the deformation and failure behaviour of the laminates under compressive load. Prior to that, mesh convergence analysis and numerical validation were performed. Failure analysis was conducted for various cutout shapes (square cutout, diamond cutout, and circular) and size, based on Maximum Stress Theory. The results show that the existence of the cutouts on the composite laminates have reduced up to ten times the strength of the laminated composite plates. This information regarding the failure behaviour is important when designing components made of composite laminates under compression.
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