Influence of ply orientation on free-edge effects in laminates subjected to in-plane loads

Solis, A.; Sánchez-Sáez, S.; Barbero, Ever J.

doi:10.1016/j.compositesb.2018.07.030

Cited by 20 publications

(15 citation statements)

References 29 publications

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“…In order to study the dependence of the out-of-plane stresses on these two parameters, an analysis of symmetric laminates with varying stacking sequences and ply orientations was carried out. [1] M. Russello et al did research on electrical conductivity of carbon fibre laminates. In this paper, by using carbon nano-tubes, the electrical conductivity of thin-ply carbon fibre laminates in transverse is increased was investigated experimentally.…”

Section: Literature Surveymentioning

confidence: 99%

Layerwise Damage Investigation of Ply Orientation on Strength Characteristics of Carbon Fibre Composite

Karale¹

2019

IJRASET

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Synthetic composites have higher strength to weight ratio and are extensively used in industrial applications. Most of the composites have orthotropic properties and their strength varies as per orientation. Carbon fibers are one of the synthetic fibres having extensively high tensile strength. Laminates having different ply orientations have different properties and strengths. Hence, to enhance strength properties, reducing layerwise damage becomes of up most important. It is not possible to investigate the layerwise damage of each ply separately by experimentation. This can be done by using ACP tool in ANSYS 19.2 software. In this project, two laminates having orientations as 0°-45°-0° and 0°-30°-60° are considered for analysis. Advance composite pre-post [ACP] tool from ANSYS software is used for simulation of these layers. From this analysis total deformation, equivalent stress and damage of each layer is determined. After getting layerwise damage, experimentation is done. Experimental tensile test is done on specimens above ply orientations to obtain force vs. deflection diagrams. Comparative analysis is made between simulation and experimental results. Results and conclusion is drawn. Experimental and simulation values differ by only 1%. This validates the simulation value of force reaction. Also from the result it can be seen that 0°-45°-0° laminate gives better results than that of 0°-30°-60° laminate. Hence, it can be concluded that Plate 1 has higher strength than Plate 2 i.e., 0°-45°-0° is better ply orientation than 0°-30°-60° ply orientation. Also it is observed that different ply orientations have different strengths.

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Section: Literature Surveymentioning

confidence: 99%

Layerwise Damage Investigation of Ply Orientation on Strength Characteristics of Carbon Fibre Composite

Karale¹

2019

IJRASET

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“…The angle configurations concern tapes and fabrics used to produce laminates. Lately, the usage of different angles, such as ±30°, ±60° [ 2 , 3 , 4 , 5 , 6 , 7 , 8 , 9 , 10 , 11 ], has been debated. In the case of tubes and pressure vessels, the angle of fibre location (depending on the target strength properties) is determined to the nearest 1°.…”

Section: Introductionmentioning

confidence: 99%

Optimisation of the Thin-Walled Composite Structures in Terms of Critical Buckling Force

Szklarek

Gajewski

2020

Materials

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The paper presents the optimisation of thin-walled composite structures on a representative sample of a thin-walled column made of carbon laminate with a channel section-type profile. The optimisation consisted of determining the configuration of laminate layers for which the tested structure has the greatest resistance to the loss of stability. The optimisation of the layer configuration was performed using two methods. The first method, divided into two stages to reduce the time, was to determine the optimum arrangement angle in each laminate layer using finite element methods (FEM). The second method employed artificial neural networks for predicting critical buckling force values and the creation of an optimisation tool. Artificial neural networks were combined into groups of networks, thereby improving the quality of the obtained results and simplifying the obtained neural networks. The results from computations were verified against the results obtained from the experiment. The optimisation was performed using ABAQUS® and STATISTICA® software.

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“…The analysis of the interlaminar stresses at the free-edge in laminates has been studied since the 70s of the last century [4]. Since then many works have focused on this topic, mainly on the free-edge of a laminate because the modelization of a straight edge is simpler [5][6][7][8]. The stress field around the hole is clearly three-dimensional and with large gradients in all the components [9,10].…”

Section: Introductionmentioning

confidence: 99%

“…The stress field around the hole is clearly three-dimensional and with large gradients in all the components [9,10]. Some works use analytical models [11,12] or numerical models [1,8] to estimate the three-dimensional stress field in intact laminates. When damage appears, the stresses change and purely elastic models can not be considered valid.…”

Section: Introductionmentioning

confidence: 99%

“…More complex models can predict damage initiation and growth [23,[28][29][30][31][32][33][34][35] In a previous work, the authors analysed the edge effect in laminates without damage subjected to tensile loads [8] due the symmetries of the stress field of this problem some simplification reduced the complexity of the model. To analyse laminates with holes and with damage more complex models are needed.…”

Section: Introductionmentioning

confidence: 99%

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Numerical analysis of interlaminar stresses in open-hole laminates under compression

Solis

Sánchez-Sáez

Martı́nez

et al. 2019

Composite Structures

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In this paper, the interlaminar stresses in open-hole laminates subjected to compressive loads are analysed using a numerical model. This model implements the Serial/Parallel Mixing Theory (S/PMT) and a Continuum Damage Mechanics (CDM) approach. The S/PMT estimates the global stiffness in the laminate from fibre and matrix properties.The CDM approach models the damage initiation due to fibre microbuckling. The global response estimated by the model was verified with experimental data from the literature. The model predicts that the damage initiates in the laminate middle-plane where the thickest block of plies oriented in the load direction is located, and progressively propagates to the nearest block of layers with the same orientation. Two laminate stacking sequences were analysed. The interlaminar stresses around the hole presented symmetry with respect to the load direction and the perpendicular axis, being located the maximum and minimum values in different angular positions for each stress component and laminate.

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Influence of ply orientation on free-edge effects in laminates subjected to in-plane loads

Abstract: Influence of ply orientation on free-edge effects in laminates subjected to in-plane loads. Composites Part B: Engineering, 153, 149-158.

Cited by 20 publications

References 29 publications

Layerwise Damage Investigation of Ply Orientation on Strength Characteristics of Carbon Fibre Composite

Layerwise Damage Investigation of Ply Orientation on Strength Characteristics of Carbon Fibre Composite

Optimisation of the Thin-Walled Composite Structures in Terms of Critical Buckling Force

Numerical analysis of interlaminar stresses in open-hole laminates under compression

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