Performance Analysis of Ply Orientation in Composite Laminates

Kumari, Nutan; Mehar, Afroz; Abdulrahman, Mohammed Ahmed; Tatineni, Sheetal; Shashank, Ellendula Venkateshwara; Muthyala, Jonathan Ted

doi:10.1016/j.matpr.2017.12.200

Cited by 3 publications

(1 citation statement)

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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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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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Performance analysis of composite ply orientation in aeronautical application of unmanned aerial vehicle (UAV) NACA4415 wing

Basri

Sultan

Faizal

et al. 2019

Journal of Materials Research and Technology

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Analysis and determination of first ply failure of the composite laminate using different failure criteria

Dewangan¹,

Rajput²

2019

IOP Conf. Ser.: Mater. Sci. Eng.

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This work relates to the first ply failure load investigation of composite laminate plates for different failure criteria under in-plane loading condition in two-dimensional spaces. In this context, first ply failure strengths investigated for different angle ply and number of the lamina. Writing a programme of FEM (finite element method) in MATLAB and calculating failure load for each lamina of the composite laminate by using various failure criteria such as max stress failure criterion, max strain failure criterion, Tsai-Hill, Tsai-Wu and Hoffman failure theory. Failure load calculated for three-ply composite laminate with [45°/-45°/45°] ply angle on the basis of these five failure theories shows very good conformity with the previous paper results. Kevlar/epoxy is taken for the calculation of first ply failure load with different ply orientation.

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Performance Analysis of Ply Orientation in Composite Laminates

Cited by 3 publications

References 0 publications

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

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

Performance analysis of composite ply orientation in aeronautical application of unmanned aerial vehicle (UAV) NACA4415 wing

Analysis and determination of first ply failure of the composite laminate using different failure criteria

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