Finite Element Implementation of Failure and Damage Simulation in Composite Plates

Žmindák, Milan; Dudinský, Martin

doi:10.5772/48248

Cited by 10 publications

(9 citation statements)

References 20 publications

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“…A two-subplate orthotropic model [13] loaded by mode II was proposed as failure model. The material characteristics of the sublaminates were calculated by homogenization [14].…”

Section: Discussionmentioning

confidence: 99%

Delamination of Composite Laminate Plate by Sliding Load Mode

Kormaníková¹

2017

Transactions of the VŠB – Technical University of Ostrava, Civil Engineering Series.

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The paper presents the mixed-mode delamination response of laminate plate made of two sublaminates. To this purpose a sliding load mode of delamination is proposed as failure model. A quasistatic rate-independent delamination problem of laminate plates with a finite thickness is considered. A rate-independent delamination model for a laminated Kirchhoff-Love plate is obtained. The failure model is implemented in ANSYS code to calculate the mixed-mode delamination response as energy release rate along the lamination front.

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“…A two-subplate orthotropic model [13] loaded by mode II was proposed as failure model. The material characteristics of the sublaminates were calculated by homogenization [14].…”

Section: Discussionmentioning

confidence: 99%

Delamination of Composite Laminate Plate by Sliding Load Mode

Kormaníková¹

2017

Transactions of the VŠB – Technical University of Ostrava, Civil Engineering Series.

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“…-The return -mapping algorithm (RMA) [7] calculates the increment (decrement) of crack density λ as A RMA achieves this by integrating until = 0 and updating the crack density with iterative increments calculated as = − ⁄ .…”

Section: Solution Algorithmmentioning

confidence: 99%

Determination of the laminate strains using discrete damage mechanics

Žmindák

Kaco²,

Novák

et al. 2019

MATEC Web Conf.

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In this paper discrete damage mechanics (DDM) is used to predict inter-laminar transverse and shear damage initiation and evolution in terms of the fracture toughness of the laminate. The finite element method (FEM) is one of the most widely and most popular numerical methods for analyzing composite structures, therefore ANSYS commercial software is used for analysis of layered plate composite structure reinforced with long unidirectional fibers with Carbon/Epoxy material. Because ANSYS does not have a built-in capability for calculating crack density, we have to use plugin. A methodology for determination of the fracture toughness is based on fitting DDM model and these data are obtained from literature. Also, prediction of modulus vs. applied strain is contrasted with ply discount results and the effect of in situ correction of strength is highlighted. Evaluation of matrix cracking detected in lamina has been solved using return mapping algorithm.

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“…They play a very important role in the automotive, aviation and aerospace industry and are also used for the manufacture of ships, submarines, nuclear and chemical installations, etc. [1]. Damage to laminated fiber-reinforced composites involves fiber breakage, matrix cracking, fiber-matrix debonding and delamination.…”

Section: Introductionmentioning

confidence: 99%

Vibration Analysis of Damaged Viscoelastic Composite Sandwich Plate

Messaoud,

Amrane

2024

Period. Polytech. Mech. Eng.

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This paper presents a study of free and forced vibration of composite sandwich plate with and without damage using the finite element analysis developed under ANSYS APDL software. This modeling uses the 8-node shell 281 element to modelized the composite laminates of the top and bottom face sheets of the sandwich plate and the 20-node higher order solid 186 element to modelized the viscoelastic core. Two sets of boundaries are considered; Simply supported and clamped boundary conditions at all edges. The effect of damaged face sheets layers on natural frequencies, mode shapes, the frequency and transient responses of the sandwich plate is investigated. Numerical results show remarkable shifts of the natural frequencies, frequency and transient responses due to the presence of damage. It is concluded that the natural frequencies decreasing is due to the loss of structural stiffness. Natural frequencies of the sandwich plates are close to those issued from numerical results available in the literature.

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Finite Element Implementation of Failure and Damage Simulation in Composite Plates

Cited by 10 publications

References 20 publications

Delamination of Composite Laminate Plate by Sliding Load Mode

Delamination of Composite Laminate Plate by Sliding Load Mode

Determination of the laminate strains using discrete damage mechanics

Vibration Analysis of Damaged Viscoelastic Composite Sandwich Plate

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