Damage Model and Progressive Failure Analyses for Filament Wound Composite Laminates

Ribeiro, Marcelo Leite; Vandepitte, Dirk

doi:10.1007/s10443-013-9315-x

Cited by 55 publications

(31 citation statements)

References 18 publications

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“…In continuum damage mechanics (CDM) the types of damage are represented and modelled by material stiffness degradation [21]- Figure 2. The paper by Ribeiro [22] presents the development of the damage model and its subsequent application to the simulation of the progressive failure criterion. The work is strictly related to The paper by Ribeiro [22] presents the development of the damage model and its subsequent application to the simulation of the progressive failure criterion.…”

Section: Introductionmentioning

confidence: 99%

Progressive Failure Analysis of Thin-Walled Composite Structures Verified Experimentally

et al. 2020

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The subject of the presented research was a thin-walled composite column made of CFRP (carbon-epoxy laminate). The test sample had a top-hat cross-section with a symmetrical arrangement of laminate layers [90/−45/45/0]s. The composite structure was subjected to the process of axial compression. Experimental and numerical tests for the loss of stability and load-carrying capacity of the composite construction were carried out. The numerical buckling analysis was carried out based on the minimum potential energy criterion (based on the solution of an eigenvalue problem). The study of loss of load-carrying capacity was performed on the basis of a progressive failure analysis, solving the problem of non-linear stability based on Newton-Raphson’s incremental iterative method. Numerical results of critical and post-critical state were confronted with experimental research in order to estimate the vulnerable areas of the structure, showing areas prone to damage of the material.

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Section: Introductionmentioning

confidence: 99%

Progressive Failure Analysis of Thin-Walled Composite Structures Verified Experimentally

et al. 2020

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“…The model has shown good potentiality by predicting progressive failure when loading has predominating in-plane stresses. Some application can be found in literature like a 3-point bending simulation of flat filament wound laminates [12], optimization of composite stacking sequence [13], hydrostatic external pressure of composite tubes [14], and radial compression [15].…”

Section: Intralaminar Modelmentioning

confidence: 99%

A Delamination Propagation Model for Fiber Reinforced Laminated Composite Materials

Aveiga

Ribeiro

2018

Mathematical Problems in Engineering

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The employment of composite materials in the aerospace industry has been gradually considered due to the fundamental lightweight and strength characteristics that this type of materials has. The science material and technological progress reached matched perfectly with the requirements for high-performance materials in aircraft and aerospace structures; thus, the development of primary structure elements applying composite materials became something very convenient. It is extremely important to pay attention to the failure modes that influence composite materials performances, since these failures lead to a loss of stiffness and strength of the laminate. Delamination is a failure mode present in most of the damaged structures and can be ruinous, considering that the evolution of interlaminar defects can carry the structure to a total failure followed by its collapse. The present work aims at the development of a delamination propagation model to estimate a progressive interlaminar delamination failure in laminated composite materials and to allow the prediction of material's degradation due to delamination phenomenon. Experimental data, available at literature, was considered to determine some model parameters, like the strain energy release rate, using GFRPs laminated composites. This new delamination propagation model was implemented as subroutines in FORTRAN language (UMATUser Material Subroutine) with formulations based on the Fracture Mechanics and Continuum Damage Mechanics. Finally, the UMAT subroutine was complemented with an intralaminar model and compiled beside the commercial Finite Element (FE) software ABAQUS6.

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“…More details about the damage model can be found in Ribeiro et al (2012aRibeiro et al ( , 2013aRibeiro et al ( , 2013b). …”

Section: Damage Modelmentioning

confidence: 99%

“…The fundamentals of the damage model can be found at Ribeiro's PhD thesis (Ribeiro, 2013a). The equations of the damage model shown in the (Ribeiro et al, 2013b) Failure Criteria Type of Failure Degradation Law…”

Section: Damage Modelmentioning

confidence: 99%

“…The behaviour of the composite laminated structures depends on the behaviour of each homogenized lamina, including the damage mechanisms of the fibres and the matrix (epoxy resin). These damage mechanisms are represented by mathematical equations based on experimental observations performed by Ribeiro et al (2012aRibeiro et al ( , 2013b. The fundamentals of the damage model can be found at Ribeiro's PhD thesis (Ribeiro, 2013a).…”

Section: Damage Modelmentioning

confidence: 99%

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Development of a criterion for predicting residual strength of composite structures damaged by impact loading

Medeiros¹

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Damage Model and Progressive Failure Analyses for Filament Wound Composite Laminates

Cited by 55 publications

References 18 publications

Progressive Failure Analysis of Thin-Walled Composite Structures Verified Experimentally

Progressive Failure Analysis of Thin-Walled Composite Structures Verified Experimentally

A Delamination Propagation Model for Fiber Reinforced Laminated Composite Materials

Development of a criterion for predicting residual strength of composite structures damaged by impact loading

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