A progressive first ply failure model for woven ply CFRP laminates under static and fatigue loads

Hochard, Christian; Payan, Yohan; Bordreuil, Cyril

doi:10.1016/j.ijfatigue.2006.02.024

Cited by 57 publications

(29 citation statements)

References 8 publications

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“…ii) The evolution equations can be enriched or/and modified in order to account for time dependent behaviours such as visco-damage (Shahsavari et al, 2016), as well as for fatigue analyses (Hochard et al, 2006;Nouri et al, 2009). Moreover, viscoelastic mechanisms could be eventually added through a coupled formulation (Krairi and Doghri, 2014;Krasnobrizha et al, 2016;Praud et al, 2017).…”

Section: Numerical Simulations and Dissipative Behaviourmentioning

confidence: 99%

Hybrid micromechanical-phenomenological modelling of anisotropic damage and anelasticity induced by micro-cracks in unidirectional composites

Praud

Chatzigeorgiou

Chemisky

et al. 2017

Composite Structures

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Section: Numerical Simulations and Dissipative Behaviourmentioning

confidence: 99%

Hybrid micromechanical-phenomenological modelling of anisotropic damage and anelasticity induced by micro-cracks in unidirectional composites

Praud

Chatzigeorgiou

Chemisky

et al. 2017

Composite Structures

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“…Similarly for the assumption in equation 26, the out-of-plane ply stress increment is set equal to the out-of-plane laminate stress increment. The out-of-plane ply strain increment is calculated using the ply-level stiffness matrices, the in-plane laminate strain increment, and the out-of-plane laminate stress increment using equation 27. The in-plane ply stress increment is calculated similarly using equation 28.…”

Section: Ply-level Stress and Strain Calculationsmentioning

confidence: 99%

An Improved Design Methodology for Modeling Thick-Section Composite Structures Using a Multiscale Approach

Staniszewski¹,

Bogetti²,

Keefe³

et al. 2012

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Approved for public release; distribution is unlimited.ii REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)September 2012 SPONSOR/MONITOR'S REPORT NUMBER(S) 12. DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTMaterial nonlinearity and progressive ply failure are important considerations in the finite element modeling of thick-section composite structures. LAMPATNL uses a method to model the material nonlinearity and progressive ply failure of composite laminates using finite element software without explicitly simulating individual plies. Improvements to LAMPATNL are documented and discussed in this report. Also, LAMPATNL is validated against both the linear and nonlinear material point models. In this work, a standardized process for designing composite structures with LAMPATNL using newly formulated output parameters, stiffness ratios, to analyze the nonlinear response and progressive failure of the composite structure is developed. These new parameters greatly improve the visualization of critical design information of the structure. Two case studies, an open-hole sample under multi-axial loading and a compressive shear sample, are evaluated using the design methodology. Coupling LAMPATNL with a design methodology and new stiffness ratio parameters demonstrates the utility of progressive failure and nonlinear analysis when applied to composite structures. The straightforward visualization of critical design information creates a unique approach to analyzing the design of thick section composites. This methodology represents a unique contribution to the modeling of composite structures that is not matched by any current composite model. iii

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“…Woven-fabric composite laminates offer a number of attractive properties compared to their unidirectional-tape counterparts such as lower production costs, better drapability, good resistance to fracture and transverse rupture due to weaving resistance, and high impact strength [1,2]. These properties have attracted the sports industry to incorporate woven CFRP laminates in the design of sporting goods.…”

Section: Introductionmentioning

confidence: 99%

Finite-element modelling of bending of CFRP laminates: Multiple delaminations

Ullah

Harland

Lucas

et al. 2012

Computational Materials Science

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Carbon fibre-reinforced polymer (CFRP) composites are widely used in aerospace, automotive and construction structures thanks to their high specific strength and stiffness. They can also be used in various products in sports industry. Such products can be exposed to different in-service conditions such as large bending deformation and multiple impacts. In contrast to more traditional homogeneous structural materials like metals and alloys, composites demonstrate multiple modes of damage and fracture due to their heterogeneity and microstructure. Damage

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A progressive first ply failure model for woven ply CFRP laminates under static and fatigue loads

Cited by 57 publications

References 8 publications

Hybrid micromechanical-phenomenological modelling of anisotropic damage and anelasticity induced by micro-cracks in unidirectional composites

Hybrid micromechanical-phenomenological modelling of anisotropic damage and anelasticity induced by micro-cracks in unidirectional composites

An Improved Design Methodology for Modeling Thick-Section Composite Structures Using a Multiscale Approach

Finite-element modelling of bending of CFRP laminates: Multiple delaminations

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