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INTRA-LAMINAR PROGRESSIVE DAMAGE OF GENERAL CONFIGURATION LAMINATED COMPOSITES
Adi Adumitroaie (Johannes Kepler University Linz) Ever Barbero (West Virginia University) Martin Schagerl (Johannes Kepler University Linz)
A new analytical model for progressive damage transverse matrix cracking in continuous _x000C_fiber reinforced laminates is developed. The increase of fracture toughness during matrix crack multiplication (R-curve) is included into the model.
NON-LOCALIZED FAILURE CRITERION FOR OPEN-HOLE AND PINNED JOINT COMPOSITE STRUCTURE USING CHARACTERISTIC AREA/VOLUME APPROACH
Arruck Tragangoon (MINES ParisTech) Baramee Patamaprohm (MINES ParisTech) Jacques Renard (MINES ParisTech)
The method to predict the failure of composite laminate structure induced by local stress concentration is proposed. Open-hole and bolted joint specimens of woven glass/polyamide6 composite were investigated in this work.
COMPUTATIONAL FRAMEWORK FOR DAMAGE MODELLING OF FIBER REINFORCED COMPOSITES
Michael Stuebner (University of Dayton) Endel Iarve (University of Texas Arlington) Artem Aleshin (University of South Carolina) Eric Zhou (University of Dayton) David Mollenhauer (Air Force Research Laboratory) Michael Braginsky Brent Volk (US Air Force Research Laboratory)
An advanced framework for damage modelling in composites applicable to a wide range of fiber-reinforced polymer matrix and ceramic matrix composites based on the FEM package BSAM designed at the University of Dayton Research Institute is presented.
EVALUATION OF IMPACT DAMAGE IN CIRCULAR LAMINATES SUBJECTED TO A TRANSVERSE LOAD
Hiroshi Suemasu (Sophia University)
Responses of nonlinear axisymmetric plates with multiple delaminations subjected to a transverse concentrated load are approximately solved to evaluate the significance of low velocity foreign object damage in quasi-isotropic composite laminates.
DAMAGE EVOLUTION UNDER LONG-TERM, HIGH AND CONSTANT LOADING OF A CARBON/EPOXY LAMINATE
Aurore Girardot (CEA) Noël Lahellec (LMA-CNRS) Christian Hochard (LMA-CNRS) Sandrine Leroch (CEA)
The objective of this work is to study,under high loads and long periods,the propagation of transverse cracks.Experimental results are presented and it is observed an evolution of the matrix damage which is compared to the evolution for cyclic loads.
SCALING EFFECT IN NOTCHED COMPOSITES: THE DISCRETE PLY MODEL APPROACH
Joel Serra (Institut Clément Ader) Christophe Bouvet (Institut Clément Ader) Bruno Castanié (Institut Clément Ader) Caroline Petiot (Airbus Group Innovations)
Numerical and experimental investigations were carried out on the size effect in notched carbon/epoxy laminates. This paper presents a computational study of scaled open-hole tensile tests using the Discrete Ply Modeling (DPM) method.
SIZE EFFECT ON THROUGH-THICKNESS STRENGTH PROPERTIES OF 3D LOADED COMPOSITE LAMINATES
Marco Hoffmann (Airbus Group Innovations) Kristian Zimmermann (Airbus Group Innovations) Brian Bautz (Airbus Group Innovations) Peter Middendorf (University of Stuttgart)
The size effect on the through-thickness strength properties of unidirectional and quasi-isotropic carbon/epoxy laminates has been studied by a combined experimental and numerical approach. The results were evaluated by the Weibull statistical model.
PROGRESSIVE MATRIX CRACKING INDUCED DELAMINATION: A COMPARISON OF FINITE ELEMENT MODELLING TECHNIQUES
Johannes Reiner (University of Queensland) Martin Veidt (University of Queensland) Matthew Dargusch (University of Queensland) Lutz Gross (University of Queensland)
Matrix Cracking Induced Delamination is numerically investigated in carbon fibre reinforced laminates subjected to four-point bending. Two finite element modelling techniques with and without pre-inserted transverse matrix cracks are presented.
DAMAGE SUPPRESSION IN UD-CFRP WITH FIBRE DISCONTINUITY BY INTERLAMINAR TOUGHENING USING POLYAMIDE MESH
Hayato Nakatani (Osaka City University) Tatsuya Imamura (Osaka City University) Katsuhiko Osaka (Osaka City University)
Polyamide mesh is inserted into UD-CFRP with fibre discontinuity to improve interlaminar crack onset stress. An analytical model successfully predicts the onset stress by using fracture toughness G_IIR=3.82 kJ/m^2 obtained by a stabilized ENF test.
IDENTIFYING FAILURE INITIATION IN AUTOMOTIVE STRUCTURES MADE OF NCF REINFORCED COMPOSITES FOR HOT SPOT ANALYSIS
Henrik Molker (Volvo Car Corporation) Renaud Gutkin (Imperial College London) Silvestre Pinho (Imperial College London) Leif Asp (Chalmers University of Technology)
Identification of hot spots in shell model structure with orthotropic composite materials using state of the art 3D failure criteria. The full 3D stress state is evaluated from shell element results, based on stress equillibrium.
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