Item


A Thermodynamically Consistent Damage Model for Advanced Composites

A continuum damage model for the prediction of damage onset and structural collapse of structures manufactured in fiber-reinforced plastic laminates is proposed. The principal damage mechanisms occurring in the longitudinal and transverse directions of a ply are represented by a damage tensor that is fixed in space. Crack closure under load reversal effects are taken into account using damage variables established as a function of the sign of the components of the stress tensor. Damage activation functions based on the LaRC04 failure criteria are used to predict the different damage mechanisms occurring at the ply level. The constitutive damage model is implemented in a finite element code. The objectivity of the numerical model is assured by regularizing the dissipated energy at a material point using Bazant’s Crack Band Model. To verify the accuracy of the approach, analyses of coupon specimens were performed, and the numerical predictions were compared with experimental data

NASA/TM-2006-214282

© NASA TM Technical Reports, 2006, núm. 214282

National Aeronautics and Space Administration

Author: Maimí Vert, Pere
Camanho, Pedro Manuel Ponces Rodrigues de Castro
Mayugo Majó, Joan Andreu
Dávila, Carlos G.
Date: 2006
Abstract: A continuum damage model for the prediction of damage onset and structural collapse of structures manufactured in fiber-reinforced plastic laminates is proposed. The principal damage mechanisms occurring in the longitudinal and transverse directions of a ply are represented by a damage tensor that is fixed in space. Crack closure under load reversal effects are taken into account using damage variables established as a function of the sign of the components of the stress tensor. Damage activation functions based on the LaRC04 failure criteria are used to predict the different damage mechanisms occurring at the ply level. The constitutive damage model is implemented in a finite element code. The objectivity of the numerical model is assured by regularizing the dissipated energy at a material point using Bazant’s Crack Band Model. To verify the accuracy of the approach, analyses of coupon specimens were performed, and the numerical predictions were compared with experimental data
NASA/TM-2006-214282
Format: application/pdf
Document access: http://hdl.handle.net/10256/7898
Language: eng
Publisher: National Aeronautics and Space Administration
Collection: Articles publicats (D-EMCI)
Is part of: © NASA TM Technical Reports, 2006, núm. 214282
Rights: Tots els drets reservats
Subject: Mecànica de fractura
Fracture mechanics
Materials compostos -- Fatiga
Composite materials -- Fatigue
Assaigs de materials
Materials -- Testing
Title: A Thermodynamically Consistent Damage Model for Advanced Composites
Type: info:eu-repo/semantics/article
Repository: DUGiDocs

Subjects

Authors