| Titre : |
Impact on composite aircraft fuselages : Modeling strategies for predicting the residual strength |
| Type de document : |
texte imprimé |
| Auteurs : |
Christine Espinosa, Auteur ; Frédéric Lachaud, Auteur ; Laurent Michel, Auteur ; Robert Piquet, Auteur |
| Année de publication : |
2014 |
| Article en page(s) : |
p. 271-318 |
| Note générale : |
Bibliogr. |
| Langues : |
Anglais (eng) |
| Catégories : |
Analyse numérique
Avions -- Fuselage
Avions -- Matériaux
Composites -- Délaminage
Endommagement (mécanique)
Essais (technologie)
Impact (mécanique)
Modèles mathématiques
Modélisation tridimensionnelle
Plasticité
|
| Index. décimale : |
620.1 Mécanique de l'ingénieur (mécanique appliquée) et matériaux |
| Résumé : |
Computer based design using damage mechanics is thought about as a new methodology to replace tests and help deriving realistic while simple new rules for Aeronautic Certification of composite structures. Numerical methods and models must then be robust and predictive. Three different computational strategies are developed and compared : a Cohesive Model (CM), a Continuous Damage Material model coupling failure modes and damage (CDM), a Mixed Methodology (MM) using the CDM for delamination initiation and the CM for 3D crack propagation and mesh openings. The CDM model is used to simulate the impact of a composite blade on a composite fuselage section and to predict the CAI behavior of samples up to fracture. Comparisons with experiments are discussed. |
| Note de contenu : |
- INTRODUCTION : Purpose and limits of this chapter - Topics and issues addressed
- DELAMINATION ANALYSIS : Cohesive Model (CM) approach - Structural behaviors with the Cohesive Model approach - Data identification and discussion
- UNIDIRECTIONAL PLY BEHAVIOR : A CONTINUOUS DAMAGE MODEL
- COUPLINGPLY DAMAGE AND 3D OPEN CRACKS BRANCHING : A MIXED METHODOLOGY : Numerical method - Principe of the models coupling
- VIRTUAL VERSUS EXPERIMENTAL TEST OF IMPACT RESISTANCE : Impact tests and damage - Cohesive model : interface elements for plies delamination - Continuum Damage Mechanics model - 3D crack opening model : Mixed Methodology - Comparing Cohesive Model and Continuous Damage Model
- BOTTOM UP : TO THE VIRTUAL TESTING OF COMPOSITE FUSELAGE : Impact damage tolerance : CAI - Impact resistance of a fuselage : a numerical approach |
| DOI : |
10.3166/rcma.24.271-318 |
| Permalink : |
https://e-campus.itech.fr/pmb/opac_css/index.php?lvl=notice_display&id=21972 |
in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES > Vol. 24, N° 3 (07-08-09/2014) . - p. 271-318
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Impact on composite aircraft fuselages in REVUE DES COMPOSITES ET DES MATERIAUX AVANCES, Vol. 24, N° 3 (07-08-09/2014)
