Publication :


Modelling strategies for predicting the residual strength of impacted composite aircraft fuselages

Authors: F. Lachaud, C. Espinosa, L. Michel, P. Rahme and R. Piquet
Year: décembre 2015
Journal: Applied Composite Materials.
Volume: 22, Number: 6, Pages: 599-621

DOI: 10.1007/s10443-014-9427-y
Référencé ISI Web Of Science
Référencé Scopus

Abstract Aeronautic Certification rules established for the metallic materials are not conve- nient for the composite structures concerning the resistance against impact. The computer- based design is a new methodology that is thought about to replace the experimental tests. It becomes necessary for numerical methods to be robust and predictive for impact. Three questions are addressed in this study: (i) can a numerical model be “ mechanically intrinsic ” to predict damage after impact, (ii) can this model be the same for a lab sample and a large structure, and (iii) can the numerical model be predictive enough to predict the Compression After Impact (CAI)? Three different computational strategies are used and compared: a Cohesive Model (CM), a Continuous Damage Model (CDM) coupling failure modes and damage, and a Mixed Methodology (MM) using the CDM for delamination initiation and the CM for cracks propagation. The first attempts to use the Smooth Particle Hydrodynamics method are presented. Finally, impact on a fuselage is modelled and a numerical two-stage strategy is developed to predict the CAI

Bibtex citation :
Author={Lachaud, F. and Espinosa, C. and Michel, L. and Rahme, P. and Piquet, R.},
Title={Modelling strategies for predicting the residual strength of impacted composite aircraft fuselages},
Journal={Applied Composite Materials},

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