Modelling Strategies for Predicting the Residual Strength of Impacted Composite Aircraft Fuselages

Abstract : Aeronautic Certification rules established for the metallic materials are not convenient 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 \textquotedblleftmechanically intrinsic\textquotedblright 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.
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Contributor : Pierre Naegelen <>
Submitted on : Tuesday, December 11, 2018 - 12:18:51 PM
Last modification on : Friday, April 12, 2019 - 4:23:20 PM

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  • HAL Id : hal-01951234, version 1

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Frederic Lachaud, Christine Espinosa, Laurent Michel, Pierre Rahme, Robert Piquet. Modelling Strategies for Predicting the Residual Strength of Impacted Composite Aircraft Fuselages. Applied Composite Materials, 2015, 22 (6), pp.599--621. ⟨hal-01951234⟩

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