Applied Composite Materials

, Volume 22, Issue 6, pp 599–621 | Cite as

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

  • Frederic Lachaud
  • Christine Espinosa
  • Laurent Michel
  • Pierre Rahme
  • Robert Piquet
Article
  • 316 Downloads

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 “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.

Keywords

Composite Materials Delamination Crack Propagation Mixed Mode Compression After Impact Smooth Particle Hydrodynamics 

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Copyright information

© Springer Science+Business Media Dordrecht 2014

Authors and Affiliations

  • Frederic Lachaud
    • 1
  • Christine Espinosa
    • 1
  • Laurent Michel
    • 1
  • Pierre Rahme
    • 2
  • Robert Piquet
    • 1
  1. 1.Université de Toulouse, ISAE ICA (Institut Clément Ader)Toulouse Cedex4France
  2. 2.Faculty of Engineering, Mechanical Engineering DepartmentLebanese UniversityRoumiehLebanon

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