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

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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.

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Acknowledgments

The authors are grateful of Higher Education Commission of Pakistan for partial funding. Special thanks are also extended to IMPETUS Afea France and all the students and technical staff of ISAE for their valuable input towards numerical and experimental aspects, respectively.

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Authors and Affiliations

  1. Université de Toulouse, ISAE ICA (Institut Clément Ader), ISAE/DMSM, 10, Avenue Edouard Belin, BP54032, 31055, Toulouse Cedex4, France

    Frederic Lachaud, Christine Espinosa, Laurent Michel & Robert Piquet

  2. Faculty of Engineering, Mechanical Engineering Department, Lebanese University, P.O. Box: 27622319, Roumieh, Lebanon

    Pierre Rahme

Authors
  1. Frederic Lachaud
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  2. Christine Espinosa
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  3. Laurent Michel
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  4. Pierre Rahme
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  5. Robert Piquet
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Corresponding author

Correspondence to Frederic Lachaud.

Appendix A

Appendix A

Fig. 24
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View of delamination size for 0/45 interface and damages of 0° plies after impact, [02,452,90,−452,02,−452,90,452,02] laminate (non impacted face)

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Fig. 25
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View of delamination size for 452/90 interface and damages of 45° plies after impact, [02,452,90,−452,02,−452,90,452,02] laminate

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Fig. 26
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View of delamination size for 90/−452 interface and damages of 90° ply after impact, [02,452,90,−452,02,−452,90,452,02] laminate

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Fig. 27
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View of delamination size for −452/02 interface and damages of −45° plies after impact, [02,452,90,−452,02,−452,90,452,02] laminate

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Fig. 28
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View of delamination size for −452/02 interface and damages of 0° plies after impact, [02,452,90,−452,02,−452,90,452,02] laminate

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Fig. 29
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View of delamination size for -452/90 interface and damages of −45° plies after impact, [02,452,90,−452,02,−452,90,452,02] laminate

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Fig. 30
figure 30

View of delamination size for 90/452 interface and damages of 90° ply after impact, [02,452,90,−452,02,−452,90,452,02] laminate

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Fig. 31
figure 31

View of delamination size for 452/02 interface and damages of −45° plies after impact, [02,452,90,−452,02,−452,90,452,02] laminate (impacted face)

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Lachaud, F., Espinosa, C., Michel, L. et al. Modelling Strategies for Predicting the Residual Strength of Impacted Composite Aircraft Fuselages. Appl Compos Mater 22, 599–621 (2015). https://doi.org/10.1007/s10443-014-9427-y

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  • DOI: https://doi.org/10.1007/s10443-014-9427-y

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