Modelling bird impacts on an aircraft wing - Part 2: Modelling the impact with an SPH bird model

In a collaborative research project, aircraft wing leading edge structures with a glass-based Fibre Metal Laminate (FML) skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this second part of a two-part paper, a finite element...

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Bibliographic Details
Published in:International journal of crashworthiness 2005-01, Vol.10 (1), p.51-59
Main Authors: McCarthy, M A, Xiao, J R, McCarthy, C T, Kamoulakos, A, Ramos, J, Gallard, J P, Melito, V
Format: Article
Language:English
Subjects:
aircraft wing leading edge
Aves
Bird strike
Fibre Metal Laminate
smooth particle hydrodynamics
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Summary:In a collaborative research project, aircraft wing leading edge structures with a glass-based Fibre Metal Laminate (FML) skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this second part of a two-part paper, a finite element model is developed for simulating the bird strike tests, using Smooth Particle Hydrodynamics (SPH) for modelling the bird and the material model developed in Part 1 of the paper for modelling the leading edge skin. The bird parameters are obtained from a system identification analysis of strikes on flat plates. Pre-test simulations correctly predicted that the bird did no penetrate the leading edge skin, and correctly forecast that one FML lay-up would deform more than the other. The SPH bird model showed no signs of instability and correctly modelled the break-up of the bird into particles. The rivets connecting the skin to the ribs were found to have a profound effect on the performance of the structure.
ISSN:1358-8265
1573-8965
1754-2111
DOI:10.1533/ijcr.2005.0325