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Bird Strike Damage Analysis in Aircraft Structures Using Abaqus/Explicit and Coupled Eulerian Lagrangian Approach (CROSBI ID 168101)

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Smojver, Ivica ; Ivančević, Darko Bird Strike Damage Analysis in Aircraft Structures Using Abaqus/Explicit and Coupled Eulerian Lagrangian Approach // Composites science and technology, 71 (2011), 4; 489-498. doi: 10.1016/j.compscitech.2010.12.024

Podaci o odgovornosti

Smojver, Ivica ; Ivančević, Darko

engleski

Bird Strike Damage Analysis in Aircraft Structures Using Abaqus/Explicit and Coupled Eulerian Lagrangian Approach

The subject of this paper is numerical prediction of bird strike induced damage in real aeronautical structures using highly detailed finite element models and modern numerical approaches. Due to the complexity of today’s aeronautical structures, numerical damage prediction methods have to be able to take into account various failure and degradation models of different materials. A continuum damage mechanics approach has been employed to simulate failure initiation and damage evolution in unidirectional composite laminates. Hashin’s failure initiation criteria have been employed in order to be able to distinct between four ply failure modes. The problem of soft body impacts has been tackled by applying the Coupled Eulerian Lagrangian technique, thereby avoiding numerical difficulties associated with extensive mesh distortion. This improvement in impactor deformation modelling resulted in a more realistic behaviour of bird material during impact. Numerical geometrical and material nonlinear transient dynamic analyses have been performed using Abaqus/Explicit. The main focus of the work presented in this paper is the application of the damage prediction procedure in damage assessment of bird impact on a typical large airliner inboard flap structure. Due to the high cost of gas-gun testing of aircraft components, experimental testing on the real flap structure could not have been performed. In order to evaluate the accuracy of the presented method, the bird and composite damage model have been validated against experimental data available in the literature.

carbon fibres; damage mechanics; finite element analysis (FEA); impact behaviour; layered structures

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Podaci o izdanju

71 (4)

2011.

489-498

objavljeno

0266-3538

10.1016/j.compscitech.2010.12.024

Povezanost rada

Strojarstvo, Zrakoplovstvo, raketna i svemirska tehnika

Poveznice
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