DBEM Crack Growth Simulation and Experimental Results for a Multi-Layer and Multi-Material Aeronautic Panel

Roberto G. Citarella; M. Silvestri; A. Apicella

doi:10.4028/www.scientific.net/KEM.324-325.1123

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DBEM Crack Growth Simulation and Experimental Results for a Multi-Layer and Multi-Material Aeronautic Panel
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HomeKey Engineering MaterialsKey Engineering Materials Vols. 324-325DBEM Crack Growth Simulation and Experimental...

DBEM Crack Growth Simulation and Experimental Results for a Multi-Layer and Multi-Material Aeronautic Panel

Abstract:

A special specimen was created cutting a rectangular notched area from the surrounding of the upper left corner of a wide body aircraft door. This part of the aircraft skin is made of different layers with variable thickness and material (titanium or aluminum). Then a fatigue traction load was applied and some notches were cut in the different layers in order to speed up the crack initiation and reproduce a realistic crack scenario. Such through cracks were monitored during their propagation along the specimen width, in order to have available for the simulation a realistic initial scenario and experimental propagation data useful for the correlation with the simulated crack path and growth rates. In particular an innovative DBEM modelling approach was devised, using a commercial code (BEASY), capable of explicitly modelling the different test article layers with their rivet connections even in a two-dimensional approach. The results of the simulation show a satisfactory correlation with the experimental crack path and growth rates even for such a complex problem: three different panels (one skin with two doublers), made of different materials, each one with a variable thickness and connected through numerous rivets (whose shear stiffness is taken into account for the simulation).

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Periodical:

Key Engineering Materials (Volumes 324-325)

Pages:

1123-1126

DOI:

https://doi.org/10.4028/www.scientific.net/KEM.324-325.1123

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Online since:

November 2006

Authors:

Roberto G. Citarella, M. Silvestri, A. Apicella

Keywords:

Damage Tolerance Test, DBEM, Wide Body Aircraft Door

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References

[1] M.H. Aliabadi, The Boundary Element Method (Vol. 2), Wiley and sons, Ltd, Chichester, (2002).

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[2] E. Armentani, R. Citarella, DBEM and FEM analysis on non-linear multiple crack propagation in an aeronautic doubler-skin assembly, International Journal of Fatigue 28 (2006) 598-608.

DOI: 10.1016/j.ijfatigue.2005.06.050

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