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Parametric damage tolerance design of metallic aeronautical stiffened panels

Published online by Cambridge University Press:  27 January 2016

G. Molinari ,
I. Meneghin ,
M. Melega  and
E. Troiani
G. Molinari*
Affiliation:
MaSTeR Lab – Material Structure Technology Research Laboratory, Faculty of Engineering, University of Bologna, Forli, Italy
I. Meneghin
Affiliation:
MaSTeR Lab – Material Structure Technology Research Laboratory, Faculty of Engineering, University of Bologna, Forli, Italy
M. Melega
Affiliation:
MaSTeR Lab – Material Structure Technology Research Laboratory, Faculty of Engineering, University of Bologna, Forli, Italy
E. Troiani
Affiliation:
MaSTeR Lab – Material Structure Technology Research Laboratory, Faculty of Engineering, University of Bologna, Forli, Italy
*
[email protected]
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Abstract

On the basis of well-known literature, an analytical tool named LEAF (linear elastic analysis of fracture) was developed by the authors to predict the damage tolerance (DT) proprieties of aeronautical stiffened panels. The tool is based on the linear elastic fracture mechanics and the displacement compatibility method. By means of LEAF, an extensive parametric analysis of stiffened panels, representative of typical aeronautical constructions, was performed to provide meaningful design guidelines. The effects of riveted, integral and adhesively bonded stringers on the fatigue crack propagation performances of stiffened panels were investigated, as well as the crack retarder contribution using metallic straps (named doublers) bonded in the middle of the stringers bays. The effect of both perfectly bonded and partially debonded doublers was investigated as well. Adhesively bonded stiffeners showed the best DT properties in comparison with riveted and integral ones. A great reduction of the skin crack growth propagation rate can be achieved with the adoption of additional doublers bonded between the stringers.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1182 , August 2012 , pp. 815 - 831
Copyright
Copyright © Royal Aeronautical Society 2012 

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