Buckling Deformation of Thin Layer Coverings of Small Curvatures Used in Aircraft Construction.
Tomasz Kopecki 1  
,  
Przemysław Mazurek 1  
,  
Tomasz Lis 1  
,  
 
 
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1
Rzeszów University of Technology, The Faculty of Mechanical Engineering and Aeronautiucs, Al. Powstańców Warszawy 8, 35-959 Rzeszów, Poland
2
University of the West of England, Department of Engineering Design and Mathematics, Coldharbour Lane, Stoke Gifford, Bristol BS16 1QY, UK
Publish date: 2018-03-01
 
Adv. Sci. Technol. Res. J. 2018; 12(1):293–302
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ABSTRACT:
This paper presents results of experimental and numerical analysis in terms of the finite element method of skin components of aircraft load bearing structures. The subject matter of the study was composite panels with stiffeners in the form of a regular grid of oriented longitudinal elements in accordance with the directions of the principal stresses in the covering. Analysis was conducted in the buckling states of structural deformation which showed that structures with stiffeners exhibit much more favorable behavior in buckling deformation states than in laminar structures. This translates into stress distributions and their gradients, which are milder in forms of stiffened structures.
CORRESPONDING AUTHOR:
Tomasz Kopecki   
Rzeszów University of Technology \nThe Faculty of Mechanical Engineering and Aeronautiucs, Al. Powstańców Warszawy 8, 35-959 Rzeszów, Poland