WIT Press


A Comparison Of Finite Element Buckling Analysis Predictions And Experimental Results For Riveted Aircraft Fuselage Panels

Price

Free (open access)

Paper DOI

10.2495/CMEM010281

Volume

30

Pages

10

Published

2001

Size

779 kb

Author(s)

K. Kofi, A. Gibson, M. Price

Abstract

A comparison of finite element buckling analysis predictions and experimental results for riveted aircraft fuselage panels K. Koffi, A. Gibson, M. Price School of Aeronautical Engineering, Queen's University Belfast, Northern Ireland, UK. Abstract The prediction of the behaviour and the ultimate load for compressively stiffened aircraft shell structures is a very important non-linear analysis problem for engineers. Herein, finite element analysis and experimental tests are carried out for the buckling of aircraft stiffened fuselage panels. The calculated finite element results for both flat and curved bulbed-T panels correlated well with the experimental results. A change of mode shape is observed for the curve panel, which is very imperfection sensitive. This study reveals that the finite element code used, ABAQUS is capable of modelling the behaviour of the buckling phenomenon for small aircraft fuselage panels. 1 Introduction Shell buckling problems have bee

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