Impact of finite element idealisation on the prediction of welded fuselage stiffened panel buckling

T Ekmekyapar, A Murphy, D Quinn, M Özakça

Research output: Contribution to journalArticlepeer-review

2 Citations (Scopus)
506 Downloads (Pure)

Abstract

Lap joints are widely used in the manufacture of stiffened panels and influence local panel sub-component stability, defining buckling unit dimensions and boundary conditions. Using the Finite Element method it is possible to model joints in great detail and predict panel buckling behaviour with accuracy. However, when modelling large panel structures such detailed analysis becomes computationally expensive. Moreover, the impact of local behaviour on global panel performance may reduce as the scale of the modelled structure increases. Thus this study presents coupled computational and experimental analysis, aimed at developing relationships between modelling fidelity and the size of the modelled structure, when the global static load to cause initial buckling is the required analysis output. Small, medium and large specimens representing welded lap-joined fuselage panel structure are examined. Two element types, shell and solid-shell, are employed to model each specimen, highlighting the impact of idealisation on the prediction of welded stiffened panel initial skin buckling.
Original languageEnglish
Pages (from-to)259-279
Number of pages21
JournalProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Volume230
Issue number2
Early online date18 Jun 2015
DOIs
Publication statusPublished - Feb 2016

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