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 analyses, 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.
Impact of finite element idealisation on the prediction of welded fuselage stiffened panel buckling
2016
Article (Journal)
English
Impact of finite element idealisation on the prediction of welded fuselage stiffened panel buckling
SAGE Publications | 2016
|Non-linear idealisation error analysis of an aerospace stiffened panel loaded in compression
SAGE Publications | 2014
|Non-linear idealisation error analysis of an aerospace stiffened panel loaded in compression
Online Contents | 2014
|Damage Tolerance of Fuselage Welded Stiffened Panels
British Library Conference Proceedings | 2004
|POST-BUCKLING DESIGN ANALYSIS FOR STIFFENED HELICOPTER FUSELAGE ALUMINUM PANELS
British Library Conference Proceedings | 2019
|