Publication: Finite element analysis of aeronautical composite laminated panel (secondary structure)
Date
2009-04-01
Authors
Bazal Ahmad, Mohammad Muzzammil
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Abstract
Stress analysis of a honeycomb sandwich panel was studied in this project . Software packages, based on the Finite Element Method (FEM) was used to model and analyze the panel model. A uniform distributed pressure was applied to the panel in performing the structural analysis. The result obtained in the analysis were Von Mises Stress, maximum shear stress and deformation at the honeycomb sandwich panel. The type of analysis used was linear static.. From the results shown, the ply stacking sequences and material used for the facing can influence the stress distribution and deformation at honeycomb sandwich panel.