Structural analysis of a transport aircraft wing

Abstract

In this study the procedures of structural analysis of a typical transport aircraft wing has been followed. The wing model has been drawn using CATIA® V5; this model consists of several structural components such as spars, ribs and skin. The model has been exported into structural analysis software ANSYS® 2016. Stresses, strains, deformations and safety factors were obtained for the model. It is found that the obtained stresses caused by the aerodynamic loads on the wing are within the design structural limits where the failure by yield or buckling has not been occurred.