Graphical abstract

Finite element method is increasingly used in the analysis of aircraft structures, including Unmanned Aerial Vehicles (UAVs). The structural model used for finite element analysis however needs to be validated in order to ensure that it correctly represents the physical behaviour of the actual structure. In this work, a case study of a straight, unswept and untapered wing structure made of composite material subjected to aerodynamic loading was modelled and analysed using finite element method. Four-noded, reduced integration shell elements were used, with structural components attached by adhesive joints modelled using tied surface constraints. For the validation process an experimental set-up of the actual wing was loaded using sandbags to simulate the aerodynamic loads. The deflection of the wing at three key locations were obtained and compared between both methods. It was found that the difference between both results ranges between 0.3 % (at the tip) to 36.1 % (near the root, for small deflections)