Wing loading test is one of the most important milestones a manufacturer has to pass during the aircraft certification process. In this context, finite element simulations can arise as an excellent tool to reduce time in design processes prior to test, as well as to serve on posteriori analysis. Due to utmost importance of wing loading test the structural model requires consideration of the nonlinear characteristics associated to the wing. This work presents the basis of both finite element method and nonlinear continuum analysis to afterwards implement them in a collaborative software formed by other four students and called FEM-MAT-OO. First, the finite element method is introduced within the framework of linear elasticity. Then, the development of continuum kinematics, stress and equilibrium equations is followed by considering hyperelasticity as the material constitutive model. After a discussion Saint Venant model arises as the suitable for the wing model. Once the set of equations is obtained a linearization phase occurs before the final discretization. The solution is achieved by using the Newton-Raphson scheme. The computer implementation is based on test-driven development and it grows concur-rently with the results. Cases with geometries of increasingly complexity are solved until reaching the wing case.

The goal of the Master thesis is to understang the following aspects:Finite element method Linear elasticity problemLarge deformation problem