Aeroelastic Analysis through Non-Linear Beam Finite Elements with Bending-Torsion Coupling Formulation

This research paper presents a procedure for static aeroelastic analysis of high aspect-ratio composite wings. The structural analysis is performed through the finite element method coupled with an aerodynamic analysis based on the vortex lattice method. The finite element model is obtained with beam finite elements with bending-torsion coupling formulation, which allows to consider the material coupling given by oriented anisotropic material. An advanced formulation of the same beam element can be used to consider geometric non-linearities. An iterative procedure computes the aerodynamic loads acting on the initially undeformed structures, then the obtained deformation is used to compute the aerodynamic loads for the deformed configuration until convergence. The aeroelastic analysis can be repeated for different speeds to find the divergence speed. This procedure has been tested on previously published analytical and experimental results on composite structures with different layups showing good accordance. Moreover, curvilinear lamination has been considered for the analysis to show the effects on the static aeroelastic performance.