Simulation of transient fluid–structure interaction in flapping-wing micro aerial vehicles

The objective of this study is to investigate aeroelastic phenomena occurring during airflow around flapping wings of a micro aerial vehicle (MAV) inspired by insect anatomy. A numerical model of the wing and the flow configuration was developed based on an experiment conducted at ESPCI Paris. Transient fluid–structure interaction (FSI) simulations were carried out in the Ansys environment, employing independent solvers for fluid flow (CFD) and structural deformation (FEM), coupled through the System Coupling module. The analysis focused on the role of wing compliance in thrust generation, with particular attention to the effects of flapping frequency and wing stiffness, determined by the thickness of the membrane forming the lifting surface. The results demonstrate a strong dependence of thrust generation on the degree of wing deformation, in good agreement with the experimental findings. These findings highlight the importance of structural flexibility in enhancing aerodynamic performance and provide practical guidelines for the design of efficient flapping-wing micro aerial vehicles.