Dynamic Response of a MorphingWing

Abstract

This work aims to develope a computational framework to predict the dynamic response of a morphing wing. Unlike conventional aerodynamic surfaces, the investigated wing has the capability of continuously morphing its trailing edge shape in order to improve the wing aerodynamic performance. The computational tool here developed incorporates a structural wing linear model whose dynamics are coupled with the unsteady aerodynamics generated by the wing interaction with an incompressible airflow. The wing equations of motion are derived from the theory of thin plates, while the airflow dynamics are described through an unsteady formulation and solved by the vortex lattice method (VLM). The fluid-structure interaction is then obtained by performing iterative simulation loops in which, starting from a reference wing and airflow configuration, the mechanical unknowns (i.e., the wing deflections and velocities) are used as input to modify the reference geometry of the aerodynamic surface and thus to modify accordingly the airflow dynamics around it. This allows the determination of the equivalent aerodynamic loads acting on the wing and the calculation of its dynamic response. The critical airflow speed leading to the flutter instability is evaluated for several trailing edge shapes of the morphing wing and compared with the critical speed attained in the unmorphed case.