Computational Modeling of Aeroelastic Vibrations in an Aircraft Wing under Turbulent Flow Using an Optimized Tuned Mass Damper

Resumo

This paper presents a computational study on the mitigation of aeroelastic vibrations in an aircraft wing, subjected to atmospheric turbulence, through the application of an optimized Tuned Mass Damper (TMD). The wing is modeled as a two-degree-of-freedom system, and the aerodynamic excitations are represented using discrete gust models derived from Hoblit’s methodology. The structural response is computed using the Newmark integration method, implemented in MATLAB. An optimization routine using the fmincon solver is developed to determine optimal TMD parameters (mass, stiffness, and damping) aimed at minimizing the wing’s vibration amplitudes. The effectiveness of the TMD is evaluated by comparing time-domain responses of the wing with and without the device. The results demonstrate that the optimized TMD significantly reduces vibrational amplitudes and enhances structural stability under turbulent flow conditions. The study reinforces the applicability of TMDs in aerospace structures and highlights the importance of combining numerical modeling with optimization techniques for vibration control.