Estudo comparativo do comportamento vibratório estrutural e aeroelástico de uma asa de aeronave de pequeno porte

Abstract

The increasing use of small aircraft, such as surveillance drones and agricultural platforms, has intensified the demand for lightweight, resistant structures with good dynamic performance. In this context, understanding the structural and dynamic behavior of wings is essential to ensure safety, stability, and aerodynamic efficiency. This work aims to perform the modeling, modal analysis, and structural validation of scaled-down aircraft wings for aeroelastic applications. The adopted methodology includes the development of a physical model based on NACA 4-digit airfoils, 3D modeling using CAD software, and numerical simulation of dynamic behavior through modal analysis using Siemens NX. Material properties were obtained from technical databases, and the natural vibration modes were compared to experimental data collected through impact tests and wind tunnel experiments, using piezoelectric sensors, accelerometers, and force transducers. Additionally, a computational model was implemented in GNU Octave to simulate the dynamic behavior of the wing based on the differential equations of a mass-spring-damper system. As a result, the natural frequencies and vibration modes of the structure were identified, allowing verification of consistency between numerical and experimental models. The validated structural model, even at reduced scale, provides important insights for the future development of more complex aeroelastic systems, particularly in applications where flutter and other dynamic instabilities pose risks to aircraft stability.