Análise modal e estática aeroelástica de uma semi-asa alterando a pressão dinâmica e ângulo de ataque via NASTRAN

Abstract

Modern aircraft have benefited from the use of more efficient, in terms of weight, and flexible wing structures to better adapt to the aerodynamic loads present during flight. High speeds and different values of angle of attack change the aerodynamic loading, causing different deformations or resonant vibrations that can damage the structural integrity of the wing. Therefore, studies in the field of aeroelasticity are necessary to guarantee positive safety margins during the structural design stages of a wing. This work focuses on the application of knowledge and analysis techniques in finite elements for aeroelastic modal and static analyses, with an emphasis on the NASTRAN software, for a half-wing. Developed in the 1960s by NASA in collaboration with the aerospace industry, NASTRAN represented a milestone in aerospace engineering and its creation was in response to the growing need to analyze and design complex structures. Among the existing solutions in NASTRAN, this work focuses on the modal solution, identifying the first natural vibration frequencies of the numerical model of the half-wing, and on the aeroelastic static solution whose function is to evaluate the final displacement at the tip of the half-wing in due to the variables angle of attack and dynamic pressure, verifying their influence on the displacement profile.