ON THE REALIZATION OF GHM VISCOELASTIC MODEL TO THE TREATMENT OF THE AEROELASTIC STABILITY OF PLATES
André Garcia Cunha Filho1; Leandro de Souza Leão1; Antônio Marcos Gonçalves de Lima1; Maurício Vicente Donadon2
1 Universidade Federal de Uberlândia; 2 Instituto Tecnológico de Aeronáutica
doi:10.20906/CPS/COB-2015-1216
Resumo
This paper investigates the influence of viscoelastic damping in the aeroelastic stability boundary of flutter in aeronautical panels. Flutter in aeronautical panels is a kind of self-excited oscillation, which can occurs during supersonic flights. In the point of flutter occurrence, when the critical dynamic pressure is reached, the vibrations of the panel become unstable and increase significantly in time. As a result, it can leads to a fatigue failure of the considered structure. Thus, it becomes important to investigate the possibility of reducing the effects of the flutter in order to increase the reliability of the structures during service. In the present contribution, the Piston Theory is adopted to model the aerodynamic loading in supersonic condition. Aiming the reduction of the aeroelastic instabilities effects and the improvement of the structural dynamic performance, viscoelastic materials applied as constraining damping layers is an interesting strategy to be investigated, since very little effort has been carried-out on this subject. To do so, the Golla-Hughes-McTavish (GHM) parametric model is developed through the identification of the model parameters from the experimental data. Within this context, the finite element model of a three-layer sandwich plate element is presented. After exposing theoretical foundations of the methodology, the description of a numerical study on the flutter analysis of a rectangular plate treated by passive constraining layer damping is addressed.
Palavras-chave: Viscoelastic material; Passive control; Finite Elements; Flutter; Aeroelasticity