Numerical model for the simulation of fixed wings aeroelastic response

Autor(es)

G. R. Benini ^[1] ; E. M. Belo ^[2] ; F. D. Marques ^[3]

Afiliação do(s) autor(es)

^[1] Universidade de São Paulo. Escola de Engenharia de São Carlos. Núcleo de Pesquisas em Aeronáutica - Brasil

^[2] Universidade de São Paulo. Escola de Engenharia de São Carlos. Núcleo de Pesquisas em Aeronáutica - Brasil

^[3] Universidade de São Paulo. Escola de Engenharia de São Carlos. Núcleo de Pesquisas em Aeronáutica - Brasil

• Tipo de documento: Artigo Científico
• Fonte: Journal of the Brazilian Society of Mechanical Sciences and Engineering; v. 26, n. 2, p. 129-136, 2004-06-00.

Resumo

A numerical model for the simulation of fixed wings aeroelastic response is presented. The methodology used in the work is to treat the aerodynamics and the structural dynamics separately and then couple them in the equations of motion. The dynamic characterization of the wing structure is done by the finite element method and the equations of motion are written in modal coordinates. The unsteady aerodynamic loads are predicted using the vortex lattice method. The exchange of information between the aerodynamic and structural meshes is done by the surface splines interpolation scheme, and the equations of motion are solved iteratively in the time domain, employing a predictor-corrector method. Numerical simulations are performed for a prototype aircraft wing. The aeroelastic response is represented by time histories of the modal coordinates for different airspeeds, and the flutter occurrence is verified when the time histories diverge (i.e. the amplitudes keep growing). Fast Fourier Transforms of these time histories show the coupling of frequencies typical of the flutter phenomenon. (AU)

• Processo FAPESP: 00/00361-3 - Aplicação do método de malha de vórtices não-estacionário na análise de flutter
• Beneficiário: Guilherme Ribeiro Begnini
• Modalidade de apoio: Bolsas no Brasil - Mestrado