State-Space modeling and active aeroelastic control of a typical airfoil section with three degrees of freedom.

Detalhes bibliográficos
Ano de defesa: 2008
Autor(a) principal: Felipe Augusto Sviaghin Ferri
Orientador(a): Não Informado pela instituição
Banca de defesa: Não Informado pela instituição
Tipo de documento: Dissertação
Tipo de acesso: Acesso aberto
Idioma: eng
Instituição de defesa: Instituto Tecnológico de Aeronáutica
Programa de Pós-Graduação: Não Informado pela instituição
Departamento: Não Informado pela instituição
País: Não Informado pela instituição
Palavras-chave em Português:
Link de acesso: http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1198
Resumo: This dissertation presents a detailed analysis of a typical section model with three degrees of freedom. This is a classic model used for the study of basic aerodynamic and aeroelastic phenomena. The equations of motion are derived and discussed. The equations for the aerodynamic loads induced by arbitrary motion of the typical section and by arbitrary shaped wind gusts are derived. These equations are converted into a state-space formulation by replacing the nonlinear Wagner and Küssner functions by rational function approximations, that are Laplace transformable. The equations of motion, the aerodynamic loads and the gust loads equations and the Dryden model for stochastic wind gusts, all of these in the state-space form, are joined in a unified state-space model. This model is then used to perform simulations to evaluate the dynamic response and stability of the typical section. A control structure is presented, along with procedures for calculating the gains for this control structure by minimizing three different performance indices: linear quadratic, time weighted linear quadratic and H-infinity-norm. An angle of attack tracker is designed using these performance indices and its response to control input and gust disturbances is presented and discussed.