Active Flutter suppression including uncertainties

• Ano de defesa: 2023
• Autor(a) principal: Ribeiro, Frederico Albuquerque
• Tipo de documento: Tese
• Tipo de acesso: Acesso aberto
• Idioma: eng
• Instituição de defesa: Universidade Estadual Paulista (Unesp)
• Palavras-chave em Português: Aeroelasticity; Flutter; Active Flutter suppression; Uncertain aeroelastic system; Linear matrix inequalities; Piezoelectric actuator; Aeroelasticidade; Supressão ativa de flutter; Sistema aeroelástico Incerto; Desigualdades matriciais lineares; Atuadores piezoelétricos
• Link de acesso: https://hdl.handle.net/11449/252756

The effects associated with aeroelastic phenomena constitute an important class of problems involved in aircraft design, especially because they can compromise the safety of air vehicles. In particular, flutter stands out as a potentially catastrophic instability, with design requirements established by certification agencies to ensure the development of air vehicles. In general, commercial aircraft have flutter speed outside the operational flight envelope. On the other hand, there are active control systems being developed, with different levels of technological readiness, around the world, by companies in the aeronautical sector and research centers. However, studies that evaluate how tolerant such active flutter suppression systems are to the presence of uncertainties in the physical properties of aircraft are still embryonic, although this understanding is fundamental, especially for practical applications in flight envelope. Thus, this thesis comprises the development of an evaluation method for unsteady aerodynamic approximation. Parametric uncertainty flutter analysis through LMI-based techniques. Active flutter suppression of uncertain aeroelastic system with piezoelectric actuators and the limit cycle oscilation with uncertain freeplay. The methodology will be based on the formulation of convex spaces and the solution of controllers through Linear Matrix Inequalities (LMI). A typical section with unsteady aerodynamics will be considered, with uncertain airspeed, structural frequencies and actuation system, described parametric affine model. The results shows a valitation of the proposed control design with wind tunnel test results. The main ideia is to proposes LMIs analysis methodology and control design to as an alternative to classical solutions for aeroelastic systems.