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Active flutter suppression including uncertainties and using piezoelectric stack actuators

Grant number: 19/24729-6
Support type:Scholarships in Brazil - Doctorate
Effective date (Start): January 01, 2021
Effective date (End): February 28, 2023
Field of knowledge:Engineering - Mechanical Engineering - Mechanics of Solids
Principal researcher:Douglas Domingues Bueno
Grantee:Frederico Albuquerque Ribeiro
Home Institution: Faculdade de Engenharia (FEIS). Universidade Estadual Paulista (UNESP). Campus de Ilha Solteira. Ilha Solteira , SP, Brazil

Abstract

The effects associated to the aeroelastic phenomena define an important class of problems to be addressed during the aircraft design, especially because they can decrease the safety levels of aerial vehicles. Particularly, flutter stands out because it is a potentially catastrophic instability, which implies to well-defined requirements established by the aeronautical certification agencies for designing an aircraft. The commercial aircraft exhibits the flutter velocity out of its operational flight envelope. Moreover, active control systems have been developed by aviation companies and research centers around the world, and they have different levels of technological readiness. On the other hand, according to the literature, the inclusion of uncertainties on the flutter prediction is an important point to be considered. However, in context of active flutter control, the influence of uncertain parameters on the controller performance is a topic not explored in details by the scientific community, although it is very relevant to establish robust control system. Thus, this research comprises to develop a new robust active control methodology based on formulating the flutter problem considering structural uncertainties by linear matrix inequalities. It will be written a polytope in a convex space and an Affine Parameter model will be used to describe the uncertain aeroelastic system. Frequencies and damping ratios will be considered uncertain in a typical section defined by unsteady aerodynamics. Piezoelectric stack actuators will be included to apply the control force, and experimental wind tunnel tests will be performed to demonstrate the approach. (AU)

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