Nonlinear analysis and bifurcation characteristics of whirl flutter in unmanned aerial systems

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MetadadosDescriçãoIdioma
Autor(es): dc.contributorNew Mexico State University-
Autor(es): dc.contributorUniversidade Estadual Paulista (UNESP)-
Autor(es): dc.creatorQuintana, Anthony-
Autor(es): dc.creatorVasconcellos, Rui-
Autor(es): dc.creatorThroneberry, Glen-
Autor(es): dc.creatorAbdelkefi, Abdessattar-
Data de aceite: dc.date.accessioned2025-08-21T17:38:40Z-
Data de disponibilização: dc.date.available2025-08-21T17:38:40Z-
Data de envio: dc.date.issued2022-04-28-
Data de envio: dc.date.issued2022-04-28-
Data de envio: dc.date.issued2021-11-30-
Fonte completa do material: dc.identifierhttp://dx.doi.org/10.3390/drones5040122-
Fonte completa do material: dc.identifierhttp://hdl.handle.net/11449/222743-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/222743-
Descrição: dc.descriptionAerial drones have improved significantly over the recent decades with stronger and smaller motors, more powerful propellers, and overall optimization of systems. These improvements have consequently increased top speeds and improved a variety of performance aspects, along with introducing new structural challenges, such as whirl flutter. Whirl flutter is an aeroelastic instability that can be affected by structural or aerodynamic nonlinearities. This instability may affect the prediction of potentially dangerous behaviors. In this work, a nonlinear reduced-order model for a nacelle-rotor system, considering quasi-steady aerodynamics, is implemented. First, a parametric study for the linear system is performed to determine the main aerodynamic and structural characteristics that affect the onset of instability. Multiple polynomial nonlinearities in the two degrees of freedom nacelle-rotor model are tested to simulate possible structural nonlinear effects including symmetric cubic hardening nonlinearities for the pitch and yaw degrees of freedom; purely yaw nonlinearity; purely pitch nonlinearity; and a combination of quadratic, cubic, and fifth-order nonlinearities for both degrees of freedom. Results show that the presence of hardening structural nonlinearities introduces limit cycle oscillations to the system in the post-flutter regime. Moreover, it is demonstrated that the inclusion of quadratic nonlinearity introduces asymmetric oscillations and subcritical behavior, where large and potentially dangerous deformations can be reached before the predicted linear flutter speed.-
Descrição: dc.descriptionDepartment of Mechanical and Aerospace Engineering New Mexico State University-
Descrição: dc.descriptionCampus of São João da Boa Vista São Paulo State University (UNESP)-
Descrição: dc.descriptionCampus of São João da Boa Vista São Paulo State University (UNESP)-
Idioma: dc.languageen-
Relação: dc.relationDrones-
???dc.source???: dc.sourceScopus-
Palavras-chave: dc.subjectFluid-structure interaction-
Palavras-chave: dc.subjectNonlinear dynamics-
Palavras-chave: dc.subjectRotor-nacelle system-
Palavras-chave: dc.subjectUnmanned aerial systems-
Palavras-chave: dc.subjectWhirl flutter-
Título: dc.titleNonlinear analysis and bifurcation characteristics of whirl flutter in unmanned aerial systems-
Tipo de arquivo: dc.typelivro digital-
Aparece nas coleções:Repositório Institucional - Unesp

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