Bifurcation Analysis and Sticking Phenomenon for Unmanned Rotor-Nacelle Systems with the Presence of Multi-Segmented Structural Nonlinearity

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Autor(es): dc.contributorNew Mexico State University-
Autor(es): dc.contributorSandia National Laboratories-
Autor(es): dc.contributorUniversidade Estadual Paulista (UNESP)-
Autor(es): dc.creatorQuintana, Anthony-
Autor(es): dc.creatorSaunders, Brian Evan-
Autor(es): dc.creatorVasconcellos, Rui-
Autor(es): dc.creatorAbdelkefi, Abdessattar-
Data de aceite: dc.date.accessioned2025-08-21T23:27:35Z-
Data de disponibilização: dc.date.available2025-08-21T23:27:35Z-
Data de envio: dc.date.issued2025-04-29-
Data de envio: dc.date.issued2024-01-31-
Fonte completa do material: dc.identifierhttp://dx.doi.org/10.3390/drones8020059-
Fonte completa do material: dc.identifierhttps://hdl.handle.net/11449/304053-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/304053-
Descrição: dc.descriptionWhirl flutter is a phenomenon caused by an aeroelastic instability, causing oscillations to propagate in manned or unmanned rotor-nacelle type aircraft. Under the conditions where multi-segmented freeplay are present, complex behaviors can dominate these oscillations and can lead to disastrous consequences. This study investigates a rotor-nacelle system with multi-segmented stiffnesses with a freeplay gap to encompass the real-world influences of aircraft. The mathematical aerodynamics model considers a quasi-steady application of strip theory along each blade to outline the external forces being applied. A free-body diagram is then used to incorporate the structural stiffness and damping terms with multi-segmented freeplay considered in the structural stiffness matrix. Multiple structural responses of the defined system are investigated and characterized to determine the influence of varying symmetric and asymmetric multi-segmented stiffnesses with varying gap parameters, including a route to impact investigation. The findings are characterized using phase portraits, Poincaré maps, time histories, and basins of attraction. It is found that under these conditions, the structural influences can lead to aperiodic oscillations with the existence of grazing bifurcations. Furthermore, these results unveil that under certain conditions and high freestream velocities, the sticking phenomenon becomes apparent which is strongly dependent on the strength of the multi-segmented representation, its gap sizes, and its symmetry. Lastly, a route to impact study shows the strong coupled influence between pitch and yaw when asymmetric conditions are applied and the possible presence of grazing-sliding bifurcations. The numerical simulations performed in this study can form a basis for drone designers to create reliable rotor-nacelle systems resistant to whirl flutter caused by freeplay effects.-
Descrição: dc.descriptionNew Mexico Space Grant Consortium-
Descrição: dc.descriptionDepartment of Mechanical & Aerospace Engineering New Mexico State University-
Descrição: dc.descriptionSandia National Laboratories-
Descrição: dc.descriptionSão Paulo State University (UNESP), Campus of São João da Boa Vista-
Descrição: dc.descriptionSão Paulo State University (UNESP), Campus of São João da Boa Vista-
Idioma: dc.languageen-
Relação: dc.relationDrones-
???dc.source???: dc.sourceScopus-
Palavras-chave: dc.subjectbifurcation analysis-
Palavras-chave: dc.subjectfluid-structure interaction-
Palavras-chave: dc.subjectfreeplay nonlinearity-
Palavras-chave: dc.subjectmulti-segmented nonlinearity-
Palavras-chave: dc.subjectnonlinear dynamics-
Palavras-chave: dc.subjectrotor-nacelle-
Palavras-chave: dc.subjectunmanned aircraft-
Título: dc.titleBifurcation Analysis and Sticking Phenomenon for Unmanned Rotor-Nacelle Systems with the Presence of Multi-Segmented Structural Nonlinearity-
Tipo de arquivo: dc.typelivro digital-
Aparece nas coleções:Repositório Institucional - Unesp

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