Hybrid-electric aircraft: conceptual design, structural and aeroelastic analyses

Silva, Higor Luis; Gil, Alexandre Acerra

Please use this identifier to cite or link to this item: https://repositorio.ufu.br/handle/123456789/20599

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DC Field	Value	Language
dc.creator	Silva, Higor Luis	-
dc.creator	Gil, Alexandre Acerra	-
dc.date.accessioned	2018-02-05T13:42:48Z	-
dc.date.available	2018-02-05T13:42:48Z	-
dc.date.issued	2017-12-21	-
dc.identifier.citation	SILVA, Higor Luis, GIL, Alexandre Acerra. Hybrid-electric aircraft: conceptual design, structural and aeroelastic analyses. 2017. 123 f. Trabalho de Conclusão de Curso (Graduação em Engenharia Aeronáutica) - Universidade Federal de Uberlândia, Uberlândia, 2017.	pt_BR
dc.identifier.uri	https://repositorio.ufu.br/handle/123456789/20599	-
dc.description.sponsorship	UFU - Universidade Federal de Uberlândia	pt_BR
dc.language	eng	pt_BR
dc.publisher	Universidade Federal de Uberlândia	pt_BR
dc.rights	Acesso Aberto	pt_BR
dc.subject	Aeronautical Design	pt_BR
dc.subject	Hybrid Aircraft	pt_BR
dc.subject	Optimization	pt_BR
dc.subject	Aerodynamic Loads	pt_BR
dc.subject	Aeronautical structures	pt_BR
dc.subject	Aeroelasticity	pt_BR
dc.subject	Projeto Aeronáutico	pt_BR
dc.subject	Aeronave híbrida	pt_BR
dc.subject	Otimização	pt_BR
dc.subject	Cargas Aerodinâmicas	pt_BR
dc.subject	Estruturas Aeronáuticas	pt_BR
dc.subject	Aeroelasticidade	pt_BR
dc.title	Hybrid-electric aircraft: conceptual design, structural and aeroelastic analyses	pt_BR
dc.type	Trabalho de Conclusão de Curso	pt_BR
dc.contributor.advisor1	Guimarães, Thiago Augusto Machado	-
dc.contributor.referee1	Sanches, Leonardo	-
dc.contributor.referee2	Morais, Tobias Souza	-
dc.description.degreename	Trabalho de Conclusão de Curso (Graduação)	pt_BR
dc.description.resumo	This work presents the conceptual design of two hybrid aircrafts (four and six passengers) and the structural and aeroelastic analyses for the wing and empennages. The requirements in the conceptual phase were established by the aeronautical design competition held annually by the American Institute of Aeronautics and Astronautics (AIAA). The initial characteristics and geometries of a conventional aircraft were estimated through the study of historical trends. Then, the hybridization characteristics were evaluated using the series architecture, which affects mainly the range equations and the definition of the propulsive system elements that better fit the project, e. g., the internal combustion engine and batteries. To explore the multidisciplinary characteristics of the aircraft development, it was implemented an optimization procedure based on a genetic algorithm fully integrated with an aerodynamic module with performance and stability constraints, searching for the best values of the geometrical design variables. After finishing the conceptual design, the structural evaluation of wing and empennages (horizontal and vertical) was performed considering only static loads, but the failure index and the buckling instability were checked. The evaluated loads were extracted from aerodynamic models at the extreme conditions of flight envelope presented in V-n diagrams. First, the structural components were defined in aluminum 7050-T651 and later using composite material, specifically the carbon-epoxy Hexcel 8552 NMS 128/2. Additionally, only the aeroelastic analysis for the wing was evaluated, because in this work the fuselage analysis wasn't done. The results showed no flutter speed and no divergence phenomena within the aircraft's flight envelope, which is justified by the torsional rigidity obtained in the main box structure.	pt_BR
dc.publisher.country	Brasil	pt_BR
dc.publisher.course	Engenharia Aeronáutica	pt_BR
dc.sizeorduration	123	pt_BR
dc.subject.cnpq	CNPQ::ENGENHARIAS::ENGENHARIA AEROESPACIAL::ESTRUTURAS AEROESPACIAIS	pt_BR
Appears in Collections:	TCC - Engenharia Aeronáutica

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