Modelação por elementos finitos do comportamento estrutural de soluções compósitas para asa de planador/ultraleve
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2018-01-10
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A existência de mais de 130 pistas em Portugal e os baixos custos de manutenção têm tornado a aviação de recreio um desporto em crescendo, em terras lusitanas, fazendo um crescimento na procura e interesse no desenvolvimento e comercialização de novas aeronaves, cada vez mais inovadoras e procurando soluções de conceção cada vez mais eficientes e assentes em tecnologia elevada. Esta tese de mestrado teve como objetivo a análise computacional do comportamento da asa da aeronave em estudo, desenvolvida de raiz, destinada a assegurar o seu bom funcionamento em voo plano, com recurso a materiais compósitos laminados. A análise foi desenvolvida usando o método dos Elementos Finitos (MEF). Procedeu-se à avaliação do comportamento da asa com vista a validar a estrutura proposta, tendo por base forças de sustentação como referência. Esta primeira análise, enquadra apenas a aprovação de estrutura desenvolvida, sendo que posteriormente serão necessários estudos mais avançados, de modo, a contemplar forças de sustentação eventualmente medidas em modelos experimentais também suportadas pela asa, forças essas presentes em manobras realizadas pela aeronave, tais como o levantar, o aterrar e as próprias manobras. Para se proceder a esta avaliação, foi necessário obter a solução nodal do modelo computacional, sendo elas o campo de deslocamentos, campo de deformações e campo de tensões; esta última usada para avaliar a integração estrutural recorrendo a critérios de tensão. Estas Soluções vão permitir saber, se a asa suporta as forças que estão a atuar, bem como a identificação de pontos críticos, que possam comprometer a asa e consequentemente toda a aeronave. O estudo realizado à asa, reveste-se de grande importância, pois permite detetar possíveis imperfeições a nível de construção/design, conciliando as valências de duas áreas distintas, mas que se completam, como é o caso da Engenharia Estrutural e de Resistência dos Materiais.
The existence of more than 130 landing runways in Portugal and the minimal maintenance costs have made recreational aviation a growing sport in Lusitanian lands, increasing demand and interest in the development and commercialization of new, increasingly innovative aircraft, looking for design solutions that increasingly efficient and based on high technology. This master’s thesis aims a computational analysis of the behavior of the wing of the aircraft under study, developed from scratch, to ensure its smooth operation in plane flight, using laminated composites materials. The analysis was developed using the Finite Element Method (FEM). The behavior of the wing was evaluated in order to validate the proposed structure, based on sustaining forces as reference. This analysis only includes approval of a developed structure and later studies will be necessary, to contemplate forces possibly measured in experimental models also supported by the wing, forces present in maneuvers performed by the aircraft, such as lifting, the landing and the maneuvers themselves. In order to carry out this evaluation, was necessary to obtain the nodal solution of the computational model, being they the field of displacement, flield of deformations and field of tensions; the latter used to evaluate structural integration using stress criteria. These solutions will allow us to know if the wing supports the forces acting on them, as well as the identification of critical points that could compromise the wing and consequently all aircraft. The study carried out on the wing is of immense importance, since it allows to detect possible imperfections in construction/design, conciliating the valences of two distinct areas, but which are completed, as is the case of Structural Engineering and Strength of Materials.
The existence of more than 130 landing runways in Portugal and the minimal maintenance costs have made recreational aviation a growing sport in Lusitanian lands, increasing demand and interest in the development and commercialization of new, increasingly innovative aircraft, looking for design solutions that increasingly efficient and based on high technology. This master’s thesis aims a computational analysis of the behavior of the wing of the aircraft under study, developed from scratch, to ensure its smooth operation in plane flight, using laminated composites materials. The analysis was developed using the Finite Element Method (FEM). The behavior of the wing was evaluated in order to validate the proposed structure, based on sustaining forces as reference. This analysis only includes approval of a developed structure and later studies will be necessary, to contemplate forces possibly measured in experimental models also supported by the wing, forces present in maneuvers performed by the aircraft, such as lifting, the landing and the maneuvers themselves. In order to carry out this evaluation, was necessary to obtain the nodal solution of the computational model, being they the field of displacement, flield of deformations and field of tensions; the latter used to evaluate structural integration using stress criteria. These solutions will allow us to know if the wing supports the forces acting on them, as well as the identification of critical points that could compromise the wing and consequently all aircraft. The study carried out on the wing is of immense importance, since it allows to detect possible imperfections in construction/design, conciliating the valences of two distinct areas, but which are completed, as is the case of Structural Engineering and Strength of Materials.
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Dissertação de Mestrado em Engenharia Mecânica