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Abstract(s)
No âmbito de tentar aumentar a disponibilidade do ciclo de vida das aeronaves e sua eficiência, as empresas de construção procuram desenvolver métodos e soluções para retirarem um maior desempenho da aeronave garantindo os níveis de segurança elevados. Assim, é necessário precaver situações anormais, simulando e solucionando qualquer tipo de futuros problemas e ao mesmo tempo otimizar toda a estrutura da aeronave.
Atendendo a estas circunstâncias, o presente trabalho consiste no desenvolvimento de um modelo estrutural, mais precisamente na asa do planador Crossover, para uma simulação computacional de todos os esforços presentes na estrutura, e identificação de zonas críticas para as diferentes fases de voo, como por exemplo as zonas de montagem da asa.
Uma revisão bibliográfica sobre o estudo de vários autores na área foi feita para ajudar o cálculo de todos os tipos de carregamentos e esforços existentes na asa da aeronave, obtendo uma plataforma de otimização estrutural dos planadores. Verificou-se diversas formas de construção de uma asa de um planador e é principalmente constituída por compósitos. O desenvolvimento destes compósitos e suas propriedades foi um grande passo para reduzir o peso de uma aeronave e ao mesmo tempo suportar carregamentos, que outros materiais como o alumínio e o aço suportariam.
Neste trabalho são estudados diferentes cargas na asa da aeronave e, tentou-se simular computacionalmente todas elas. Foram obtidas com o auxílio do software XFLR5 e posteriormente através de ferramentas de cálculo para obtenção de todos os esforços. Com os valores dos carregamentos desenvolve-se o melhor modelo estrutural de forma a retirar a melhor eficiência e peso reduzido, de forma a suportar todas as cargas.
Para uma melhor compreensão do modelo estrutural, foi realizado o desenho 3D em CATIA V5 com as devidas dimensões. O modelo em elementos finitos é realizado no software Ansys de forma a garantir os cálculos efetuados analiticamente.
In a context of trying to increase the cycle of life of the aircrafts and its efficiency, the construction companies seek to develop methods and solutions so that the aircraft can reach a higher performance and maintain the high levels of security. Thus, it is necessary to avoid abnormal situations, by simulating and solving any future problems while optimizing the entire structure of the aircraft. Given these circunstances, the present work consist in the development of a structural model, specifically the Crossover glider wing, for a computer simulation of all efforts present in the structure, and identification of critical areas for different flight phases, such as the assembly areas of the wing. A literature review about the study of various authors in the field was made, as to estimate all types of loads and efforts on the aircraft’s wing, where we obtained a structural optimization platform of the gliders. There are several ways to build a wing of a glider and its nomenclature is mainly made up of composites. The development of these composites and their properties was a major step towards reducing the weight of an aircraft while ensuring loads, that other materials, such as aluminum and steel, would support those efforts. In the present work is studied different loads on the aircraft wing and, it is also tried to simulate computationally all of them. They were obtained with the help of software XFLR5 and afterwards through calculation tools to obtain all efforts. The load values allows to conceive a better structural model in order to obtain the best efficiency, with low weight and capable of withstand all loads. For a better understanding of the structural model, it was sketched in CATIA V5 a 3D design with appropriate dimensions. The finite element model is carried out in ANSYS software to ensure the calculations performed analytically.
In a context of trying to increase the cycle of life of the aircrafts and its efficiency, the construction companies seek to develop methods and solutions so that the aircraft can reach a higher performance and maintain the high levels of security. Thus, it is necessary to avoid abnormal situations, by simulating and solving any future problems while optimizing the entire structure of the aircraft. Given these circunstances, the present work consist in the development of a structural model, specifically the Crossover glider wing, for a computer simulation of all efforts present in the structure, and identification of critical areas for different flight phases, such as the assembly areas of the wing. A literature review about the study of various authors in the field was made, as to estimate all types of loads and efforts on the aircraft’s wing, where we obtained a structural optimization platform of the gliders. There are several ways to build a wing of a glider and its nomenclature is mainly made up of composites. The development of these composites and their properties was a major step towards reducing the weight of an aircraft while ensuring loads, that other materials, such as aluminum and steel, would support those efforts. In the present work is studied different loads on the aircraft wing and, it is also tried to simulate computationally all of them. They were obtained with the help of software XFLR5 and afterwards through calculation tools to obtain all efforts. The load values allows to conceive a better structural model in order to obtain the best efficiency, with low weight and capable of withstand all loads. For a better understanding of the structural model, it was sketched in CATIA V5 a 3D design with appropriate dimensions. The finite element model is carried out in ANSYS software to ensure the calculations performed analytically.
Description
Keywords
Cargas Deformações Forças de Corte Longarinas Materiais Compósitos Modelo Estrutural Momentos Planador Tensões Tensores de Inercia