Análise em elementos finitos de projetos em fibra de carbono com valores de propriedades obtidas experimentalmente
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Data
2018-01-22
Autores
Mendes, Cláudia Luisa
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Universidade Estadual Paulista (Unesp)
Resumo
A exigência dos requisitos de desempenho em estruturas aeroespaciais, navais e automobilísticas vem proporcionando o desenvolvimento de novos materiais, bem como de novas técnicas de fabricação. Normalmente, elevados valores de resistência e rigidez específicas aliados ao baixo peso específico são procurados em projetos estruturais, obtendo-se soluções por meio da utilização de materiais compósitos, particularmente polímeros termo fixos dotados de reforços fibrosos. O entendimento do que é um material composto é necessário, pois trata-se da combinação de no mínimo dois materiais com fase heterogênea, que separados possuem propriedades e características distintas e sua combinação é desejada para a confecção de um material único, com a conformidade das propriedades de ambos os materiais, tornando atrativa sua aplicação. Para otimizar a confecção do laminado em cada projeto, é imprescindível a utilização do modelo em elementos finitos para a obtenção da faixa de tensões, pelo método do critério de falha, sofrida pela amostra e assim obter-se a melhor propriedade mecânica para o seu uso. O presente trabalho tem por objetivo elaborar um estudo comparativo entre os resultados obtidos experimentalmente e os obtidos virtualmente, para validar o uso do software de elementos finitos na execução de um projeto utilizando como material principal o compósito estrutural de fibra de carbono com resina epóxi. Para isso, foram realizados ensaios para obter as propriedades mecânicas, e a melhor temperatura de cura da resina SQ 2004. Posteriormente foram feitos laminados de fibra de carbono com esta resina e extraído suas propriedades mecânicas. Por fim, utilizou-se as propriedades obtidas como entrada do software de elementos finitos e comparou-se o resultado através de três critérios de falha: Hill, Hoffman e Tsai-Wu. Como resultado, constata-se que o critério de falha de Tsai-Wu é o mais indicado para o cálculo da integridade estrutural de um componente de compósito que utiliza fibra de carbono.
The demand of requirements in performance of aerospace, naval and automotive structures has been providing the development of new materials as well as new manufacturing techniques. High values of specific strength and stiffness combined with low specific gravity are usually sought in blade designs for wind generators and other components of these systems, obtaining solutions using composite materials, particularly thermoset polymers endowed with fibrous reinforcements. The understanding of what is a composite material is necessary because it is a combination of at least two materials with heterogeneous phase, which have different properties and characteristics and their combination is desired for the manufacture of a single material with conformity of the properties of both materials, making its application attractive. To optimize the preparation of the laminate in each project, it is essential to use the finite element model to obtain the stress range, by the failure criterion method, and to obtain the best mechanical property for its use. The present work has the objective of elaborating a comparative study between the results obtained experimentally and those obtained virtually to validate the use of finite element software in the execution of a project using the structural material of carbon fiber with epoxy resin as its main material. For this, tests were carried out to obtain the mechanical properties and the best curing temperature of the SQ 2004 resin. Later, carbon fiber laminates were made with this resin and extracted its mechanical properties. Finally, the obtained properties were used as inputs to the finite element software and the result was compared through three failure criteria: Hill, Hoffman and Tsai-Wu. It is concluded that the Tsai-Wu failure criterion is the most suitable for calculating the structural integrity of a composite component using carbon fiber.
The demand of requirements in performance of aerospace, naval and automotive structures has been providing the development of new materials as well as new manufacturing techniques. High values of specific strength and stiffness combined with low specific gravity are usually sought in blade designs for wind generators and other components of these systems, obtaining solutions using composite materials, particularly thermoset polymers endowed with fibrous reinforcements. The understanding of what is a composite material is necessary because it is a combination of at least two materials with heterogeneous phase, which have different properties and characteristics and their combination is desired for the manufacture of a single material with conformity of the properties of both materials, making its application attractive. To optimize the preparation of the laminate in each project, it is essential to use the finite element model to obtain the stress range, by the failure criterion method, and to obtain the best mechanical property for its use. The present work has the objective of elaborating a comparative study between the results obtained experimentally and those obtained virtually to validate the use of finite element software in the execution of a project using the structural material of carbon fiber with epoxy resin as its main material. For this, tests were carried out to obtain the mechanical properties and the best curing temperature of the SQ 2004 resin. Later, carbon fiber laminates were made with this resin and extracted its mechanical properties. Finally, the obtained properties were used as inputs to the finite element software and the result was compared through three failure criteria: Hill, Hoffman and Tsai-Wu. It is concluded that the Tsai-Wu failure criterion is the most suitable for calculating the structural integrity of a composite component using carbon fiber.
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Palavras-chave
Fibra de carbono, Compósitos, Laminados, Elementos finitos, Critério de falha, Carbon fiber, Composites, Laminates, Finite elements, Failure criterion