In-plane and buckling analysis of variable angle tow composites

Detalhes bibliográficos
Ano de defesa: 2021
Autor(a) principal: Diego Magela Lemos
Orientador(a): Não Informado pela instituição
Banca de defesa: Não Informado pela instituição
Tipo de documento: Dissertação
Tipo de acesso: Acesso aberto
Idioma: eng
Instituição de defesa: Universidade Federal de Minas Gerais
Brasil
ENG - DEPARTAMENTO DE ENGENHARIA ESTRUTURAS
Programa de Pós-Graduação em Engenharia de Estruturas
UFMG
Programa de Pós-Graduação: Não Informado pela instituição
Departamento: Não Informado pela instituição
País: Não Informado pela instituição
Palavras-chave em Português:
Link de acesso: http://hdl.handle.net/1843/37995
Resumo: Advances in manufacturing techniques have allowed more flexibility to the design and new possibilities to apply composites materials in lightweight structures. Novel techniques such as the automated fiber placement allow the fibers to follow curvilinear paths, making possible laminate properties that vary within the laminate plane. These type of laminates are known as variable stiffness laminates or variable angle tow. In this work, the in-plane and buckling response of composite panels with variable stiffness through a spatially varying fiber orientation has been analyzed for two different boundary conditions. This work compares the outcomes of in-plane stress and critical buckling load for linear cubic fiber angle considering four aspect ratios. Manufacturing constraint has been considered in the analysis of the laminates. The finite element method has been applied to solve the system elliptic partial differential equations that govern the in-plane behavior of these panels. The Ritz method has been used to find the buckling loads for the variable stiffness panels. Results for four different aspects ratios are presented. Improvements in the buckling load of up to 18% over linear fiber angle variation were found.