Variable-stiffness composite panels: Buckling and first-ply failure improvements over straight-fibre laminates

• Tipo: Artigo em Revista Científica Internacional
• Data: 2008

Autores

Lopes, CS (Autor) Outra; Gurdal, Z (Autor) Outra; Camanho, PP (Autor) FEUP

Revista

Título: Computers and Structures

Vol. 86

Páginas: 897-907

ISSN: 0045-7949

Editora: Elsevier

Indexação

ISI Web of Knowledge - 150 Citações

Scopus - 216 Citações

Classificação Científica

FOS: Ciências da engenharia e tecnologias > Engenharia civil

Outras Informações

ID Authenticus: P-003-ZKH

DOI: 10.1016/j.compstruc.2007.04.016

Abstract (EN): One of the primary advantages of using fibre-reinforced laminated composites in structural design is the ability to change the stiffness and strength properties of the laminate by designing the laminate stacking sequence in order to improve its performance. This procedure is typically referred to as laminate tailoring. Traditionally, tailoring is done by keeping the fibre orientation angle within each layer constant throughout a structural component. Allowing the fibres to follow curvilinear paths within the plane of the laminates constitutes all advanced tailoring option that can lead to modification of load paths within the laminate to result in more favourable stress distributions and improve the laminate performance. Based on numerical simulations, the present work demonstrates the advantages of variable-stiffness over straight-fibre laminates in terms of compressive buckling and first-ply failure. A physically based set of failure criteria, able to predict the various modes of failure of a composite laminated structure, is implemented in finite element models of straight and variable-stiffness panels under compression. Non-linear analyses are carried out to simulate first-ply failure in the postbuckling regime.

Idioma: Inglês

Tipo (Avaliação Docente): Científica

Nº de páginas: 11