Compressive Behavior of Multiply Delaminated Composite Laminates Part 2: Finite Element Analysis

Postbuckling behavior of rectangular composite plates with multiple circular delaminations is studied numerically using finite element analysis. Embedded circular delaminations an placed at regular intervals in the thickness direction at the plate center. The plate is fixed along its loading edges a...

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Bibliographic Details
Published in:AIAA journal 1998-07, Vol.36 (7), p.1286-1290
Main Authors: Suemasu, Hiroshi, Kumagai, Tatsuya
Format: Article
Language:English
Subjects:
Aircraft
Buckling
Composite materials
Exact sciences and technology
Finite element analysis
Fundamental areas of phenomenology (including applications)
Mechanical engineering
Physics
Solid mechanics
Static buckling and instability
Structural and continuum mechanics
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Summary:Postbuckling behavior of rectangular composite plates with multiple circular delaminations is studied numerically using finite element analysis. Embedded circular delaminations an placed at regular intervals in the thickness direction at the plate center. The plate is fixed along its loading edges and simply supported at its side edges. The three-dimensional block element 6 adopted to accurately obtain distributions of energy release rates GI, GII, and GIII, along the delamination fronts based on the virtual crack closure technique.
ISSN:0001-1452
1533-385X
DOI:10.2514/2.512