Delamination Characteristics around Hole in Laminates with Softening Strip
Publication: Journal of Aerospace Engineering
Volume 6, Issue 2
Abstract
Graphite/epoxy laminates with and without a softening strip around a hole were investigated. The softening strip is a portion of the graphite critical ply, which is replaced by a glass/epoxy composite. Analysis was conducted with finite element methods: The in‐plane stress distribution was found using a planform two‐dimensional model and interlaminar stress distributions around a hole were obtained from a through‐thickness quasi‐three‐dimensional model. The variation of strain‐energy release rate for a delamination occurring at the critical interface was investigated. The finite element results indicate that the inplane and interlaminar stress distributions, as well as the strain‐energy release rates, are significantly reduced for laminates with a softening strip.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 6 • Issue 2 • April 1993
Pages: 199 - 215
Copyright
Copyright © 1993 American Society of Civil Engineers.
History
Received: Aug 19, 1991
Published online: Apr 1, 1993
Published in print: Apr 1993
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