Peridynamic Analysis of Impact Damage in Composite Laminates
Publication: Journal of Aerospace Engineering
Volume 21, Issue 3
Abstract
The traditional methods for analyzing deformation in structures attempt to solve the partial differential equations of the classical theory of continuum mechanics. Yet these equations, because they require the partial derivatives of displacement to be known throughout the region modeled, are in some ways unsuitable for the modeling of discontinuities caused by damage, in which these derivatives fail to exist. As a means of avoiding this limitation, the peridynamic model of solid mechanics has been developed for applications involving discontinuities. The objective of this method is to treat crack and fracture as just another type of deformation, rather than as pathology that requires special mathematical treatment. The peridynamic theory is based on integral equations so there is no problem in applying the equations across discontinuities. The peridynamic method has been applied successfully to damage and failure analysis in composites. It predicts in detail the delamination and matrix damage process in composite laminates due to low velocity impact, and the simulation results of damage area correlates very well with the experimental data.
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Acknowledgments
The writers wish to express their appreciations for access to the Columbia supercomputer at NASA Advanced Supercomputing Division (NAS) and technical assistance received from NASA in facilitating this work. Sandia is a multiprogram laboratory operated by Sandia Corporation, a Lockheed Martin Company, for the United States Department of Energy’s National Nuclear Security Administration under Contract DOEDE-AC04-94AL85000.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 21 • Issue 3 • July 2008
Pages: 187 - 194
Copyright
© 2008 ASCE.
History
Received: Dec 28, 2006
Accepted: Aug 13, 2007
Published online: Jul 1, 2008
Published in print: Jul 2008
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