Simplified Braiding through Integration Points Model for Triaxially Braided Composites
Publication: Journal of Aerospace Engineering
Volume 21, Issue 3
Abstract
A simplified methodology has been developed for modeling two-dimensional triaxially braided composite plates impacted by a soft projectile using an explicit nonlinear finite-element analysis code LS-DYNA. The fiber preform architecture is modeled using shell elements by incorporating the fiber preform architecture at the level of integration points. The soft projectile was modeled by an equation of state. An arbitrary Lagrangian–Eulerian formulation is used to resolve numerical problems caused by large deformation of the projectile. The computed results indicate that this numerical model is able to simulate a triaxially braided composite undergoing a ballistic impact effectively and accurately, including the deformation and failure with a reasonable level of computational efficiency.
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Acknowledgments
The writers would like to thank the NASA Glenn Research Center which funded part of this work through Grant No. NCC3-932 and for the scientific assistance from Dr. Gary D. Roberts.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 21 • Issue 3 • July 2008
Pages: 152 - 161
Copyright
© 2008 ASCE.
History
Received: Dec 4, 2006
Accepted: Aug 13, 2007
Published online: Jul 1, 2008
Published in print: Jul 2008
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