Methodology for Impact Modeling of Triaxial Braided Composites Using Shell Elements
Publication: Journal of Aerospace Engineering
Volume 22, Issue 3
Abstract
In this paper, a two-dimensional triaxial braided composite model has been studied using the nonlinear explicit finite-element code LSDYNA. The unit cell consists of six subcells and material properties associated with shell element integration point simulate braiding architecture. The local material properties were selected by correlation of the global behavior of a coupon model with static specimen tests. By changing subcell size and orientation angle at integration points, different braids architectures were obtained. Panel ballistic models were performed with benefits of computation efficiency of shell elements. Mechanical properties, panel impact threshold velocities, and failure initiations for braids with bias angles of 75, 60, 45, and 30° were studied. Boundary effects were also investigated.
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Acknowledgments
The writers acknowledge support of the National Aeronautics and Space AdministrationNASA.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 22 • Issue 3 • July 2009
Pages: 310 - 317
Copyright
© 2009 ASCE.
History
Received: Jul 15, 2008
Accepted: Jan 22, 2009
Published online: Jun 15, 2009
Published in print: Jul 2009
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