Failure mechanism of composite laminates with different size multiple delaminations subjected to compressive load-Reference-Cited by-同舟云学术

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Failure mechanism of composite laminates with different size multiple delaminations subjected to compressive load

Published:2000-04-03 Issue: Volume: Page:
ISSN:
Container-title:41st Structures, Structural Dynamics, and Materials Conference and Exhibit
language:
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Author:

Suemasu Hiroshi¹,Wakabayashi Hidetoshi¹

Affiliation:

1. Sophia Univ., Tokyo, Japan

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2000-1402

Reference10 articles.

1. Finite Element Analysis of Compressive Behaviors and Delamination Crack Instability of Multiply Delaminated Cross-Ply Laminates.

2. Strain-Energy Release Rate Analysis of Plates with Postbuckled Delaminations

3. A mechanical model for the buckling of unilaterally constrained rectangular plates

4. Efficient modeling of postbuckling delamination growth in composite laminates using plate elements

5. Some experimental findings in compression-after-impact (CAI) tests of CF/PEEK (APC-2) and conventional CF/epoxy flat plates

Cited by 2 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Investigation for the Reduction of In-plane Compressive Strength in Preconditioned Thin Composite Panels;Journal of Composite Materials;2005-03

2. Buckling behaviour and delamination growth in impacted composite specimens under fatigue load: an experimental study;Composites Science and Technology;2001-10

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