Buckling Mode Transition in Composite Panels under Different Stiffening Conditions

DOI

10.2991/ame-17.2017.48How to use a DOI?

Keywords

Composite, Stiffened panel, Post-buckling, Buckling mode transition.

Abstract

Two stiffened composite panel configurations which were designed with the same skin but different T-shape stiffeners were took into consideration and loaded in uniaxial compression to collapse. Comparison were made in terms of buckling mode, structural stiffness and failure mode. Scale factors of the first and second modes were predicted employing a deduced energy method, and were implemented in the post-buckling analysis, which was performed in a commercial FEM code ABAQUS. Experimentally and numerically, buckling mode transition was observed merely in the panel with lighter stiffeners. A good agreement between simulation and test validates the prediction method and indicates that a higher stiffener stiffness restrains the transition of buckling mode, which may cause the instability of structural stiffness loaded in uniaxial compression.

Copyright

© 2017, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Si-Yuan Jiang
AU  - Zhi-Dong Guan
AU  - Zeng-Shan Li
PY  - 2017/04
DA  - 2017/04
TI  - Buckling Mode Transition in Composite Panels under Different Stiffening Conditions
BT  - Proceedings of the 3rd Annual International Conference on Advanced Material Engineering (AME 2017)
PB  - Atlantis Press
SP  - 279
EP  - 287
SN  - 2352-5401
UR  - https://doi.org/10.2991/ame-17.2017.48
DO  - 10.2991/ame-17.2017.48
ID  - Jiang2017/04
ER  -