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Flutter of Thermally Buckled Composite Sandwich Plates

Le-Chung Shiau1, Shih-Yao Kuo2

Professor, Department of Aeronautics & Astronautics, National Cheng Kung University, Tainan, Taiwan R.O.C.
Former Graduate Student, now as Assistant Professor at Dept. of Flight Service Management, Aletheia Univ.,Tainan, Taiwan, R.O.C.

Computers, Materials & Continua 2007, 5(3), 213-222. https://doi.org/10.3970/cmc.2007.005.213

Abstract

A high precision high order triangular plate element is developed for the linear flutter analysis of thermally buckled composite sandwich plates. Due to uneven thermal expansion in the two local material directions, the buckling mode of the plate may be shifted from one pattern to another for certain fiber orientation or plate aspect ratio as the aerodynamic pressure is present. This buckle pattern change alters the frequencies and modes of the plate and that in turn changes the flutter coalescent modes. Numerical results show that temperature has a destabilizing effect on the flutter boundary but the aerodynamic pressure has a stabilizing effect on the buckling boundary.

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Cite This Article

L. . Shiau and S. . Kuo, "Flutter of thermally buckled composite sandwich plates," Computers, Materials & Continua, vol. 5, no.3, pp. 213–222, 2007.



cc This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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