Journal
JOURNAL OF VIBRATION AND CONTROL
Volume 26, Issue 3-4, Pages 214-228Publisher
SAGE PUBLICATIONS LTD
DOI: 10.1177/1077546319878538
Keywords
Normal deformation; modified couple stress theory; laminated composite; free vibration; buckling
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In this paper, the free vibration and buckling responses of laminated composite and sandwich microbeams with arbitrary boundary conditions are investigated. The governing equations based on the modified couple stress theory are derived by using the total potential energy of a microbeam and employing a transverse shear-normal deformable beam theory. Extensive analysis results in terms of dimensionless fundamental frequencies and dimensionless critical buckling loads are introduced for various boundary conditions, aspect ratios, orthotropy ratios, fiber orientation angles, thickness to material length scale parameter ratios, and core thickness to face layer thickness ratios.
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