This paper treats the instability of rectangular sandwich panels with nonisotropic cores and faces of different materials or thicknesses. The simply supported panel is loaded with a uniform edge compression. The solution is expressed in terms of a major buckling coefficient, given as the ratio of the critical lateral buckling load to the critical cylindrical buckling load, which is a function of several nondimensional parameters. A single family of curves shows the buckling behavior for all parameters. The effect of a moderate temperature differential between the two faces can be approximately considered by modifying their moduli of elasticity in accordance with their temperature levels. Besides the regular panel instability, a zone of core shear instability is determined and discussed in detail. Numerical examples are presented to illustrate the application of the analysis.
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September 1960
Research Papers
Elastic Instability of Rectangular Sandwich Panel of Orthotropic Core With Different Face Thicknesses and Materials
C. C. Chang,
C. C. Chang
Department of Aeronautical Engineering, Institute of Technology, University of Minnesota, Minneapolis, Minn.
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I. K. Ebcioglu
I. K. Ebcioglu
Department of Aeronautical Engineering, Institute of Technology, University of Minnesota, Minneapolis, Minn.
Search for other works by this author on:
C. C. Chang
Department of Aeronautical Engineering, Institute of Technology, University of Minnesota, Minneapolis, Minn.
I. K. Ebcioglu
Department of Aeronautical Engineering, Institute of Technology, University of Minnesota, Minneapolis, Minn.
J. Appl. Mech. Sep 1960, 27(3): 474-480 (7 pages)
Published Online: September 1, 1960
Article history
Received:
April 30, 1959
Online:
September 16, 2011
Citation
Chang, C. C., and Ebcioglu, I. K. (September 1, 1960). "Elastic Instability of Rectangular Sandwich Panel of Orthotropic Core With Different Face Thicknesses and Materials." ASME. J. Appl. Mech. September 1960; 27(3): 474–480. https://doi.org/10.1115/1.3644027
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