Thermo-elastic equations for a sandwich panel under arbitrary temperature distribution, transverse load and edge compression /
Ibrahim K. Ebcioglu.
Description
- Language(s)
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English
- Published
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Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1961.
- Summary
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The problem of designing sandwich panels for use under an arbitrary temperature distribution, transverse load, and edge compression was extremely simplified. The core of the sandwich panel is assumed to be orthotropic and the faces may be of different thicknesses and materials. The general differential equations for a sandwich panel are obtained from the principles of mechanics, and corresponding boundary conditions are formulated from the principle of virtual displacements and variational calculus. A reduction from 5 differential equations for a sandwich panel to 2 independent systems of differential equations is accomplished by the suitable transformations of the independent variables. The final 2 systems of differential equations are solved simultaneously for an arbitrary temperature distribution, transverse load, and uniform edge compression with simply-supported boundary conditions. The analysis is greatly simplified by the use of the uperposition principle. Th theoretical solution is applied to a particular temperature distribution and center deflection in the sandwich panel plotted against loading parameter.
- Note
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"Includes errata sheet."
"AD0267040 (from http://www.dtic.mil)."
"August 1961."
- Physical Description
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iv, 64 pages :
illustrations, figures ;
28 cm.
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