Buckling of Orthotropic Sandwich Cylinders Under Axial Compression and Bending
Authors:
- 1 April 1974
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 11 (4) , 207-212
Abstract
No abstract availableThis publication has 10 references indexed in Scilit:
- Simplified design equations for buckling of axially compressed sandwich cylinders with orthotropic facings and coreJournal of Aircraft, 1969
- Buckling of cylindrical and conical sandwich shells with orthotropicfacings.AIAA Journal, 1969
- Experimental investigation of sandwich cylinders and cones subjectedto axial compression.AIAA Journal, 1968
- Buckling of composite cylindrical shells under pure bending.AIAA Journal, 1968
- UNIRED THEORY FOR THE BENDING AND BUCKLING OF SANDWICH SHELLS - APPLICATION TO AXIALLY COMPRESSED CIRCULAR CYLINTRICAL SHELLS1967
- Structural efficiency of orthotropic cylindrical shells subjected toaxial compression.AIAA Journal, 1966
- Stability of circumferentially corrugated sandwich cylinders under combined loadsAIAA Journal, 1964
- Sandwich cylinder instability under nonuniform axial stressAIAA Journal, 1964
- On the Buckling of Circular Cylindrical Shells Under Pure BendingJournal of Applied Mechanics, 1961
- Buckling of Sandwich Cylinders Under Combined Compression, Torsion, and Bending LoadsJournal of Applied Mechanics, 1955