The effect of flexural/twist anisotropy on compression buckling of quasi-isotropic laminated cylindrical shells
- 28 February 2002
- journal article
- Published by Elsevier BV in Composite Structures
- Vol. 55 (2), 195-204
- https://doi.org/10.1016/s0263-8223(01)00147-7
Abstract
No abstract availableKeywords
This publication has 14 references indexed in Scilit:
- Buckling optimization of composite axisymmetric cylindrical shells under uncertain loading combinationsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,2000
- Design of laminated composite cylindrical shells under axial compressionComposites Part B: Engineering, 2000
- Layup optimization against buckling of shear panelsStructural and Multidisciplinary Optimization, 1991
- Optimal Design of Laminated-Composite Circular-Cylindrical Shells Subjected to Combined LoadsJournal of Applied Mechanics, 1988
- Importance of anisotropy on buckling of compression-loaded symmetriccomposite platesAIAA Journal, 1986
- Optimal laminate configurations of cylindrical shells for axial bucklingAIAA Journal, 1985
- Stability of imperfect laminated cylinders - A comparison between theory and experimentAIAA Journal, 1985
- Buckling of laminated composite cylinders: a reviewComposites, 1975
- Buckling of Laminated Anisotropic Imperfect Circular Cylinders under Axial CompressionJournal of Spacecraft and Rockets, 1973
- Structural efficiency of orthotropic cylindrical shells subjected toaxial compression.AIAA Journal, 1966