Buckling Analysis of Laminated Composite Circular Cylindrical Shells.
Abstract
The effects of prebuckling displacements on the buckling 8 OF LAMINATED COMPOSITE CIRCULAR CYLINDRICAL SHELLS ARE INVESTIGATED. Both axial compression and pure torsion are considered for two shell geometries. A clamped prebuckling boundary condition is used for all analysis with four buckling boundary conditions applied during the buckling process. The shell walls are made up of a 6 ply laminate with several symmetric ply orientations. The study was made using the STAGS computer code, utilizing the linear bifurcation branch with linear prebuckling displacements. The results are compared to the buckling loads determined when prebuckling displacements are neglected. It is shown that prebuckling deformations generally tend to decrease the buckling load of a composite shell. Increased buckling loads can occur under axial compression with prebuckling displacements ASSUMED PRESENT, FOR PARTICULAR PLY ORIENTATIONS, DUE TO A HIGHER BENDING STIFFNESS. Similarly, under torsion, an increase in buckling load can occur because of a higher tension hoop stress. It is also shown that prebuckling displacements can cause shell buckling before failure of the fibers occurs. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1978
- Accession Number
- ADA081904
Entities
People
- James G. Harper Ii
Organizations
- Air Force Institute of Technology