Analytical Shear Buckling Investigation of Curved Composite Panels.
Abstract
This numerical investigation parametrically determined how material and geometric properties affect the buckling load capability of 8-ply curved composite panels loaded under pure shear. The linear bifurcation capabilities of the STAGSC-1 finite element computer code developed by the Lockhead Palo Alto Research Laboratory was employed. Results from this computer code were compared with other published analytical results of similar configuration to verify boundary conditions. Representative material properties for both graphite-epoxy and Kevlar-epoxy were used. The aspect ratios of 0.5, 1.0, and 2.0 was achieved by varying the axial length of the cylindrical panel. Both quasi-isotropic and symmetric orthotropic fiber orientations were analysed. Results indicate that these curved composite panels, while loaded with a shear load resulting in pure shear reactions in flat plates, do not react in pure shear. Once the interior force resultants are established, the load carrying capability of the curved panels follow classical laminated plate theory. Originator-supplied keywords included: Composite Materials, Shear Buckling, Finite Elements, Bifurcation Analysis, Curved Panels.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1984
- Accession Number
- ADA153138
Entities
People
- J. K. Mcdaniel
Organizations
- Air Force Institute of Technology