STRENGTH PROPERTIES AND RELATIONSHIPS ASSOCIATED WITH VARIOUS TYPES OF FIBERGLASSREINFORCED FACING SANDWICH STRUCTURE
Abstract
Contributions to the acceptance of fiberglass-reinforced plastic (FRP) as an aircraft structural material were made through verification of existing theoretical strength relationships by the fabrication and testing of sandwich panels in the laboratory. The four basic failure modes were investigated for sandwich plates and plate columns loaded in edgewise compression. These were general buckling, face wrinkling, shear crimping and face dimpling. To achieve these modes, it was necessary to vary not only the specimen size and boundary conditions but also, in many cases, the dimensions and composition of the constituent materials. In the development of a suitable structural sandwich, a number of advances were made in the realm of fabrication. These include the development of a multi-ply pre-preg, the establishment of a precure phase in the resin cure cycle as a control of resin flow, and the use of the separately-bonded type of sandwich construction. The effect of adhesive filleting on the core strength and the effect of laminate thickness on facing strength properties were also isolated.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1965
- Accession Number
- AD0621522
Entities
People
- Gene M. Nordby
- W. C. Crisman
Organizations
- University of Oklahoma