Analytical/Experimental Investigation of the Instability of Composite Cylindrical Panels.
Abstract
An analytical and experimental program was conducted to study the instability of 8-ply laminated cylindrical panels (graphite-epoxy) subjected to an axial compressive loading. The analysis included three different ply orientations, five different boundary conditions on the vertical edges, and three different panel sizes. The analytical buckling loads were obtained by using the linear bifurcation branch of the STAGS-C computer code, and several nonlinear collapse analyses were also made on selected configurations. The experimental tests were conducted by the Air Force Flight Dynamics Laboratory using a specially deigned test fixture. Relatively good agreement was obtained between the analytical and experimental buckling loads, particularly when the nonlinear collapse load was used. The linear bifurcation results were 11 - 28% higher than the nonlinear results, indicating that the nonlinear effects in circular composite panels are important. The boundary conditions (especially w and v) had the greatest influence on the buckling load, followed by the aspect ratio and finally the ply orientation. The (+ or - 45)2s panels exhibited an unusually large increase in the buckling load when the aspect ratio was small and the in-plane displacements were restrained at the edges. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1979
- Accession Number
- ADA079850
Entities
People
- Marvin L. Becker
Organizations
- Air Force Institute of Technology