Accession Number:

AD0759537

Title:

Buckling of Fiber-Reinforced Circular Cylinders under Axial Compression.

Descriptive Note:

Final rept.,

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO

Report Date:

1972-08-01

Pagination or Media Count:

125.0

Abstract:

CKLING STRENGTH OF LAMINATED COMPOSITE CYLINDRICAL SHELLS. An analytical solution for the buckling load was obtained by using cylindrical shells. An analytical solution for the buckling load was obtained by using Koiters theory for axisymmetric and asymmetric imperfections. For axisymmetric imperfections, numerical evaluation were carried out for the case of three-ply composite shells of glass, boron and graphite-epoxy construc-tion. It was found that drastic buckling load reductions occurred comparable to isotropic shells for small values of imperfection amplitudes. For each cylindrical shell, test model fabricated from three ply preimpregnated glass-epoxy, an equivalent imperfection amplitude was computed by using the root mean square imperfection measurements obtained from several generators. Fairly good agreement was found between the analytically predicted and experimental buckling loads. Author-PL

Subject Categories:

  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE