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

Personal Author(s) : Tennyson,R. C. ; Muggeridge,D. B. ; Chan,K. H. ; Khot,N. S.

Report Date : AUG 1972

Pagination or Media Count : 125

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 Koiter's 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)

Descriptors :   (*SHELLS(STRUCTURAL FORMS), BUCKLING), LAMINATES, CYLINDRICAL BODIES, COMPOSITE MATERIALS, COMPRESSIVE PROPERTIES, LOADS(FORCES), MATHEMATICAL MODELS, COMPUTER PROGRAMS

Subject Categories : Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE