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- W2068800267 abstract "Experimental buckling behaviors for fiber-reinforced, circular cylindrical panels under prescribed uniform end-displacement are compared with numerical buckling behaviors computed from an energy-based, finite-difference computer program. Buckling behaviors were obtained for five test panels with simply-supported straight edges and clamped curved edges, and for five test panels with unsupported straight edges. Numerical buckling behaviors were obtained for one panel from each of the two groups using measured initial transverse imperfections. Experimental buckling loads for test panels with simply-supported straight edges ranged from 4600 to 5775 lb. This range of experimental buckling loads was due principally to an inability to impose circumferential displacements precisely, and to differences between distributions of initial transverse imperfections for various test panels. Numerical computations using measured initial transverse imperfections and boundary conditions along the straight edges that allowed circumferential displacements to either occur freely or to be completely restrained tend to confirm these assertions. Favorable agreement was observed, since the experimental buckling loads were included between the two limiting numerical buckling loads (4505 and 6106 lb). Experimental buckling loads for test panels with unsupported straight edges ranged from 2165 to 2715 lb. This range of experimental buckling loads was due principally to differences between distributions of initial transverse imperfections for various test panels, and, possibly, small initial stresses that accompany installation of a test panel in the testing device. Numerical computations indicate that the experimental buckling loads are associated with a limit point that correspond to equilibrium configurations remote from the equilibrium configuration corresponding to buckling of the straight edges. The computed buckling load (2500 lb) compared favorably with the experimental buckling (2715 lb) corresponding to the initial imperfections used to calculate the numerical buckling load." @default.
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- W2068800267 date "1983-01-01" @default.
- W2068800267 modified "2023-09-27" @default.
- W2068800267 title "Further comparison of the numerical and experimental buckling behaviors of composite panels" @default.
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- W2068800267 doi "https://doi.org/10.1016/0045-7949(83)90029-9" @default.
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