The response of transversely point-loaded composite shells is investigated via the finite element method. The thin, circular cylindrical shells are hinged at a fixed distance apart on the straight edges and are free on the curved edges. Stability issues are considered, including nonlinear prebuckling, limit points, bifurcation, and postbuckling. In the finite element formulation, a novel technique is utilized to identify and traverse bifurcation points efficiently in the nonlinear elastic response. A classic shell buckling benchmark problem is solved here correctly for the first time; previous studies have found the isotropic shell to have a limit point, when, in fact, the shell bifurcates before reaching a limit point. Predicted results for graphite/epoxy laminated shells are in excellent agreement with measured load-deflection and mode-shape evolutions as previously reported. Two cases of extraordinarily good agreement between the data and model, particularly large-deflection asymmetric deformations modes through a bifurcation point and far into the postbuckling regime, clearly establish validated new benchmarks. Asymmetries in both directions of the shell plane, relative to the centrally applied point load, are discussed with regard to bifurcation and material couplings in the composite laminate. Asymmetric stress distributions are discussed in the context of composite damage resistance and previous experimental findings on atypical shell damage mode and extent. The influence of test fixture compliance is evaluated and briefly discussed.
Buckling response of transversely loaded composite shells, Part 2: numerical analysis
Ausbeulung eines Zylinderschalensegments unter Einwirkung einer Querkraft, Teil 2: Numerische Analyse
AIAA Journal ; 42 , 7 ; 1465-1473
2004
9 Seiten, 17 Bilder, 1 Tabelle, 55 Quellen
Article (Journal)
English
Buckling Response of Transversely Loaded Composite Shells
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