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From: Composite Structures, Vol. 72, No. 4, April 2006, pp. 401-418: "Delamination buckling and postbuckling in composite cylindrical shells under combined axial compression and external pressure" by Azam Tafreshi, Aerospace Engineering, School of Mechanical, Aerospace and Civil Engineering (MACE), The University of Manchester, P.O. Box 88, Sackville Street, Manchester M60 1QD UK
ABSTRACT: A series of finite element analyses on the delaminated composite cylindrical shells subject to combined axial compression and pressure are carried out varying the delamination thickness and length, material properties and stacking sequence. Based on the FE results, the characteristics of the buckling and postbuckling behaviour of delaminated composite cylindrical shells are investigated. The combined double-layer and single-layer of shell elements are employed which in comparison with the three-dimensional finite elements requires less computing time and space for the same level of accuracy. The effect of contact in the buckling mode has been considered, by employing contact elements between the delaminated layers. The interactive buckling curves and postbuckling response of delaminated cylindrical shells have been obtained. In the analysis of post-buckled delaminations, a study using the virtual crack closure technique has been performed to find the distribution of the local strain energy release rate along the delamination front. The results are compared with the previous results obtained by the author on the buckling and postbuckling of delaminated composite cylindrical shells under the axial compression and external pressure, applied individually.
Shown here:
Fig. 9. (i) The first buckling mode of the graphite-epoxy cylindrical shell with the stacking sequence of [0/90/0]10T, delamination thickness of h = 0.5 and delamination width of a/L = 0.125, under different combinations of axial compression and external pressure. (ii) The first buckling mode of the graphite-epoxy cylindrical shell with the stacking sequence of [0/90/0]10T, delamination thickness of h = 0.3 and delamination width of a/L = 0.125, under different combinations of axial compression and external pressure.
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