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| Part of a laminated composite stiffened panel with a local delaamination that grows (delta A) with increasing axial compression |
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| Load-end shortening curves without and with delamination growth (delta A) |
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| Stiffened panel with original local delaminated area, A |
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| Finite element model of the stiffened panel with refined discretization covering the local delaminated area plus more in order accurately to predict delamination growth, delta A |
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| Very local post-buckling of the delamiated area. top=entire panel; bottom = zoomed post-buckled delaminated area, A + delta A |
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| (top) Overall skin buckling with associated stringer deformation; (bottom) enlarged view of the localy post-buckled delaminated region, A + delta A |
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| Circumferentially corrugated cylindrical shell |
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| Starting design and optimized design of a circumferentially corrugated cylindrical shell with external T-shaped rings |
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| Circumferentially corrugated can buckled under hydrostatic compression |
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| General and local buckling of axially compressed grid-stiffened composite cylindrical shells |
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| Part of the fuselage of a B-52 showing many local skin buckles in a region where there is high in-plane shear loading |
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| Stiffened fuselage panel: Allowing local skin post-buckling during the design phase of a project (Weight 2) produces lighter optimized designs |
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| Open cylindrical shell with a single mid-length slender ring and with widely spaced stringers |
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| 180-degree torqued widely ring/stringer-stiffened cylindrical shell, The post-critical model deformation and test results agree. |
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| Post-buckling of the panel from test (left) and theory (right) |
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