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![Figure 1. Dimensions, geometry and lay-ups of stiffeners. Top: Panels PSC1–PSC9 [Abramovich et al. 2003], BOX1 and BOX2 [Abramovich et al. 2008]. Middle: Panels AXIAL1, AXIAL2, and BOX 3 [Degenhardt et al. 2006]](thumbnails/s123.jpg) |
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| Nondimensional buckling loads for external-hydrostatic-pressure-loaded ring-stiffened isotropic cylinders with R/h=500 and simply supported edges |
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| Nondimensional buckling loads for compression-loaded stringer-stiffened isotropic cylinders with R/h=500 and simply supported edges |
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| Figure 1. Dimensions, geometry and lay-ups of stiffeners. Top: Panels PSC1–PSC9 [Abramovich et al. 2003], BOX1 and BOX2 [Abramovich et al. 2008]. Middle: Panels AXIAL1, AXIAL2, and BOX 3 [Degenhardt et al. 2006] |
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| Figure 3. Locations of strain gages and axial and lateral LVDT’s for panels AXIAL1 and AXIAL2. |
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| Figure 4. Panel AXIAL1: Development of the buckling pattern as function of axial compression under 85 kN, 93.5 kN, and 115 kN, and after collapse at 235 kN. |
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| Figure 5. Panel AXIAL1: Strain gage readings versus axial compression. |
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| Stiffened composite panel ready for testing under uniform end shortening |
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| Composite stiffened panel, locally buckled (that is, buckled between stringers) during the test under uniform end shortening |
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| Uniform end shortening versus total axial load, P, for the stiffened composite panel shown in the previous two slides |
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| Cylindrical, stiffened, locally initially damaged composite panel to be axially compressed |
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| Finite element model of the test specimen |
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| Load-end-shortening for the test specimen |
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| Load-end-shortening curves from test and finite element model |
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| Normal displacement contours from the finite element model for 4 values of end shortening (mm) |
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| Finite element model of the state of the panel at the collapse load |
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