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![Nondimensional buckling loads for external-hydrostatic-pressure-loaded ring-stiffened isotropic cylinders with R/h=500 and simply supported edges](thumbnails/s121.jpg) |
![Nondimensional buckling loads for compression-loaded stringer-stiffened isotropic cylinders with R/h=500 and simply supported edges](thumbnails/s122.jpg) |
![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) |
![Figure 3. Locations of strain gages and axial and lateral LVDT’s for panels AXIAL1 and AXIAL2.](thumbnails/s124.jpg) |
![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.](thumbnails/s125.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.](thumbnails/s126.jpg) |
![Stiffened composite panel ready for testing under uniform end shortening](thumbnails/s127.jpg) |
![Composite stiffened panel, locally buckled (that is, buckled between stringers) during the test under uniform end shortening](thumbnails/s128.jpg) |
![Uniform end shortening versus total axial load, P, for the stiffened composite panel shown in the previous two slides](thumbnails/s129.jpg) |
![Cylindrical, stiffened, locally initially damaged composite panel to be axially compressed](thumbnails/s130.jpg) |
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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](thumbnails/s131.jpg) |
![Load-end-shortening for the test specimen](thumbnails/s132.jpg) |
![Load-end-shortening curves from test and finite element model](thumbnails/s133.jpg) |
![Normal displacement contours from the finite element model for 4 values of end shortening (mm)](thumbnails/s134.jpg) |
![Finite element model of the state of the panel at the collapse load](thumbnails/s135.jpg) |
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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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