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| A ring-stiffened longitudinally corrugated cylindrical shell to be tested under combined loads at NASA Langley Research Center (1978) |
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| Corrugated, externally ring stiffened graphite-epoxy cylinder |
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| The large graphite-epoxy corrugated and ring-stiffened cylindrical shell installed in the testing machine at NASA Langley Research Center |
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| Buckled corrugated, externally ring stiffened graphite-epoxy cylinder shown in the previous two slides |
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| A large aluminum corrugated and ring-stiffened cylindrical shell installed in the testing machine at NASA Langley Research Center |
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| Buckled large corrugated and externally ring-stiffened cylindrical shell shown in the previous slide |
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| A large corrugated and internally ring-stiffened cylindrical shell to be tested in the rig shown two slides ago |
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| The buckled large corrugated and internally ring-stiffened cylindrical shell shown on the previous slide |
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| Locally and generally buckled ring and stringer stiffened aluminum cylindrical shell subjected to overall bending |
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| Locally and generally buckled ring and stringer stiffened aluminum cylindrical shell under torque |
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| Laboratory specimens tested and to be tested under hydrostatic compression |
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| Circumferential profile of two buckling modes: (a) local skin panel mode; (b) global panel mode |
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| Ring and stringer stiffened cylindrical panel |
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| Laminated composite cylindrical skin |
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| Assumed buckling patterns from the simple PANDA-type theory (See the next slide for the buckling formula) |
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