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Hokiesat Side Panel Analysis
Craig Stevens 7/12/01
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Applied proper loading (moment arm) using reinforced steel shell elements.
All loads are component masses * 11G’s in +X, +Y, +Z directions.
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Skin Shell Element Stress Distribution 3 2 1
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Skin Shell Element Stress Distribution 4 6 5
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Isogrid Beam Element Stress Distribution 1 2 3
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Isogrid Beam Element Stress Distribution 4 6 5
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Panel Test Analysis 1 Boundary Conditions:
Fixed the panel edges in panel surface normal direction Fixed 6 center fastener locations in all 3 axes Applied distributed load to beam elements totaling 44 lb
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Conclusions: Loads applied normal to the panel surface do not
provide the shear stresses on the skin panels that are observed in the launch configuration Applying greater loads to the panel to get the appropriate skin stress magnitudes will most likely damage the structure due to failure of the isogrid webs
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Panel Test Analysis 2 Boundary Conditions:
Fixed the panel edges in panel surface normal direction Fixed top edge in all 3 axes Applied distributed load to bottom edge totaling 2000 lb
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Von Mises Skin Shell Element Stress Distribution
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X-Direction Skin Shell
Element Stress Distribution
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Y-Direction Skin Shell
Element Stress Distribution
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Conclusions: Loads applied parallel to the panel surface do not
provide the normal stresses in the isogrid that are observed in the launch configuration Applying these load magnitudes to the panel is somewhat unreasonable for the personel and schedule involved
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