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Hokiesat Side Panel Analysis

Hokiesat Side Panel Analysis. Craig Stevens cls@vt.edu 7/12/01. Applied proper loading (moment arm) using reinforced steel shell elements. All loads are component masses * 11G’s in +X, +Y, +Z directions. Skin Shell Element Stress Distribution. 3. 2. 1. Skin Shell Element

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Hokiesat Side Panel Analysis

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  1. Hokiesat Side Panel Analysis Craig Stevens cls@vt.edu 7/12/01

  2. Applied proper loading (moment arm) using reinforced steel shell elements. All loads are component masses * 11G’s in +X, +Y, +Z directions.

  3. Skin Shell Element Stress Distribution 3 2 1

  4. Skin Shell Element Stress Distribution 4 6 5

  5. Isogrid Beam Element Stress Distribution 1 2 3

  6. Isogrid Beam Element Stress Distribution 4 6 5

  7. 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

  8. 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

  9. 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

  10. Von Mises Skin Shell Element Stress Distribution

  11. X-Direction Skin Shell Element Stress Distribution

  12. Y-Direction Skin Shell Element Stress Distribution

  13. 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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