1. Hokiesat Side Panel Analysis
Craig Stevens
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

9. 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

10. 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

11. Von Mises Skin Shell
Element Stress Distribution

12. X-Direction Skin Shell
Element Stress Distribution

13. Y-Direction Skin Shell
Element Stress Distribution

14. 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