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A.1 Preliminary Calculation of the Honeycomb plate using finite element Analysis
A.1.5 Results of the calculations
- Stress results
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The stresses in the honeycomb plate for each load case are shown in Figures A-8 to A-13. Figures A-8 to A-10 present the Von Mises stresses due to the three load cases in the aluminum skins + frame and triangle, while Figures A-11 to A-13 present the Von Mises stresses due to the three load cases in the honeycomb core.
The maximum stresses appear for LOAD CASE 3 (i.e. 4.25 g on X, 4.25 g on Y, and 17 g on Z). The maximum values for the Von Mises stresses are the following for all layers of the composite structure:
Maximum Von Mises stresses
| | Aluminum skin+frame and triagle | Aluminum core |
| Load case 1 | 17.5 MPa | 0.069 MPa |
| Load case 2 | 12.6 MPa | 0.05 MPa |
| Load case 3 | 41.8 MPa | 0.207 MPa |
- Displacement results
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The displacements for the honeycomb plate are shown in Figures A-14 to A-16. Different colors on these figures illustrate different displacements of the nodes from their original undeformed positions. The maximum displacements appear, of course, in the central region of the plate where the load cases are applied.
Maximum displacement results
| | Global displacement maximum value |
| Load case 1 | 0.41 mm |
| Locad case 2 | 0.40 mm |
| Locad case 3 | 1.6 mm |
- Discussion
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Considering the worse load case, i.e. load case 3, we have the maximum stress on the skins equal to 42 MPa, which multiplied by a safety factor of two gives 84 MPa. The margin of safety is 4.23. Concerning the aluminum core, we have the maximum stress for load case 3 equal to 0.2 MPa, which gives 0.4 MPa including the safety factor of two. The margin of safety is then equal to 4.75.
Issue: Draft - Revision: 04 - Last Modified: 20 April 1997