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fuselage panel cutouts (multiple coutouts)

fuselage panel cutouts (multiple coutouts)

fuselage panel cutouts (multiple coutouts)

(OP)
thread2-261148: Fuselage Cutouts and Skin Doublers

I am an aerospace engineer and I am trying to determine how to calculate a panel with 3 or more wide cutouts.
The panels has a FINITE width and length. The distance from the center of the hole to the edge (any) is less than 2D.
The load is:
- tension on x
- tension on y
- shear on xy

I calculated the principal stresses and the angle to the holes' axis and then I tried to use Peterson. Unfortunately it seems that this case is not exactly covered.

Question:
- Is there any particular analytical method that allows to calculate the stress on the edge of the holes? If yes... which one? If not... I appreciate your suggestions.

Thank you very much... in advance.

Regards,
U   

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