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Fastener load estimation from global FEM

Fastener load estimation from global FEM

Fastener load estimation from global FEM

(OP)
I have a global wing model, with plate elements for skin, ribs and spars and beam/bar elements for stringers and other longitudinal members.

which is the usual way for the estimation of the loads of a group of fasteners on a wing spar panel? should I use the nodal interface loads or estimate from the elemental stresses? how?

The panel is delimited between the vertical longeron stiffeners and the longitudinal ones.

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