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The question states:for the following beam, find the axial loads in the stiffening rods and the shear loads acting on each of the following edges.

I basically worked out the shear for the panels by making an imaginary cut and letting internal momment equal to zero. Giving 70.7KN on the two most horizontal and 30KN on the vertical . The part that I am stuck is is how do I calculate the the axial loads in the stiffening rods?

Cheers for the help.

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# Aerospace Stiffened shear panels.

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