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scheme for load redistribution after buckling


Bill Avery:
is there a recommended scheme for getting updated loads due to load redistribution after buckling? For example, a portion of a wing skin buckles and redistributes some of the load into the spar. How can i update the loads in the spar and then run margin checks?

I think what you are describing is postbuckling. If you activate postbuckling (on the buckling tab) and iterate with FEA, HyperSizer will export the reduced stiffness matrix to the FEM. Then the new load distribution will account for the panel softening and the load will redistribute into the spar caps.

See postbuckling help section topic more information:

See help topic on "iterating with FEA"

I hope this is helpful

Bill Avery:


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