WATSON, A., WILLIAMS, F.W. and KENNEDY, D., 1998. Buckling load reduction for stiffened panels due to cutouts in ribs. AIAA Journal, 36(2), pp. 264-266
In aerospace structures it is common to find stiffened panels with transverse
supporting structures, e.g. wing ribs or fuselage frames. Incorporating cutouts into
these supporting structures to allow the stringers to pass through freely considerably
reduces the buckling load of the panels. It is shown that a minor modification in the
fabrication of the stiffened panel gives most of the advantages of cutouts while still
giving a buckling load close to that of a panel with no cutouts.