The stiffness reduction of the composing walls of thin-walled compression ambers, due to initial vividness of the walls, affects the bending stiffness and consequently the buckling load in column failure. Loaded in beading thin aircraft wings obtain noticeable curvature, therefore also the compres¬sion members of the wing panels. The bending moment in these members is maximal in the center of the bays between successive ribs and minimal at the supporting ribs (crushing). Therefore their bending stiffness varies along the bay and differs from the bending stiffness in the absence of crushing. For a representative model the buckling load is being established as affected by the crushing parameter. The strength induction due to crushing is being compared to the reduction due to wall imperfection alone.
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