BUCKLING OF WING SPARS UNDER COMBINED LOADING

摘要

Design rules for the prediction of critical buckling stresses in aircraft wing spars are extended to cover loading cases which include uniform transverse compression. Curve fitting for pure loading cases enables numerical predictions to be made of the stiffener dimensions required to provide effective simple support to the skin, and of the critical buckling stress for panels of arbitrary dimensions. A proposed extension of the method to combined loading cases is outlined.