The multiweb box structures in the wings are paid special attention in aircrafts'structural design.The multiweb box is mainly composed of skins and stiffeners.The skins are approximately divided into many rectangular panels by stiffeners.During the service of an aircraft,the wing majorly bears bending,torsion,and bending-torsion coupling loads,etc.,so the panels in box structures are susceptible to instability.In traditional buckling analysis of composite panels,the boundary conditions were typically simplified as either clamped or simply supported boundaries,with significant deviations from experimental results.On the other hand,compre-hensive simulations with the finite element method are generally inefficient.Aimed at the above issues,a rapid buckling analysis method combining the unit cell model with the differential quadrature method for composite panels was proposed.Firstly,the unit cell model was established to calculate the stiffness coefficients of elastic boundaries of rectangular panels.The governing equations were then solved with the differential quadrature method to obtain the buckling loads on the panels.Finally,the buckling loads on composite panels in different types of box structures were calculated and compared to the results obtained with the finite element method to verify the accuracy of the presented buckling analysis method.
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