Buckling Analysis of A Composite Stiffend Panel Structure In The Aircraft’s Wing

Buckling analysis of the composite stiffened panel in the aircraft’s wing was performed. The composite panel must meet the requirements of the structure and reduces the weight. For compare the types of stiffeners, the number of skin layers and stiffeners were assumed to be constant at each stage. At first, buckling strength was determined using ABAQUS and it was determined that the Hat-Type stiffner in single state and with the first layup, compared to the T-Type stiffener, 31%, J-Type 35% and The blade-Type, 41% withstand more buckling load. It also withstand higher buckling load for multiple modes and the second type of layup than the T-Type stiffener, 76%, J-Type, 79%, and blade-Type 70%. Next, important parameters such as number, dimensions and different layups on the selected stiffeners were investigated. It was found that the weight of the panel with 2 stiffeners, first layup and cross section 1 is almost equal to the weight of the panel with 3 stiffeners and cross section 3, but the buckling load of the plate with 3 stiffeners is 2.31 and the buckling load of the panel with with 2 stiffeners is 0.89.