بررسی عددی بارگذاری کمانشی و شکل مود های کمانشی یک ایرفویل متقارن از جنس پوسته کامپوزیتی

Since airfoils can be considered as shells with a certain curvature, they exhibit similar buckling behavior. This paper analyzes and investigates the stability of an aircraft wing with a symmetrical NACA0012 airfoil section, so that the wing skin is a composite type with a layer of (0/90/45/-45)s and material AS4/3501-6. First, the buckling theory of shells and thin plates is investigated analytically for similar sections. Then, the buckling load and mode shapes are analyzed in the finite element software Abaqus for the mentioned section and these values ​​are compared with each other for the layer of (0)s and (90)s. In the next stage, by increasing the ribs and stringers, an attempt will be made to increase the structural strength and buckling load, which is accompanied by a 10% increase in the weight of the initial structure, and finally the outputs will be determined in terms of buckling loads depending on the type and material of the section. The results indicate that by adding ribs and stringers, the critical buckling load will increase significantly.