Wing Structure Static Analysis using Superelement

AbstractThis paper describes the use of superelement for the stress and deflection analysis of a typical fighter wing structure. Three methods of analyses were carried out and compared: practical/theoretical analysis; finite element analysis with the conventional element modeling approach; and finite element analysis with the superelement modeling. Finite element models of the wing were developed. NASTRAN FE software was used for finite element analysis. CQUAD4 and BAR2 elements represent the individual components of the wing such as the skin and stringers. In superelement approach, the wing was divided to four (4) substructures known as superelements. Wing loading at 1-g flight condition was assumed for analysis. For all these methods, the direct stress and deflection are sought and to be compared. Result shows a good agreement between the three methods