Structural Design of Composite Aircraft Based on Static Aeroelastic Analysis*

In this research article, the structural sizing and weight reduction of an airplane structure have been effectively carried out using a Two-way FSI analysis and carbon fiber-reinforced plastic (CFRP) material. Since the maximum percentage of an airplane’s weight is carried by the fuselage and main wing so in this manuscript the structural sizing and weight reduction is mainly conducted for these parts. Here the model assumes to be B737 and the composite material (T800S/3900-2B) used as a structural material is similar to the B787. In two-way FSI analysis, coupled-field method is used to exchange of information (load and deformation) between the fluid (CFD) and structural (CSD) solvers. CFD analysis has been conducted to estimate the aerodynamic load on the structure by the main wing while structural sizing has been carried out on the fuselage skin thickness using inertia relief with buckling analysis. In this model, the load between the main wing and fuselage is transferred by the RBE3 element. CROD and CBEAM element has been used for the stringer and frame while CSHELL element is used for the spar, floor beam, skin, keel beam, and bulkhead. In previous studies, CFRPs are applied for a maximum of 50% of the whole structure while in this study CFRP has been employed for the whole structure. The outcome of this study expedites that the weight of the airplane design can be reduced by 20-25%.