Abstract
To improve the fuel efficiency, commercial aircraft has recently had high aspect ratio wing. However, it increases the wing root bending moment and reduces the performance of wing strength. As a solution to this issue, adaptive wing structures are proposed. The adaptive wing means a wing which can change its shape in flight. The previous research shows that wing root bending moment can be decreased by using adaptive wing structures, but many analysis cases are needed for optimization of the wing root bending moment. This study focuses on the reduction of the high computational cost. A new method for Load Control using Superposition (LCS method) is suggested. By comparing the analysis result of LCS method with that of MSC/NASTRAN, the LCS method are verified. In addition, the LCS method is compared with geometrically nonlinear aeroelastic analysis to evaluate its accuracy for large deflection cases. The large flap angle causes the geometrically nonlinear effect, so it is suggested that the LCS method works only in range of about 10 degrees of flap angles.
