Exploration of the effect of wing component post-buckling on bending-twist coupling for nonlinear wing twist

Abstract A new investigated concept for passive load alleviation is to exploit the nonlinear behavior of wing design components trigger a deformation which reduce loads once critical level reached. The necessary torsional rotation supposed angle attack. For this target, wingbox sections are regarding their with finite element analysis. Parameter studies feature anisotropic carbon fiber reinforced polymer (CFRP) layups skins, and thicknesses spars presence stringers. Results show desired progressive bending-torsion coupling an unstiffened section, when upper skin rear spar modified. After modification they allowed buckle within envelope. has layup. needs be thinner than front spar. Both modifications result in progressively increasing load. Stringers not applied because limit nonlinearity envisioned technique.