Design and Shear Analysis of an Angled Morphing Wing Skin Module

Morphing wing skin can greatly improve the performance of aircraft by adjusting shape wings according to different flight conditions. However, it is a challenge maintain smooth aerodynamic surface during deformation process. Here, we propose an angled morphing module based on silicon rubber matrix reinforced carbon-fiber-reinforced polymer rods, which takes advantage tensile stress generated shear prevent from wrinkling under large deformation. Experiments conducted series modules with varying initial angles indicate that starting configuration, withstand pure 92° without wrinkling, 53% larger than existing designs. A parametric analysis was also analyze effects geometric and material parameters wrinkle-free range. Finally, theoretical model energy method developed unveil underlying wrinkle prevention mechanism estimate critical angle skin. The proposed design potentially expand capability wings, leading variation in sweepback therefore superior performance.