Aero-Structural Evaluation of Morphing Control Surface Using Corrugated Panels

抄録

Morphing wing technology is anticipated as a way to improve efficiency over a wider range of flight conditions, but it is difficult to realize morphing because there are two conflicting demands, i.e. stiffness for aerodynamic forces and flexibility for morphing. Super-anisotropy of the corrugated panel is a solution to satisfy those demands. This paper focuses on applying camber morphing to vertical plane. Firstly, optimal deformation of airfoil for morphing control surfaces is defined by conducting airfoil analysis. For realizing optimal deformation, deformation analysis of corrugated panels is conducted and evaluated by using high flexible 2-D beam equations.