Numerical aerodynamic-structural coupling research for flexible flapping wing

Due to the small size and light weight, flexible deformation plays an important part in flapping wing aerodynamics. the aero-elastic performances of Flapping-wing Micro Air Vehicle (FMAV) are researched by solving the Reynolds-Averaged Navier-Stokes (RANS) equations and structural dynamic equations. An aerodynamic-structural coupling computational framework is developed, which is able to simulate aerodynamic-structural coupling characteristics of flexible flapping wings. The flapping wing's unsteady aerodynamic characteristics is obtained by solving Reynolds Average Navier-Stokes (RANS) equations. Structural dynamic equations capable of describing the flapping wing's movement are derived by using Hamilton principle, then discreted through finite element method and solved by Newmark solution to get structural characteristics. Loose coupling method is used. On the basis of the above work, CFD/CSD (Computational Fluid Dynamics/Computational Structural Dynamics) grid data exchange method, dynamic grid technology as well as coupling method are further investigated, and finally a complete set of CFD/CSD coupling solver is developed. Computational results show good agreement with experimental results, which prove that the method developed in this paper are valid and suit for simulation of flexible flapping wing. Effect of inertia loads and kinetic parameters are also investigated, which can help to understand the mechanisms of flexible flapping wing's aeroelasticity and give a guidance in the design of flexible flapping wing.