Multibody Analysis of a Micro-aerial Vehicle Flapping Wing
نویسندگان
چکیده
Abstract. This paper discusses the use of multibody dynamics, augmented by the direct implementation of nonlinear finite element beams and significantly shells, to perform the coupled structural and fluid-dynamics analysis of flapping wing Micro-Aerial Vehicles. The implementation of the shell formulation in a free general-purpose multibody solver is described and validated. The solver, coupled to a free-wake aerodynamic model based on vortex-lattice, is applied to the analysis of a very flexible MAV flapping wing. Encouraging results have been obtained, which illustrate how the structural model should be able to capture the physics of the problem when coupled with more sophisticated aerodynamic models.
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