Experimentally validated flexible-multi-body structural dynamics model of a bioinspired ornithopter
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abstract
Flapping-wing vehicles combine the ability to hover like rotary-wing aircraft while also allowing for gliding flight, much like fixed-wing aircraft. They have the potential to dive and perch, are highly maneuverable and agile, and have improved safety and reduced noise emissions when compared to rotary-wing vehicles. The dynamics of flapping-wing flight needs to be better understood in order to design efficient flapping wing vehicles. The primary objective of this paper is to model the dynamic performance of a flexible wing ornithopter considering wing kinematics. It addresses the development of flexible-multibody structural dynamic model of a bioinspired ornithopter that takes into account the inertia, gravity, and aeroelactic effects. Aerodynamic loads resulting from the blade element theory are applied on the structural dynamic model employing Finite Element Methods. The flexible wing structure is integrated in a modal based flexible-multi-body dynamics solver, which is used for the simulations of experimental ornithopter configuration. The resulting ornithopter flight simulator is validated with experimental test data revealing the time history of the wing kinematics and integrated vertical and horizontal forces on the ornithopter. The model was validated and the resulting simulated wing deflections matches well with the experimental deflections, such as the wing tip path. Integrated forces acting on the flexible-multi-body dynamics model was also compared to experimental results. 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
