Six Degree-of-Freedom Dynamical Model of a Morphing Aircraft
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Morphing aircraft are envisioned to have multirole capability where the ability to change shape allows for adaptation to a changing mission environment. In order to calculate the properties of many wing configurations efficiently and rapidly, a model of a morphing air-craft is needed. This paper develops an aerodynamic model and a dynamic model of a morphing ying wing aircraft. The dynamic model includes realistic aerodynamic forces, consisting of lift, drag, and pitching moment about the leading edge, calculated using a constant strength source doublet panel method. The panel method allows for the calculation of aerodynamic forces due to large scale shape changing effects. The aerodynamic model allows for asymmetric configurations in order to generate rolling and yawing moments. The dynamic model calculates state information for the morphing wing based on the aerodynamic forces from the panel method. The model allows for multiple shape changing degrees-of-freedom for the wing, including thickness, sweep, dihedral angle, and chord length. Results show the model provides a versatile and computationally eficient tool for calculating the aerodynamic forces on the morphing aircraft and using these forces to show the associated states. Copyright © 2009 by Adam Niksch, John Valasek, Thomas W. Strganac, and Leland A. Carlson.
author list (cited authors)
Niksch, A., Valasek, J., Strganac, T., & Carlson, L.