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 aircraft is needed. This paper develops an aerodynamic model and
a dynamic model of a morphing
flying 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 efficient tool for calculating
the aerodynamic forces on the morphing aircraft and using these forces to show the
associated states.
| Identifer | oai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/ETD-TAMU-2009-08-7180 |
| Date | 14 January 2010 |
| Creators | Niksch, Adam |
| Contributors | Valasek, John |
| Source Sets | Texas A and M University |
| Language | en_US |
| Detected Language | English |
| Type | Book, Thesis, Electronic Thesis |
| Format | application/pdf |
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