This paper presents the design and dynamic analysis of a variable-span, variable-sweep morphing UAV. The construction of a morphing wing test model is discussed followed by the aerodynamic modeling of a morphing wing UAV using the vortex lattice method. The variation of the longitudinal aerodynamic coefficients as a function of span and sweep change is discussed in detail. A nonlinear dynamic model is then developed and used to simulate and analyze the response of the UAV to morphing at different rates. The variation in the longitudinal dynamic modes resulting from different morphing configurations is also presented.
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