Abstract
A complementary and systematic procedure, applied to a small fixed-wing UAV, is presented for modeling the flight dynamics. An analytical dynamic model is first constructed with the help of the vortex lattice method for the aerodynamics, and the frequency response is compared with the frequency sweep flight test. Next, the model is slightly modified based on the understood limitations of the analytical model. For the given UAV used in this work, the analytical model and the flight test are well matched for the elevator and aileron input responses with only a slight modification on the overall control power. For the rudder response, the propeller normal force effect is also taken into account in addition to the control power modification in order for the model to agree well with the flight test.
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