The attitude decoupling control of the flying wing UAV (IEEE CGNCC)

Because of the special aerodynamic layout of the flying wing UAV, a strong coupling effect will be generated among its respective channel. However, this thesis, different from the traditional methods, applies the differential geometry method to the decoupling control design of the UAV. Besides, because the difficulty of the differential geometric linearity method's linear condition cannot be solved yet, nominal output function method is put forward in the thesis. And the results of the emulation show that the attitude decoupling control of the flying wing UAV, based on the differential geometry method, can meet the requirements of the program.