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Attitude control is the inner‐loop and the most important part of the automatic flight control system of an unmanned aerial vehicle (UAV). The information fusion‐based optimal control method is applied in a UAV flight control system in this work. Firstly, a nonlinear model of alterable thrust direction UAV (ATD‐UAV) is established and linearized for controller design. The longitudinal controller and lateral controller are respectively designed based on information fusion‐based optimal control, and then the information fusion flight control system is built up. Finally, the simulation of a nonlinear model described as ATD‐UAV is carried out, the results of which show the superiority of the information fusion‐based control strategy when compared to the single‐loop design method. We also show that the ATD technique improves the anti‐disturbance capacity of the UAV

Information Fusion-Based Optimal Attitude Control for an Alterable Thrust Direction Unmanned Aerial Vehicle