A Novel Tandem Ducted Fan UAV Attitude Control Based on Cascade PID Controller

In this paper, we introduce a novel tandem ducted fan unmanned aerial vehicle (UAV) and focus on the attitude control problem of it. Firstly, the structural layout of this new vehicle is introduced, then the force analysis and mathematical formula are performed based on kinematic and dynamical formulas. Secondly, this section is not only focuses on the degsign of controller but also the analysis of its advantages. For example, how they can improve system performance through frequency domain analysis, implementation of specific algorithms. Thirdly, an outdoor flight experiment is completed. The experimental process is as follows: after having the appropriate parameters, the vehicle is first allowed to fly to a height of about 10 meters and hover down, and then three attitude angle changes are performed. Finally, we conclude that the cascade PID controller for this type of UAV attitude control is simple, practical and can cope with many flight conoditions and indicate the shortcomings of this dissertation and future work.