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Dynamic Inversion PID Based Control Law Design for A Flying Wing Aircraft

With the development of modern flight technology, the aerodynamic layout of the aircraft has been developed rapidly towards the direction of multiple control surfaces. However, the coupling of each control surface becomes higher and higher and the conventional linear control method is no longer suitable for these aircrafts. In this paper, the six degrees of freedom of the flying wing aircraft is built firstly. Then, a nonlinear dynamic inverse and PID control method is proposed to design the control system of the tailless flying wing aircraft. The dynamic inversion is used to design the control laws of fast and slow loop, and the PID control theory is applied in the slow loop to compensate the system inversion error. Finally, the validity of the control method is verified by the control law designing simulation of the flying wing aircraft.