Adaptive Super Twisting Sliding Mode Control for Flying-Wing UAV

Aiming at the attitude control problem of flying-wing UA V, an adaptive super-twisting non-singular fast terminal sliding mode control law is proposed. Flying-wing UAVs are pool in static stability due to the cancellation of the flat tail and vertical tail, which brings great challenges to the attitude control of flying-wing UAVs. Therefore, the non-singular fast terminal sliding mode control method is used for control. At the same time, using the improved super-twisting algorithm to attenuate the chattering, an adaptive super-twisting non-singular fast terminal sliding mode control law is designed: the finite-time convergence of the closed-loop system is proved using Lyapunov stability theory; Finally, through simulation analysis, it is proven that the adaptive super-twisting non-singular fast terminal sliding mode control law proposed in this paper has a better control effect. Compared with the traditional sliding mode method, the control is smoother and can suppress disturbance effectively and weaken chattering.