UAV glider control system based on dynamic contraction method

In this article two control structures for UAV (Unmanned Aerial Vehicle) glider are presented. Both structures are using control law based on dynamic contraction method, both of these are of cascade structure. Presented control systems allow to control aircraft yaw angle and velocity with respect to air. One of them also allows to stabilize sideslip angle on values close to zero. Proper operation of suggested structures is checked by using numerical simulation prepared in Matlab environment.