A controlled flight into terrain remains a serious problem for the commercial and military aircraft. Necessity of monitoring the height and other parameters of movement during operations near the ground increases load on a pilot and diverts him from his specific tasks. So, the efficiency of the task implementation is reduced. It is difficult for a pilot to adequately estimate the degree of maneuverability and safety on a modern maneuverable aircraft. To improve the flight safety applies systems which warns the pilot of the ground proximity and performs an automatic collision avoidance maneuver. We have ground collision avoidance systems based on the trajectory prediction and calculation of the height lost during the automatic collision avoidance maneuver. The available dynamic characteristics of an aircraft should be taken into account for development of the control algorithms in such systems. The article deals with the synthesis of the control algorithms for performance of the automatic maneuvers intended to avoid collision with the ground in accordance with the current parameters of movement and maneuvering characteristics of the aircraft. Analysis was done of the influence of the parameters of the control algorithms in different initial conditions and different characteristics of g-load and roll angle control loops. The logic for selection of the direction of rotation to achieve the wings' level position in the shortest time was considered. The proposed algorithm is applied in the aircraft with control loops of g-load and roll angle.