FIELD: aircraft manufacturing. SUBSTANCE: proposed method and system relate to aircraft gas-turbine engines, namely, to rotating exhaust nozzles. Method provides control of displacement of three actuating mechanisms spaced over circumference and connected in corresponding places to drive ring set in preset position to control thrust vector in exhaust nozzle of gas-turbine engine. Angular position of each of places of connection of actuating mechanism on circumference is preset, and independent calculation of value of displacement for each actuating mechanism is carried out with use of places of connection in response to commands for turning around horizontal axis and turning around vertical axis. Then actuating mechanisms are set into action to provide displacement to set nozzle in preset position. Preferable version is setting of angular positions once and trigonometrical functions of angles corresponding to said angular position and calculated and kept in memory. Control system contains device for setting angular position of each place of connection of actuating mechanism on circumference, devices for independent calculation of value of displacement of each actuating mechanism and device for setting actuating mechanisms into action. EFFECT: reduced complexity of control algorithms, reduced necessity repeated calculations. 16 cl, 5 dwg
