FIELD: transport.
SUBSTANCE: invention relates electric control system to be mounted in aircraft turbojet engine nacelle. Proposed control system comprises set of electromechanical elements (8a, 8b, 12, 14), arranged in auxiliary actuators of turbojet engine and electronic control unit (15). The latter incorporates a set of control inputs (16-21) to be connected to control elements (37-40) and set of outputs (25-27) connected to aforesaid electromechanical elements arranged in auxiliary actuators of turbojet engine. Electronic control unit can convert every received instruction into operating sequence of at least one electromechanical operating element. Proposed nacelle comprises at least one movable fairing intended for servicing purposes at least one thrust reverser with at least one movable casing, and electric control system. Aforesaid fairing and movable casing are displaces by at least one electromechanical element (8a, 8b, 12, 14). Proposed control system allows centralising of control jobs and operating steps for actuators of servicing fairing casing.
EFFECT: simplified design.
11 cl, 3 dwg
