Abstract: A variable cross-section nozzle of an aircraft has at least two movable parts enabling modification of the cross-section of the nozzle. A control device for the nozzle includes a system for regulating the engine, the system being connected to a control element which drives at least one electric motor which creates the movement of the movable parts, including an electric motor for each movable part and two mechanical transmission systems for each movable part connected only to the same electric motor.

Abstract: The invention relates to a control device of a nozzle of variable cross-section of an aircraft comprising at least two movable parts enabling medication of the cross-section of the nozzle, the control device comprising a system for regulation of the engine connected to a control element which drives at least one electric motor which creates the movement of the movable parts, wherein it comprises an electric motor for each movable part and two mechanical transmission systems for each movable part connected only to the same electric motor.

Abstract: The invention relates to a control device of a nozzle of variable cross-section of an aircraft suitable for providing a three-phase AC electrical power supply, the nozzle of variable cross-section comprising one or more movable parts which make it possible to modify the cross-section of the nozzle, the control device comprising a system for regulation of the engine connected to a control element which drives at least one electric motor which by a mechanical transmission system creates the movement of the movable part or parts, wherein the electric motor is configured to use directly the electrical power supply of the aircraft and in that the control element comprises analogue type structure to switch the phases of the electrical power supply to modify the direction of rotation of the electric motor.