초록 ▼

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 moto

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.

대표청구항 ▼

1. An aircraft comprising a nozzle of variable cross-section with a right movable part and a left movable part, each of which extend respectively over a right half and over a left half of a circumference of the nozzle and are movable in a direction of displacement parallel to a longitudinal directio

1. An aircraft comprising a nozzle of variable cross-section with a right movable part and a left movable part, each of which extend respectively over a right half and over a left half of a circumference of the nozzle and are movable in a direction of displacement parallel to a longitudinal direction of an engine to enable modification of the cross-section of the nozzle, the aircraft comprising: a control device comprising: a regulation system configured to regulate the engine connected to a control element,a first electric motor controlled by the control element which creates a movement of the right movable part by two mechanical transmission systems connected only to the first electric motor, a first mechanical transmission system being disposed close to a high generator of the nozzle and a second mechanical transmission system being disposed close to a low generator of the nozzle, anda second electric motor controlled by the control element which creates a movement of the left movable part by two mechanical transmission systems connected only to the second electric motor, a first mechanical transmission system being disposed close to the high generator of the nozzle and a second mechanical transmission system being disposed close to the low generator of the nozzle,wherein each of the first and second mechanical transmission systems respectively comprise a first stop and a second stop that delimit a travel of the right and left movable parts, so that the right and left movable parts alternately occupy first and second stable positions, the first stable position corresponding to a smallest cross-section of the nozzle when the first and second movable parts are in contact with the first stop, and a second stable position corresponding to a largest cross-section of the nozzle when the first and second movable parts are in contact with the second stop, andwherein the control device comprises a sensor for each stop delimiting the travel of the right and left movable parts, each sensor being configured to provide an indication to at least one of the regulation system and the control element that the right movable part, the left movable part, or both the right and left movable parts have reached one of the two stable positions. 2. The aircraft according to claim 1, wherein the control device comprises, for each movable part, a sensor which controls, measures, or controls and measures a real displacement of the movable part and informs the regulation system, the control element, or the regulation system and the control element. 3. The aircraft according to claim 1, wherein the control device comprises, for each movable part, a flexible coupling shaft interposed between each mechanical transmission system and a corresponding motor. 4. The aircraft according to claim 1, wherein the control device comprises, for each nozzle, an immobilizer of all movable parts deactivated solely when the regulation system controls the change of position of the first movable part, the second movable part, or the two movable parts. 5. The aircraft according to claim 4, wherein the immobilizer comprises a brake for each electric motor. 6. The aircraft according to claim 5, wherein the control element comprises, for each brake, a relay which enables reception of a signal to deactivate the brake.