Actuator for aircraft turbine engine nacelle with notably one-piece annular rear part
An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.
1. An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, said actuator disposed between a stationary part of said engine nacelle and said annular rear part of the engine nacelle, said actuator comprising:
an engine assembly comprising a nut which rotates, without translational movements along a longitudinal axis of said engine nacelle, and means for turning said nut; and
a screw assembly comprising a screw translating, without rotating, along the longitudinal axis, in mesh with said nut and a ball joint at one end of said screw fixed to said annular rear part,
wherein the screw assembly extends essentially upstream the nut when the actuator is in a retracted position, and
wherein the screw is configured to switch between a first position in which the ball joint is practically in contact with the nut, and a second position in which the ball joint is distant from the nut by a length that is substantially equal to the length of the screw.
2. The actuator according to claim 1 , wherein said engine assembly comprises a support and a casing fixed on said support and enclosing said nut.
3. The actuator according to claim 2 , further comprising a protective tube fixed on said support, said protective tube containing said screw when the actuator is in a retracted position.
4. An aircraft turbine engine nacelle with a one-piece annular rear part, said engine nacelle comprising a plurality of actuators according to claim 1 , wherein said engine nacelle comprises an uppermost beam, and said annular rear part of the engine nacelle is slidingly mounted on rails disposed on either side of the uppermost beam.
5. The aircraft turbine engine nacelle according to claim 4 , wherein said actuators are mounted on each side of the uppermost beam, in the vicinity of said rails.
6. A propulsion assembly, comprising the aircraft turbine engine nacelle according to claim 4 and a turbine engine placed inside said engine nacelle.