Abstract: An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even.

Abstract: The invention concerns an actuating device (1) for moving a mobile cover of a thrust reverser, comprising: an actuator (5) comprising a first element (10), such as a screw, and a second element (12), such as a nut, mounted mobile device relative to the first element (10) such that the rotation of the first element (10) results in a translational movement of the second element (12) relative to the first element (10), and a locking device (31) comprising a rotating part (34) linked in rotation with the first element (10), and a locking part (35) that is mobile relative to the rotating part (34) between a locked position in which the locking part (35) is engaged with the rotating part (34) to prevent the first element (10) from rotating and an unlocked position in which the locking part (35) is disengaged from the rotating part to allow the rotation of the first element (10), and an electromagnet (39) for moving the locking part (35) to the unlocked position.

Abstract: The invention concerns an actuating device (1) for moving a mobile cover of a thrust reverser, comprising: an actuator (5) comprising a first element (10), such as a screw, and a second element (12), such as a nut, mounted mobile device relative to the first element (10) such that the rotation of the first element (10) results in a translational movement of the second element (12) relative to the first element (10), and a locking device (31) comprising a rotating part (34) linked in rotation with the first element (10), and a locking part (35) that is mobile relative to the rotating part (34) between a locked position in which the locking part (35) is engaged with the rotating part (34) to prevent the first element (10) from rotating and an unlocked position in which the locking part (35) is disengaged from the rotating part to allow the rotation of the first element (10), and an electromagnet (39) for moving the locking part (35) to the unlocked position.

Abstract: An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even.

Abstract: A damper circuit for damping a synchronous servo-motor having at least one winding, at least one main damper resistor, connection means for connecting the main damper resistor in series with the winding, and at least one additional damper cell including at least one additional damper resistor connected in parallel with the main damper resistor via a static switch connected to a control module for controlling the switch as a function of a voltage of the winding. The control module has a shunt in parallel with the main damper resistor. The shunt has an output connected to the control input of the switch and a divider bridge connected to the shunt to form a comparator between the voltage of the winding and a conduction voltage of the shunt.

Abstract: A damper circuit for damping a synchronous servo-motor having at least one winding, at least one main damper resistor, connection means for connecting the main damper resistor in series with the winding, and at least one additional damper cell including at least one additional damper resistor connected in parallel with the main damper resistor via a static switch connected to a control module for controlling the switch as a function of a voltage of the winding. The control module has a shunt in parallel with the main damper resistor. The shunt has an output connected to the control input of the switch and a divider bridge connected to the shunt to form a comparator between the voltage of the winding and a conduction voltage of the shunt.