Aircraft landing gear

1. An aircraft landing gear comprising:

a strut assembly ( 2 ) articulated to a structure of the aircraft,

a strut ( 3 ) sliding along an axis of sliding X in the strut assembly ( 2 ) and a free end of which carries at least one wheel ( 5 ),

a steering tube ( 4 ) mounted with the ability to rotate about the axis (X), and

a torque link ( 6 ) connecting the steering tube ( 4 ) and the strut ( 3 ) in terms of rotation,

the landing gear ( 1 ) additionally being equipped with a steering device ( 7 ) for orienting the at least one wheel ( 5 ) about the axis X, the steering device ( 7 ) comprising a body ( 8 ) in which is incorporated an electromechanical actuator ( 41 ) equipped with an electric motor ( 42 ) intended to drive the rotation of the steering tube ( 4 ) and therefore of the strut ( 3 ) in order to steer the at least one wheel ( 5 ),

the landing gear being further equipped with damping means intended to limit the transmission of vibration from the at least one wheel ( 5 ) to the rest of the landing gear when the aircraft is on the ground,

characterized in that the body ( 8 ) of the steering device ( 7 ) is mounted with the ability to rotate about the axis (X) with a limited amplitude of rotation, and

in that the damping means extend between the body ( 8 ) of the steering device ( 7 ) and the strut assembly ( 2 ) to damp the vibration between the body ( 8 ) of the steering device ( 7 ) and the strut assembly ( 2 ).

2. The aircraft landing gear according to claim 1 , in which the damping means comprise at least one hydraulic jack ( 15 ).

3. The aircraft landing gear according to claim 2 , in which the at least one hydraulic jack ( 15 ) comprises a body ( 17 ) connected to the body ( 8 ) of the steering device ( 7 ) and a piston ( 18 ) sliding in the body ( 17 ) of the at least one hydraulic jack ( 15 ) provided with a rod ( 19 ) articulated to the strut assembly ( 2 ) of the landing gear ( 1 ).

4. The aircraft landing gear according to claim 3 , in which a return spring ( 38 ) is incorporated into the body ( 17 ) of the at least one hydraulic jack ( 15 ).

5. The aircraft landing gear according to claim 3 , in which the strut assembly ( 2 ) is equipped with a bending bar ( 40 ), and in which the rod ( 19 ) of the piston ( 18 ) is articulated to the bending bar ( 40 ).

6. The aircraft landing gear according to claim 2 , in which the damping means comprise two pairs of hydraulic jacks ( 15 ) positioned relative to one another symmetrically about a vertical plane (P) passing through the axis X.

7. The aircraft landing gear according to claim 1 , in which the electromechanical actuator ( 41 ) of the steering device ( 7 ) is equipped with clutch means ( 45 ) designed selectively to couple an output shaft ( 48 ) of the electric motor ( 42 ) to the steering tube ( 4 ) or uncouple same therefrom.

8. The aircraft landing gear according to claim 1 , in which the steering device ( 7 ) comprises locking means ( 50 , 50 ′) for locking the at least one wheel ( 5 ) of the landing gear ( 1 ) in an angular position.

9. The aircraft landing gear according to claim 8 , in which the locking means ( 50 , 50 ′) comprise a lock ( 52 , 52 ′) designed to prevent the steering tube ( 4 ) from turning.

10. The aircraft landing gear according to claim 9 , in which the lock ( 52 , 52 ′) is a bistable lock.

11. The aircraft landing gear according to claim 9 , in which the lock comprises an electromagnet ( 53 , 53 ′).

12. The aircraft landing gear according to claim 9 , in which the locking means ( 50 , 50 ′) comprise a handle ( 59 , 59 ′) allowing the angular position of the at least one wheel ( 5 ) of the landing gear ( 1 ) to be unlocked manually.