Abstract: The invention provides a method of mounting an aircraft wheel drive member (30) on an undercarriage having an axle (1) that carries the wheel and that is provided with a torque plate (3) having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support (10) that bears against an inside face of the torque plate opposite from its outside face against which a brake (2) is fitted, and of fitting the drive member on the support.

Abstract: The invention relates to an aircraft landing gear equipped with a steering device (7) for orienting the wheels (5), the steering device (7) comprising a body (8) in which is incorporated an electromechanical actuator (41) equipped with an electric motor (42). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel (5) to the rest of the landing gear (1) when the aircraft is on the ground. The body (8) of the steering device (7) is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body (8) of the steering device (7) and the strut assembly (2) of the landing gear to damp the vibration between the body (8) of the steering device (7) and the strut assembly (2).

Abstract: Aircraft undercarriage leg including an axle (3) that bears at least one wheel (4), the undercarriage leg being equipped with a unit (6) for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support (12) extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.

Abstract: A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

Abstract: The invention relates to an aircraft landing gear equipped with a steering device (7) for orienting the wheels (5), the steering device (7) comprising a body (8) in which is incorporated an electromechanical actuator (41) equipped with an electric motor (42). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel (5) to the rest of the landing gear (1) when the aircraft is on the ground. The body (8) of the steering device (7) is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body (8) of the steering device (7) and the strut assembly (2) of the landing gear to damp the vibration between the body (8) of the steering device (7) and the strut assembly (2).

Abstract: Aircraft undercarriage leg including an axle (3) that bears at least one wheel (4), the undercarriage leg being equipped with a unit (6) for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support (12) extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.

Abstract: An electromechanical actuator comprising an electric motor (11) for driving an output shaft (4) in rotation via a reduction gear (20) and passive regulation stage (30) allowing for control of the speed of rotation of the output shaft. A braking member is arranged between an output of the reduction gear and the output shaft to be driven, the braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft. The braking member is of hydraulic type and comprises a paddle (33) for transferring fluid between two chambers (34, 35) under the effect of the rotation of the output shaft, transferred fluid passing through a selective drawing member (41) which, depending on the direction of rotation of the actuator, opposes two distinct resistances to the decantation of the fluid from one chamber to the other.

Abstract: A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

Abstract: The invention provides a method of mounting an aircraft wheel drive member (30) on an undercarriage having an axle (1) that carries the wheel and that is provided with a torque plate (3) having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support (10) that bears against an inside face of the torque plate opposite from its outside face against which a brake (2) is fitted, and of fitting the drive member on the support.

Abstract: A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.

Abstract: The present invention relates to an electromechanical actuator comprising an electric motor (11) for driving an output shaft (4) in rotation via a reduction gear (20) and passive regulation means (30) allowing for control of the speed of rotation of the output shaft, and comprising a braking member (30), arranged between an output of the reduction gear and the output shaft to be driven, said braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft, characterized in that the braking member is of hydraulic type and comprises fluid decantation means (33) between two chambers (34, 35) decanting under the effect of the rotation of the output shaft through a selective drawing member (41) which, depending on the direction of rotation of the actuator, opposes two distinct resistances to the decantation of the fluid from one chamber to the other.

Abstract: A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.