Aircraft landing gear (1) comprising: an axle shaft (2); a strut (3) extending along a main strut axis (Z) and having a first part (3a) carrying the said axle shaft (2) and a second part (3b); a main damper (5) designed to damp axial movements of the first strut part (3a) with respect to the second strut part (3b); a first secondary damper (6a) distinct from the said main damper and designed to damp a movement of angular oscillation, about the axis (Z). The first secondary damper (6a) is carried by the first strut part (3a) and comprises: an inertial mass (M); and means (7a) of connecting the inertial mass (M) to the first strut part (3a) which means are designed to damp rotational movements of this inertial mass (M) about the axis (Z).

An example aircraft includes (i) a landing gear having a chassis, an axle, and wheels mounted to ends of the axle; (ii) a hydraulic actuator including a cylinder, a first piston coupled to the chassis, and a second piston coupled to the axle; and (iii) a directional control valve including: inlet ports configured to be fluidly coupled to a source of pressurized fluid, tank ports configured to be fluidly coupled to a tank, and workports configured to be fluidly coupled to the hydraulic actuator.

A landing gear (10) includes: a wheel support member (16) including a first portion for rollably supporting a wheel (14), and a second portion extending from the first portion toward a fuselage (12) in a direction of an axis of the first portion and supporting the first portion such that the first portion is rotatable about the axis; a swing support member for supporting the second portion of the wheel support member (16) such that the second portion is swingable relative to the fuselage (12); a retraction actuator (42) for swinging the wheel support member (16) to retract the wheel (14) into the fuselage (12) and deploy the wheel (14) from the fuselage (12); a brace (22) attached to the fuselage (12) and supporting the wheel support member (16); and a joint (20) connecting the brace (22) to the first portion of the wheel support member (16). The joint (20) is disposed closer to the wheel (14) than to the swing support member.

A damper is provided for responding to relative movement of arms to which the damper is coupled. The damper includes a member, springs, a first housing and a second housing. The first housing includes a first body and first bellows affixed to the member and the first body by first joints to define a first interior. The second housing includes a second body and second bellows affixed to the member and the second body by second joints to define a second interior. The first and second interiors are configured to contain fluid charged therein and the member is configured to permit bi-directional flows of the fluid between the first and second interiors responsive to the relative movement of the arms and in opposition to an elasticity of the springs.

A torque link assembly for an aircraft landing gear comprising: an upper torque link; a lower torque link; a joint pin arranged to pivotally couple the upper torque link and lower torque link; an electric motor assembly; a sensor arranged to detect movement of the upper torque link or lower torque link and in response to detecting the movement providing a control signal to the electric motor assembly, wherein the electric motor assembly is configured to linearly translate the joint pin with respect to one of the upper or lower torque links.

To provide a safety device that, when a crosswind is present, allows an aircraft to more safely land on a runway in an airport. This safety device 10 for landing in a crosswind is designed for landing of an aircraft 1 on a runway 3 in a crosswind across the runway 3, and provided with a control unit 14 for controlling, when the nose cone 1T of the fuselage 8 of the aircraft 1 is directed windward, the orientation of the wheels of the aircraft 1 such that the wheels are oriented in the direction of travel of the aircraft 1.

A damper is provided for responding to relative movement of arms to which the damper is coupled. The damper includes a member, springs, a first housing and a second housing. The first housing includes a first body and first bellows affixed to the member and the first body by first joints to define a first interior. The second housing includes a second body and second bellows affixed to the member and the second body by second joints to define a second interior. The first and second interiors are configured to contain fluid charged therein and the member is configured to permit bi-directional flows of the fluid between the first and second interiors responsive to the relative movement of the arms and in opposition to an elasticity of the springs.

A method for health monitoring of a damper associated with a landing gear is described which includes receiving sensor data from a pressure transducer and an accelerometer and optionally a thermal sensor operably mounted on or near the damper, a computer system, and applying, using the computer system, a diagnostic algorithm to the sensor data to induce and predict the health of the damper.

A landing gear control apparatus for an air mobility vehicle may include a shaft of the landing gear control apparatus, the shaft deployed when the air mobility vehicle is landing or driving; a tire provided at one end portion of the shaft; a steering rod coupled to the shaft in a direction crossing a longitudinal direction of the shaft to steer the tire by rotating the shaft; a rotation load sensor mounted on the steering rod and sensing a rotation load applied to the steering rod; a MR damper coupled to the shaft to surround thereof, having a MR fluid filled in the damper, and configured for changing, by the controller, a damping force of the MR damper for rotation of the shaft according to a current applied to the MR damper; and a controller for controlling a current applied to the MR damper on the basis of the rotation load detected by the rotation load sensor.

The invention relates to an aircraft undercarriage comprising: a strut (1) for connecting to the aircraft, a slide rod (3) slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm (7) carried by a support (8) attached to the top wall of the strut to cooperate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C1) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C2) above the diaphragm and partially filled with hydraulic fluid, a throttle needle (10) secured to the slide rod and penetrating into a calibrated orifice (12) in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut. According to the invention, the undercarriage includes at least one vane (20) fastened to the end of the throttle needle in order to extend inside a portion of the second chamber that is filled with hydraulic fluid.