A dynamic load damping apparatus is employed in a hydraulic steering system control circuit of an aircraft. The dynamic load damping apparatus is positioned in the hydraulic steering system control circuit in parallel with a control valve of the control circuit that functions as the hydraulic fluid source of the control circuit and an actuator that controls movements of a nose gear of the aircraft. The dynamic load damping apparatus dampens loads transmitted to the hydraulic actuator that controls the steering movements of the nose gear on the aircraft.

A shimmy damper for centering a landing gear includes a cap and a housing. The shimmy damper further includes a damper shaft extending from the cap to the housing. The shimmy damper further includes a plurality of magnets configured to exert an opposing force on the cap and the housing via the damper shaft, providing a centering mechanism of the damper shaft within the housing. This centering action in turn provides for the centering of the landing gear during flight.

An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element.

First and second portions of a spring are connected respectively to the upper element and to the lower element so that during movement in translation of the lower element relative to the upper element, the spring opposes any turning of the lower element relative to the upper element about said longitudinal axis.

A shimmy damper assembly may comprise: a damper piston including a piston head, the piston head comprising a first permanent magnet, a shimmy cylinder including a second permanent magnet disposed on an axial surface of the shimmy cylinder, and a gland nut coupled to the shimmy cylinder, the gland nut including a third permanent magnet spaced apart axially from the second permanent magnet, the piston head disposed between the first permanent magnet and the second permanent magnet.

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).

The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

A dynamic load damping apparatus is employed in a hydraulic steering system control circuit of an aircraft. The dynamic load damping apparatus is positioned in the hydraulic steering system control circuit in parallel with a control valve of the control circuit that functions as the hydraulic fluid source of the control circuit and an actuator that controls movements of a nose gear of the aircraft. The dynamic load damping apparatus dampens loads transmitted to the hydraulic actuator that controls the steering movements of the nose gear on the aircraft.

An example valve includes a housing, a sleeve disposed within the housing and having a first end and a second end opposite the first end, and the sleeve includes a plurality of sleeve protrusions at the first end and a plurality of fluid flow channels are formed between adjacent sleeve protrusions, a seal carrier disposed within the sleeve and having a carrier protrusion that extends from the second end of the sleeve and abuts against an interior surface of the housing, and an end cap mounted to the housing such that the plurality of sleeve protrusions abut against the end cap.

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.

A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.