Abstract: A damper for an aircraft landing gear includes a housing with an internal cavity. A weight is slidingly disposed within the cavity and positioned between and engages a first pneumatic spring and a second pneumatic spring. The shimmy damper includes at least one mounting feature to fixedly mount the housing to a component of the aircraft landing gear.

Abstract: An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground.

Abstract: A hydraulic shimmy damper that resolves drawbacks in several known shimmy dampers, such as damping characteristics that are dependent on oil temperature variations. The disclosed shimmy damper includes a hydraulic compensator (40) having an internal fluid volume that is significantly more important than a fluid volume expelled from the body of the shimmy damper when its piston moves fore and aft. The shimmy damper also includes a hydraulic manifold (30) arranged between the body and the hydraulic compensator and defining a transfer channel between chambers in the piston that is connected to the hydraulic compensator. The manifold receives interchangeable hydraulic cartridge-type valves (CV1,RV1; CV2,RV2) for metering the fluid flowing from the chambers to the transfer channel, and allows the fluid to freely enter the chambers from the transfer channel. The present shimmy damper is therefore much less sensitive to oil temperature variation under intense shimmy.

Abstract: An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels.

Abstract: A locking mechanism for locking an actuator piston within an actuator cylinder housing is disclosed. The locking mechanism comprises a locking pin that is moveable between extended and retracted positions. The locking pin can be moved using a controller, such as a hydraulic controller, for example. In the extended position the locking pin engages the actuator piston thereby locking the actuator piston in a specific position. The locking mechanism includes a mechanical bias (such as a spring or other mechanical system) that biases the locking pin towards an extended position to lock the actuator piston when counter-pressure on the locking pin is lower than the pressure provided by the mechanical bias. The locking pin can be hydraulically operated so that hydraulic pressure that forces the actuator piston to retract also exerts force on the locking pin to move it from a locked position to an unlocked position.

Abstract: An aircraft landing gear assembly comprising a bogie beam (2), an axle (4) extending through the bogie beam and a jacking dome fitting (6) extending through a sidewall (8) of the bogie beam and arranged to transfer vertical loads applied to the jacking dome fitting to the axle.

Abstract: A mechanical position indicator for providing a visual indication that a first part of an aircraft landing gear has assumed a predetermined position relative to a second part, the position indicator being arranged to be coupled to a first one of the first and second parts and in a first state arranged to hold an indicator element in a deployed position, the position indicator being arranged such that upon the first part assuming the predetermined position relative to the second part, a second one of the first and second parts changes the position indicator from the first state to a second state in which the indicator element is displaced from the deployed position, the position indicator being arranged to inhibit the indicator element thereafter returning to the deployed position.

Abstract: An aircraft landing gear including: a main strut having an upper portion arranged to be coupled to the underside of an aircraft and a lower portion telescopically mounted with respect to the upper portion; a bogie including a bogie beam pivotally coupled to the lower portion of the main strut, the bogie beam having a plurality of axles mounted on it, each axle carrying one or more wheel assemblies; an actuator arranged such that a change in its effective length causes a change in the angular position of the bogie relative to the main strut, and a control port arranged to be coupled to a control fluid supply system, wherein the aircraft landing gear includes or is in combination with a control valve having a first configuration in which it permits control fluid to be supplied to the control port of the actuator at a first pressure and a second configuration in which the control valve permits the supply of control fluid to the control port at a second pressure less than the first pressure so as to reduce loads

Abstract: An aircraft landing gear having a strut having an upper portion for mechanically coupling to an aircraft and a lower portion movably mounted with respect to the upper portion. A bogie beam is pivotally coupled to the lower strut. A bogie control linkage is mechanically coupled to the bogie at a first connection point, and to the strut at a second connection point. The bogie control linkage has: an actuator including a locking system that inhibits actuation of the actuator; a sensor linkage mechanically coupled to the lower strut and arranged to change between first and second conditions in accordance with movement of the upper strut relative to the lower strut; and an actuator control linkage arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition.

Abstract: Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.

Abstract: A landing gear assembly for an aircraft, the landing gear assembly including: an elongate bogie beam; a first axle bearing having an outer part rotatably coupled to an inner part, the outer part being coupled to the bogie beam, the inner part including a mounting aperture; and an elongate axle provided through the mounting aperture of the inner part and coupled thereto, wherein the axle is coupled to the inner part of the first axle bearing in a configuration such that the longitudinal axis of the axle is spaced from the axis of rotation of the inner part, such that rotation of the inner part causes a change in the orientation of the axle relative to the bogie beam.

Abstract: A landing gear (10), including: a bogie beam (12); an axle (14) pivotally connected to the bogie beam (12); a locking member (40) coupled to the axle (14) such that movement of the axle (14) invokes movement of the locking member (40), said movement of the locking member (40) defining a swept volume; and a locking mechanism (60) coupled to the bogie beam (12) and including first (65a) and second glide members, (65a, 65b) the locking mechanism (60) being arranged to move the glide members (65a, 65b) between locking positions, where glide members (65a, 65b) are within the swept volume on opposing sides of the locking member (40) and in which position the locking mechanism (60) is arranged to lock the locking member (40) in a predetermined position, and non-locking positions, where the locking mechanism (60) is arranged permit movement of the locking member (40).

Abstract: A brake assembly for a vehicle comprising a wheel comprising a hollow section and a rim, the rim comprising a first portion comprising an electrically conductive material and a second portion adjacent to the first portion comprising a plurality of a permanent magnets and a stator comprising at least one electromagnetic coil arranged to be located within the hollow section of the wheel, wherein the stator is moveable between a first position in which the at least one electromagnetic coil is inductively coupled to the first portion of the rim when the wheel is rotating relative to the stator, and a second position in which the at least one electromagnetic coil is inductively coupled to the second portion of the rim.

Abstract: An apparatus includes a fitting connected to a body. The fitting has an engagement portion including a channel formed into a peripheral surface of it and an axis. The body includes an axial layer provided around at least some of the peripheral surface of the engagement portion of the end fitting and a hoop layer provided around the axial layer at a location corresponding to at least some of the channel so as to urge at least some of the axial layer into a portion of the channel. The channel is arranged such that at least some of it defines a pathway that is non-orthogonal with respect to the axis of the fitting, such that at least some of the surface area of the channel defines a load bearing surface for the transfer of torque between the fitting and body when a rotational force is applied to one of them.

Abstract: An aircraft landing gear including a fairing (12) arranged to be moveable between first and second configurations, wherein in the first configuration the fairing shields an element of the landing gear from an incident airflow, the fairing being arranged to be in the first configuration when the landing gear is deployed but unloaded, and wherein in the second configuration the fairing exposes the landing gear element to the incident airflow, the fairing being arranged to be in the second configuration when the landing gear is deployed and loaded.

Abstract: Aircraft landing gear including an axle pivotally connected to a bogie beam and a locking device. The locking couples the axle to the bogie beam, and has a movable member and a follower. The movable member is movable between first and second configurations. Movement of the movable member towards the second configuration causes corresponding movement of the follower so as to transfer a steering force to the axle through the follower which causes the axle to rotate in a first direction. With the movable member in the first configuration, the follower is in a first configuration that inhibits the movable member being moved by an external force applied to the axle. With the movable member in the second configuration, the follower in a second configuration that permits the movable member to be moved by an external force applied to the axle.

Abstract: A stop pad (11) for an aircraft landing gear arranged to provide protection against impact between first and second elements of the landing gear, the stop pad being arranged to provide an indication that it is been subject to an impact against one of the first or second landing gear elements, the impact having an impact load above a predetermined threshold level.

Abstract: An aircraft landing gear includes at least one load bearing longitudinal structural element. The longitudinal structural element is hollow and is arranged to have a non-structural element located inside.

Abstract: An aircraft landing gear having a strut having an upper portion for mechanically coupling to an aircraft and a lower portion movably mounted with respect to the upper portion. A bogie beam is pivotally coupled to the lower strut. A bogie control linkage is mechanically coupled to the bogie at a first connection point, and to the strut at a second connection point. The bogie control linkage has: an actuator including a locking system that inhibits actuation of the actuator; a sensor linkage mechanically coupled to the lower strut and arranged to change between first and second conditions in accordance with movement of the upper strut relative to the lower strut; and an actuator control linkage arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition.

Abstract: A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manual rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators.