Abstract: A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.

Abstract: A taxi drive system is disclosed that provides motive force to wheels of an aircraft. The motive force is transferred by a motor powered continuous track (e.g., belt, chain, or other flexible transmission element) directly to the wheel(s) of an aircraft. The system is carried by the landing gear of the aircraft, and is placed in engagement with an aircraft wheel with sufficient force to allow for the track to drive the aircraft wheel. The taxi drive system includes a separate motor from the main aircraft engines so that the aircraft may be taxied while the main engines are shutdown or at idle.

Abstract: A thermal actuator includes a piston slidingly within a cylinder. The piston cooperates with the cylinder to define a cavity. The piston also includes a rod extending away from the cavity. A magnetic field generator selectively imparts an alternating magnetic field to the cylinder, and inductively heats a heating element mounted within the cavity. The cavity also includes a volume of a phase-change material, which is melted by the heating element. The melting phase-change material expands to drive the rod from a retracted position to an extended position.

Abstract: A landing gear system includes an axle having an internal cavity and a wheel rotatably coupled to the axle. A drive shaft is mounted within the cavity to be rotatable about an axis. The landing gear system further includes a rod slidably mounted within the drive shaft and a clutch. The clutch has a first portion that is coupled to the rod and rotates with the drive shaft. A second portion of the clutch is fixedly coupled to the wheel. The rod selectively reciprocates along the axis between a first position and a second position to engage and disengage the clutch.

Abstract: A bushing is configured for installation in the hole of a lug, which has a protrusion extending radially inward from a surface of the hole. The bushing includes a first cylindrical body that is sized to be received within the hole of the lug. A flange extends radially outward from one end of the first cylindrical body, and a first recess is formed in the first cylindrical body to a radial face. The recess is sized and configured to receive the protrusion of the lug when the bushing is installed in the hole. Engagement of the protrusion with the recess preventing movement of the bushing relative to the lug.

Abstract: An aircraft landing gear assembly having a main strut pivotally coupled to an aircraft, a bogie beam pivotally connected to the main strut, a first axle mounted at the first end of the bogie beam and arranged to carry one or more first wheel assemblies and brake assemblies, each first brake assembly being attached to the bogie beam by a brake rod, and a second axle mounted at a second end of the bogie beam and arranged to carry one or more second wheel assemblies and brake assemblies. A double acting actuator is coupled between the strut and the bogie beam to apply a compressive or tensile force to the bogie beam. The ends of the bogie beam are arranged to position the bogie pivot axis below a plane intersecting the axes of rotation of the first and second wheel assemblies when the strut is in the deployed condition.

Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.

Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.

Abstract: An aircraft assembly having landing gear with a known deployment value, apparatus for permitting landing gear deployment, down-lock sensing apparatus, a navigation system, a landing gear control system, a flight control system, and a deployment controller. The deployment controller is configured to: calculate a touch down value using the aircraft position and speed information provided by the aircraft navigation system; command the landing gear control system to provide the deploy signal when the touch down value reaches a deployment threshold value which is greater than the landing gear deployment value; and command the flight control system to execute a landing abort sequence if the controller does not receive the down-lock signal from the landing gear sensing apparatus within a deployment value window which is greater than or equal to the known deployment value for the landing gear but less than the touch down value.

Abstract: Disclosed is an online platform for facilitating sharing of data between users. The online platform comprising a communication device, a processing device and a storage device. The communication device configured for transmitting a first account indicator associated with a first user account, receiving a first account selection, receiving a second user profile data associated with a second user account, transmitting the second user profile data, and receiving a modified second user profile data. The processing device is configured for creating an account connection between the first user account and the second user account, associating a copy of the second user profile data with the first user account. The storage device is configured for storing the account connection, storing the copy of the second user profile data and storing the modified second user profile data in association with the first user account.

Abstract: A shock absorber assembly having a wheel assembly including first and second coupling points, and first and second shock absorber elements. Each shock absorber element includes a housing portion defining a bore, and a rod slidably coupled within the bore such that the shock absorber element has a variable length. Each rod is coupled to a respective coupling point of the wheel assembly. The shock absorber assembly is arranged to maintain the relative positions of the first and second housing portions such that the longitudinal axis of the first bore has a generally fixed relationship with respect to the longitudinal axis of the second bore.

Abstract: An aircraft landing gear shock absorber assembly having an outer casing having a bore which extends through the outer casing. The bore has a first opening and a second opening. A rod is slidably coupled within the bore such that a first end of the rod projects out of the first opening of the bore, the first end of the rod being arranged to be attached to a wheel assembly. A closure is provided for the second opening of the bore. The bore has a reduced width portion relative to the second opening of the bore, and the rod includes a radially enlarged portion that is wider than the reduced width portion of the bore.

Abstract: An aircraft landing gear assembly includes a structural member coupled to another part by a joint including engagement formations or a relatively high friction coating arranged such that the joint inhibits pivotal movement of the structural member when the structural member is compressively loaded in an axial manner.

Abstract: A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. The cardan pin member has a cylindrical portion with a first recessed annular channel. The cardan pin member is retained in the socket by a ring assembly formed by two semi-annular ring members that slidably engages the first recessed channel. The ring assembly defines a second recessed annular channel. A collar is configured to be positioned over the second recessed channel, and to contract upon a change in temperature to lockingly engage the second recessed channel, to secure the split ring assembly in the first recessed channel.

Abstract: A brake rod assembly for an aircraft landing gear. The brake rod assembly includes a support member, a first brake rod having a first pivot point and a second pivot point, and a second brake rod. The support member is coupled to the first pivot point, the second brake rod is coupled to the second pivot point, and the first and second pivot points are longitudinally spaced apart along a first portion of the first brake rod.

Abstract: An aircraft landing gear assembly having a main strut configured to move between a deployed condition and a stowed condition, a damping device to oppose movement of the main strut as it approaches the deployed condition, a retraction actuator and a mechanical retraction linkage coupled between the aircraft and the main strut, and a locking device. The locking device is operable to change the retraction linkage between a locking condition in which the retraction actuator can apply a stowing force to the main strut through the retraction linkage to move the main strut from the deployed condition to the stowed condition, and an extensible condition in which the retraction linkage permits the main strut to be deployed by way of gravity.

Abstract: This application describes a handlebar and handlebar end assembly for effectively locking a handlebar end to a handlebar without the use of tools or instruments. The handlebar and handlebar end assembly according to an embodiment comprises a knob, threaded stud, non-threaded expansion retaining block, threaded expansion retaining block and handlebar. According to another embodiment, a wakeboard/water sports binding/boot attachment system for more securely attaching a wakeboard/water sports binding/boot to the ski/board is disclosed herein.

Abstract: A key fob associated with a select one of a plurality of driver profiles stored in a vehicle memory is provided. The key fob comprises a memory for storing a profile indication for identifying the driver profile associated with the key fob, and an output device for presenting the profile indication. Another embodiment provides a wireless system comprising a vehicle storing driver profiles in a memory, and a key fob associated with a select profile and comprising an output device for presenting a profile indication assigned to that profile. Another embodiment includes a method of providing a profile indication on a key fob associated with one of the driver profiles stored in the vehicle. The method comprises transmitting an identifier to the vehicle, receiving a profile indication associated with the identifier from the vehicle, and presenting the profile indication on an output device of the key fob.

Abstract: An aircraft landing gear assembly having a main strut pivotally coupled to an aircraft, a bogie beam pivotally connected to the main strut, a first axle mounted at the first end of the bogie beam and arranged to carry one or more first wheel assemblies and brake assemblies, each first brake assembly being attached to the bogie beam by a brake rod, and a second axle mounted at a second end of the bogie beam and arranged to carry one or more second wheel assemblies and brake assemblies. A double acting actuator is coupled between the strut and the bogie beam to apply a compressive or tensile force to the bogie beam. The ends of the bogie beam are arranged to position the bogie pivot axis below a plane intersecting the axes of rotation of the first and second wheel assemblies when the strut is in the deployed condition.

Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.