Abstract: A wheel retaining assembly for a landing gear having an axle and an outer wheel bearing, the axle defining an axial direction along an axial centerline, is disclosed. In various embodiments, the wheel retaining assembly includes a first wheel spacer configured to slide over the axle and to abut the outer wheel bearing, the first wheel spacer having an axially outward portion; and a second wheel spacer configured to slide over the axle, the second wheel spacer having an axially inward portion configured to engage the axially outward portion of the first wheel spacer.

Abstract: Methods of designing and producing a connecting rod using carbon fiber reinforced epoxy molding compound composite material are provided, such that the method allows connecting rod designer to machine several different connecting rod designs, lengths, and beams. The material is molded into a near-net shape. After molding, the blank is machined into the final shape of a connecting rod and the material is sealed.

Abstract: A retainer for a segmented annular heat shield of a wheel includes a first end, a second end opposite the first end, and a body extending between the first end and the second end. Both the first end and the second end are configured to be coupled to at least one of the wheel and a torque bar. Further, the body includes opposing longitudinal sides configured to respectively engage and secure a respective heat shield segment of the segmented annular heat shield. Also, the retainer includes a cover coupled to and extending over at least the body, with an air gap being defined between the body and the cover.

Abstract: An actuation mechanism for a multi-plate disc brake includes an energy storage element configured to apply said disc brake, the energy storage element being movable between a first position where said disc brake is released, and a second position where said disc brake is applied; a force transmission path configured to transmit force from the energy storage element to apply said disc brake; and a hydraulic chamber. The force transmission path includes a first member and a second member arranged in series; wherein the hydraulic chamber is configured, when pressurized, to act on the first member such that the energy storage element is moved to the first position; and wherein the second member is separated from the chamber such that, when the chamber is pressurized, no pressure is applied to the second member.

Abstract: In some examples, an assembly includes a vehicle wheel that defines an interior and an exterior surface, where the interior surface defines a first protrusion and a second protrusion. The first protrusion defines a first aperture extending in a substantially axial direction. The assembly further includes a rotor drive key on the interior surface, the drive key defining a first and second feature, and the first feature defines a second aperture extending in the substantially axial direction and is configured to align with the first aperture. The assembly includes a fastener configured to be inserted through the first and second aperture in the substantially axial direction to attach the key to the interior surface of the wheel, where the second aperture is configured to form a threaded connection with an end of the fastener. When the fastener is tightened via the threaded connection, the second feature engages the second protrusion.

Abstract: A wheel assembly includes a wheel portion comprises a web having an inboard surface. The web may define a torque bar retention slot that extends from the inboard surface of the web. The wheel assembly may also include a bushing disposed in the torque bar retention slot, wherein the bushing comprises an open end and a closed end. Still further, the wheel assembly may include a torque bar coupled to the wheel, and the torque bar may include a boss extending into the bushing through the open end of the bushing such that the boss of the torque bar is at least partially disposed within the torque bar retention slot of the wheel portion.

Abstract: A hybrid torque tube for a brake assembly may comprise a tube portion having a centerline axis, and a conical back-leg portion extending from the tube portion. A stator spline may be formed on a radially outward surface of the tube portion. A foot may be formed on a radially inward surface of the tube portion. The tube portion is formed using a first manufacturing process and at least one of the conical back-leg, stator spline, or foot is formed using additive manufacturing.

Abstract: A method for controlling a separation between rotational axes of a pair of meshing gears is disclosed. A parameter indicative of a transmission error through the gears is measured and the separation is controlled, aiming to minimise variations in the measured signal. This acts to reduce variations in transmission error and the related vibrations created in the drive system and in the surrounding components. A related drive system and aircraft landing gear are described.

Abstract: Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, a system may comprise an electric motor and a clutch. The electric motor may include a first output shaft and a second output shaft. The clutch may selectively engaging the motor to at least one of a driver transmission and a brake transmission, wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft, wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack.

Abstract: An aircraft landing gear wheel is disclosed. A main body includes a hub portion with a gear end and an attachment end. A driven gear portion includes a first annular rail and a second annular rail, the driven gear portion being integrally and drivingly connected with the hub portion at the gear end. Rollers are rotatingly connected between roller apertures of the first annular rail and the second annular rail. Bearings rotatingly support portions of the rollers within the roller apertures.

Abstract: An aircraft wheel equipped with rotational drive (10) attached to clevises (19) projecting from a flank of a rim (5) of the wheel. The drive comprises a ring (11) able to cooperate with a drive actuator and is provided with members (12) for attaching to the clevises of the rim such that, between two attachment members, the ring forms a flexible and deformable segment.

Abstract: A bearing arrangement for an aircraft landing gear wheel is provided that effectively supports the wheel on an axle while maximizing internal wheel volume available for mounting non-engine drive means used to power the wheel and/or brakes or other structures within the maximized wheel volume. The bearing arrangement is preferably employed with a two-part aircraft wheel mounted on a landing gear axle and includes bearing structures located only on wheel sections adjacent to the axle. A specifically configured cantilevered joint portion of inboard and outboard wheel sections supports weight and loads bearing structures, eliminating the need for and space required by a high speed bearing. Stiffness necessary for strength and structural integrity is provided by the materials selected to form the wheel sections.

Abstract: A wheel bearing for aircraft, that has a long service life and is reliable. The wheel bearing has a small number of individual parts and components that are simple to handle, to mount or to dismount. The wheel bearing of an aircraft landing gear has a wheel rim that is rotationally mounted about an axis over two roller bearings of a bearing arrangement. The external rings of the roller bearings are received together in a single-piece external ring bearing housing. The wheel rim can be detachably connected to the bearing arrangement in such a manner that it can be mounted or dismounted independently from the bearing arrangement.

Abstract: A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), is characterized in that the drive unit (16) comprises at least one power output assembly (122, 124) for driving at least one of the first and second wheels (4, 6), with each of the at least one power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a sprocket element (108, 110) coupled to one of the first and second wheels (4, 6).

Abstract: A heat shield segment includes at least one tab extending from an outboard end, the tab adapted to secure the heat shield segment against radial and axial movement. The at least one tab is received over a retaining ring positioned within a tube well of a wheel. The retaining ring is received in recesses formed in the inner surface of drive keys spaced around the interior of the tube well. The heat shield segment is secured at the inboard end by a fastener, and is spaced from the tube well by a spacer positioned between the heat shield segment and the tube well. The at least one tab of the heat shield segment allows for easy assembly and maintenance of the heat shield assembly formed by a plurality of the heat shield segments.

Abstract: Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, system comprising an electric motor coupled to a first transmission, a first clutch for selectively engaging the first transmission to a propulsion transmission and a brake damping system, wherein, in response to engagement with the propulsion transmission, the electric motor drives an aircraft wheel, wherein, in response to engagement with the actuator ram, the electric, motor drives the brake clamping system to apply force to an aircraft brake disk stack.

Abstract: A method is provided for optimizing requirements for brake size, complexity, and heat dissipation capability in an aircraft, wherein the aircraft is powered during ground travel by an onboard wheel drive assembly, including controllable drive means, mounted on at least one aircraft wheel, and ground travel is controlled by the pilot to move the aircraft on the ground without relying on the operation of the aircraft engines, while substantially minimizing brake use between landing and takeoff. Brakes can be optimally sized and configured to meet landing and taxi requirements, resulting in reduced brake size and complexity and increased effective heat dissipation. Substantially minimizing brake use during taxi produces improved brake cooling, substantially eliminating delays caused by slow brake heat shedding and enables rapid aircraft turnaround between landing and takeoff.

Abstract: The invention relates to a bar for an aircraft wheel, the bar comprising an oblong body (2) extended at each end by respective endpieces (4, 5) extending parallel to the body and parallel to each other, the endpieces being offset relative to each other. The invention also relates to a wheel specially adapted to receive such a bar.

Abstract: The invention relates to a system for motorizing a wheel (2), the system comprising a motor unit (4), a drive member (6) secured to the wheel (2) and a clutch device (7) connects the output shaft (8) of the motor unit (4) to the drive member (6). According to the invention, the motor unit (4) comprises an electric motor (11) and is carried by an unsprung part of a suspension strut (3) of an aircraft so that the latter can be made to move along the ground.

Abstract: The two-piece wheel rim assembly includes first and second hub sections affixed together and rotatably mounted on an axle by a set of bearings which are longitudinally spaced apart on the axle. The hub sections have radially inboard wall segments and radially outboard segments. The inboard segments form a radial cavity about the axle longitudinally bounded by the bearings. An oil bath substantially fills the radial cavity except for a small thermal expansion air pocket. The thermal expansion air pocket is positioned above the axle and the bearings when the hub-tire combination is in use. The thermal expansion air pocket has a nominal size only sufficient to account for thermal expansion and contraction of the wheel.

Abstract: The invention provides an aircraft wheel-and-brake set, the wheel including a rim mounted to rotate on an axle of the aircraft about an axis of rotation, and the brake including a stack of disks extending into the rim in service, and a support carrying brake actuators facing the stack of disks in order to selectively press said disks together, wherein the support carries at least one rotary drive member for driving the wheel in rotation, which drive member is carried in such a manner that it extends outside said wheel.

Abstract: The invention relates to a bar for an aircraft wheel, the bar comprising an oblong body (2) extended at each end by respective endpieces (4, 5) extending parallel to the body and parallel to each other, the endpieces being offset relative to each other. The invention also relates to a wheel specially adapted to receive such a bar.

Abstract: An aircraft wheel assembly includes a wheel (12) and a beam key (40) mounted on the wheel (12). The beam key (40) includes a body (46) having first and second longitudinally spaced ends (42, 44), an upper side (48), and a lower side (52) having a first surface (53), and a bore (60) having a first end opening (66) in the first surface and a second end opening (64). The wheel (12) includes a centerline (20), an opening (18) for receiving the body first end (42), a second surface (26) angled with respect to the centerline (20), and a wheel bore (30) coaxially aligned with the beam key bore (60) when the body first end (42) is received in the opening (18), the wheel bore (30) having a first end opening in the second surface (28). A spacer (70) must be included between the beam key (40) and the wheel (12).

Abstract: A steel member (10) having wear and corrosion resistance through a combination of coatings is disclosed, the steel member (10) being a hardened and tempered steel member having a high tensile strength, at least one selected portion (18) of the steel member (10) coated by thermal spraying with a tungsten carbide-cobalt composition (22) to provide wear and corrosion resistance, the tungsten carbide-cobalt composition (22) being approximately 78-90% tungsten carbide and approximately 10-19% cobalt, and a sacrificial ceramic-metallic coating (24) on the steel member (10) to provide corrosion resistance for the steel member (10). A method of coating a steel member (10) is also disclosed.

Abstract: Apparatus and methods to balance a wheel which rotates around an axle. The wheel has a rim having an outer surface and an opposite interior surface positioned circumferentially around the axle. A plurality of rotor drive keys are mounted at the interior surface of the rim. At least one rotor drive key having a different weight than the other rotor drive keys is mounted approximately opposite an abnormal weight in order to balance the wheel.

Abstract: A heat shield assembly for a wheel and brake assembly includes one or more torque bars that include a coupling device which cooperates with a portion of a heat shield (and more particularly heat shield sections) at a location axially outwardly remote from the inboard end of the heat shield so as to restrain radial outward movement of the heat shield. In another embodiment, the heat shield assembly includes heat shield carriers between which respective heat shield sections are axially inserted, and retainers are removably secured with respect to the carriers for blocking axial withdrawal of the heat shield sections from respective carriers. In another embodiment, heat shield carriers include a reversely bent edge portion defining a capture slot, and at least one aperture in the bent edge portion. A heat shield section has at one side thereof a first tab portion circumferentially inserted in the capture slot and at an opposite side thereof a second tab portion engaged in the aperture.

Abstract: An aircraft brake assembly incorporating components which are sensitive to heat and to contact with substances present in runway,.e.g., de-icer compositions and cleansing liquids. The assembly includes an external member to shield the components from the liquids. The external member may comprise a rigid or flexible, fluid-impermeable or porous material located to receive and retain the liquids. Heat generated through the use of the brake assembly may evaporate any liquid settled on the external member or at least discourage any liquid from settling thereon.