The present invention provides a wheel hub for a vehicle, including: a) a wheel axle defining an axis of rotation for the wheel; b) a hub body rotatably coupled to the axle for rotation about the axis of rotation, the hub body defining an internal cavity; and, c) a braking assembly, including: i) at least one first annular plate disposed within the internal cavity about the axle, the at least one first annular plate rotatably fixed with respect to the hub body so as to rotate therewith about the axis of rotation; ii) at least one second annular plate disposed within the internal cavity about the axle and adjacent to the at least one first annular plate, the at least one second annular plate rotatably fixed with respect to the axle, and at least one of the first and second annular plates being slidably movable within at least part of the internal cavity; and, iii) an actuator disposed within the internal cavity and configured in use, to cause an axial load to be applied to the slidably movable plate to thereby cause the at least one first and second annular plates to frictionally engage thereby applying a braking load between the hub body and wheel axle so as to brake the wheel of the vehicle.

The invention relates to a braking device (1) of an aircraft wheel, comprising a ring (15) which has a plurality of cavities (17) in which actuators (18) are fitted in order to apply a braking force to a stack of discs (11) which extend opposite the ring. The ring is provided with a heat shield (25) which extends opposite a face of the ring directed towards the stack of discs in order to protect the ring from thermal radiation which is generated by the stack of discs.

According to the disclosure, the heat shield is provided with holes (26) through which the actuators extend and which have a sectional profile which is formed to reflect the thermal radiation away from the device.

A disc brake for a vehicle, having a first and a second brake lining (2a), and a brake disc (1) which is arranged between them, and a brake calliper which engages over the brake disc (1) with a brake calliper housing (6), in which a brake application device is arranged, wherein the brake application device comprises a pressure piece (3) which can be applied against the first brake lining (2a), wherein a boot (5) is provided for protecting the interior of the brake calliper housing against contaminants, wherein the boot (5) is fastened by way of a first end region (5a) to the brake calliper housing (6) and by way of a second end region (5b) to a sheet metal arrangement (7) consisting of a sheet metal plate (8) and a sheet metal ring (9) which is arranged coaxially with respect thereto and is connected in an integrally joined manner to said sheet metal plate (8), wherein the sheet metal plate (8) is arranged between an end side of the pressure piece (3) and the first brake lining (2a), wherein the sheet metal ring (9) is arranged between the boot (5) and the brake lining (2a) for protecting the boot (5) against heat radiation which is generated by way of braking operations on the brake linings (2a, 2b) and the brake disc (1), and wherein the sheet metal ring (9) has at least one cut-out (11) for reducing its flexural stiffness.

An aircraft wheel (1) comprising a hub connected to a rim (3) provided with a tire (100), the hub having an outer surface that extends facing an inner surface (4) of the rim (3) and that co-operates therewith to define an annular space for receiving a stack of brake disks including rotor disks having axial peripheral notches, each notch receiving a segment of an axial bar (10) extending projecting from the inner surface (4) of the rim (3), and respective heat shields (20), each in the form of an annular segment, being mounted between the two bars (10) of respective pairs of adjacent bars. Each heat shield (20) includes at least one holder portion bearing against at least one first abutment (19, 119) secured to the rim (3) in order to hold the heat shield (20) in position on the rim (3) elastically.

A heat shield assembly is disclosed. In various embodiments, the heat shield assembly includes a first heat shield segment having a first end and a second end spaced from the first end, the first end including a first hook member and the second end including a second hook member; and a first heat shield retainer including a first clip member configured to engage the first hook member and a second clip member.

A thermal management system and methods for use are disclosed. The thermal management system comprises a shield portion and a dissipation portion. The shield portion may comprise a hot side skin, a conduction layer, an insulation layer, and a cool side skin. The dissipation portion may comprise a fin array. Heat absorbed by the shield portion is partially or fully conducted to the dissipation portion for transfer to the ambient environment. The thermal management system may be employed as an aircraft wheel heat shield, an automotive brake heat shield, a gas turbine heat shield, an electronic heat sink, and in various other applications where heat shielding and/or heat transfer are desirable.

A brake system includes a series of rotors for operatively coupling to a shaft and stators for operatively coupling to a frame. A service brake system includes a singular annular service piston extending continuously around the series of rotors and stators and a parking brake system includes a singular annular parking piston positioned to extend continuously around the series of rotors and stators. The service piston nests with the parking piston, under a spring bias, such that the parking piston and service piston continuously engage together around the series of rotors and stators to thereby create the parking brake forces. Springs act on the parking piston to drive the parking piston and nested service piston to engage for parking brake forces. Pressurization of the parking piston deactuates the nested pistons. Then separate pressurization of fluid acts on the service piston to overcome the spring bias and separate the service piston from the parking piston to create service brake forces.

A torque bar assembly for use in an aircraft wheel is disclosed. In various embodiments, the assembly includes a torque bar; and a spacer configured for positioning between the torque bar and a wheel well of the aircraft wheel and to thermally insulate the wheel well from the torque bar, wherein the spacer includes a first anodized metal oxide layer on a first surface of the spacer configured to contact the torque bar. In various embodiments, the spacer includes a second anodized metal oxide layer on a second surface of the spacer configured to contact the wheel well.

A heat shield for an aircraft wheel assembly is made of a heat shield material evenly distributed across the heat shield along both the circumferential and the axial directions. The heat shield material has a high thermal conductivity greater than 30 W/mK. In various embodiments, the thermal conductivity is greater than 85 W/mK. In this manner, thermal flux is maximized throughout the heat shield to distribute heat evenly across the heat shield in both circumferential and axial directions.

A heat shield assembly includes a plate of heat shield material having an attachment hole therein by means of which the plate can be attached to another part using a fixation means. The assembly also includes a stress reduction plate secured to the plate of heat shield material at a plurality of securing points spaced from the attachment hole.