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 brake application device (1) for a disc brake (2) of commercial vehicles comprising an actuating spindle (3) with, axially of the actuating spindle (3), a pressure plate (4) arranged on the actuating spindle (3), and the pressure plate (4) having an annular groove (6) radially for receiving a boot (5). A heat shield (7) is at least partially disposed between the pressure plate head (4a) and the boot (5) at a spacing (X). An insulating layer (8) may be present between the heat shield (7) and the pressure plate head (4a). The heat shield (7) may be a metal ring (10) encapsulated in or coated with an elastomer (9a). The heat shield (7) may alternatively be formed of plastic or silicone.

A wheel module for a vehicle is disclosed including a wheel, said wheel having a wheel rim; a wheel axle, the wheel rim being rotatably mounted on said wheel axle; and a braking device for braking the wheel, said braking device comprising a brake disc and a brake pad. The brake disc and the brake pad being mutually contactable in order to transmit a braking force F1 to the wheel rim, wherein the brake disc can be axially moved to contact the brake pad and the brake pad remains axially fixed.

A fixed brake caliper for a disc brake disc has a first half-body housing a first thrust device, and facing a first braking surface, a second half-body housing a second thrust device, and facing a second braking surface, and a first bridge element connecting and supporting the second half-body to the first half-body. The first bridge element has a first and a second guiding and resting bridge surfaces. The first half-body has a first protrusion protruding towards the opposite second half-body. The second half-body has a second protrusion protruding towards the opposite first half-body. The first and second half-bodies and the bridge element are mutually separable. The first and second protrusions each delimit a guiding and resting half-body surface, respectively. The first bridge element rests the first bridge surface against the first half-body surface and the second bridge surface against the second half-body surface.

A braking system (4) for an aircraft wheel (2) comprises first and second brake rotor discs (20a, 20b) axially spaced along an axis (A) and rotationally coupled to the wheel (2), a stator disc (24) arranged axially between the first and second rotor discs (20a, 20b), and a heat shield (34) mounted to at least one of the first and second rotor discs (20a, 20b). Radially outer portions (30) of the first and second rotor discs (20a, 20b) extend radially outwardly of the stator disc (24) to define a gap (32) between the radially outer portions (30) of the first and second rotor discs (20a, 20b). The heat shield (34) extends at least partially over or into the gap (32).

The present disclosure provides a heat shield. The heat shield may comprise a first layer comprising a first material, a second layer radially outward of the first layer comprising a second material, and a third layer radially outward of the second layer comprising a third material, wherein the first layer is coupled to the second layer by at least one post and at least one support extending from a radially outer surface of the first layer.

A heat shield assembly includes a first heat shield segment having a first end and a second end spaced from the first end, and a heat shield retainer including a radial extension, wherein a torque bar aperture extends through the radial extension, the torque bar aperture configured to receive a torque bar. The heat shield retainer is secured from radial movement via the radial extension.

An aircraft brake insulator assembly for a brake mechanism of an aircraft includes a torque barrel assembly and a multi-layer insulator. The torque barrel assembly includes a torque plate and a torque barrel coupled to the torque plate. The multi-layer insulator is configured to be located between a piston housing of the brake mechanism and the torque plate. The multi-layer insulator includes a first insulator layer and a second insulator layer contacting the first insulator layer.

An electrically operated vehicle includes a braking resistor in a heat sink cover. The heat sink cover has an air throughflow body having vent openings and an air throughflow direction perpendicular to a direction of travel of the vehicle. The heat sink cover includes an inlet flap on an air inflow side and an outlet flap on an air outflow side. An opening mechanism opens and closes the flaps. In the closed state, the flaps are oriented along the direction of travel and obliquely to the air throughflow direction. In a plan view of the vent openings, the vent openings are at least 90% covered by the flaps in the closed state and at most 60% covered by the flaps in the opened state. The flaps are disposed symmetrically to a vehicle center axis, and the vent openings are oriented parallel to side surfaces of the vehicle.

A motor includes a housing containing a rotor and stator. A brake assembly is adapted to restrain rotation of the rotor. A brake controller includes a brake diagnostics system. At least one vibration sensor is located in the housing and provides vibration data to the brake diagnostics system in response to a brake operation cycle of the brake assembly. The vibration data is used by the brake diagnostics system to assess an operative condition of the brake assembly.