The invention relates to an aircraft wheel comprising a rim and a tire (20) received on the rim, the rim comprising two parts (1; 2) assembled with one another by means of assembly bolts (5), one of the parts comprising a recess (3) in which is arranged a seal (4) which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct (6) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tire, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.

A wheel assembly including a rigid wheel and a flexible tire. The rigid wheel includes a radially outer rim wall, a plurality of mounting elements, and a plurality of inflatable spacers between the mounting elements. The flexible tire may be mounted on the mounting elements of the rigid wheel such that portions of the flexible tire between the mounting elements are separated from the outer rim wall by spaces between the mounting elements and are configured to flex inwardly when subject to ground engaging pressure. The inflatable spacers limit the amount of inward flex of the inwardly flexible portions of the flexible tire.

A quick release apparatus for a bicycle tire or tube is provided, which reduces time and effort spent in changing the tire or tube. A main wheel frame and a sub wheel frame are provided. These two frames with rim respectively can be assembled to construct a complete wheel frame set. When said main wheel frame connects with the sub wheel frame, it provides a complete rim with two walls for containing the tube. When said main wheel frame leaves said sub wheel frame, it generates a gap between these two frames for removing the tube easily.

A wheel assembly including a rigid wheel having a radially outer rim wall presenting a polygonal shape with a plurality of outermost vertices connecting a plurality of planar faces, and a flexible tire mounted on the outer rim wall. The tire is supported by the vertices of the rim wall and is separated from the rim faces by a space, portions of the tire located between the vertices being configured to flex inwardly when subject to ground engaging pressure.

A wheel assembly in accordance with various embodiments for use with an aircraft can include an inner surface, a first lug extending into an area defined by the inner surface and a heat shield configured to be coupled to the first lug. The wheel assembly can also include a gasket configured to be positioned between the inner surface and the heat shield and to remain in place relative to the first lug in response to rotation of the wheel assembly relative to the aircraft.

Aircraft wheel rim in two parts, one of them a main part (1) comprising a hub (2), a disc (4) extending between the hub and an annular external portion (3) intended to accept a tire and shaped to have a flange (5) at one of its ends. The other end is shaped to accept the second part, a removable part (10) forming a flange (12) which removable part is attached to the annular external portion after the tire has been fitted. The rim has a structure for preventing the removable flange from rotating relative to the rim. The structure comprises at least one link (20) having ends, the centers of which define an axis which extends in a plane perpendicular to an axis of rotation of the rim while at the same time extending obliquely to make an angle () with respect to a radial direction, one of the ends being coupled to the main part and the other of its ends being coupled to the removable part.

Systems and apparatus for an oval O-ring groove for aircraft wheels may generally comprise an inboard wheel portion and an inboard O-ring groove. The inboard wheel portion may include an inboard rim located opposite of an inboard tubewell. The inboard tubewell may have an inboard mating surface located on an axially outward edge of the inboard tubewell. The inboard O-ring groove may be formed as a partial oval-shaped recess located on an outer edge of the inboard mating surface.

A driver key is provided for coupling a rim base and a bead seat band of a wheel rim assembly together. The driver key includes a body having a first engagement surface and a second engagement surface. The first and second engagement surfaces are each oriented at an angle of less than ninety degrees relative to a longitudinal axis of the body.

A method for rotationally driving an aircraft wheel, the wheel being equipped with a rim comprising two half-rims assembled by bolts (5). According to the method, a drive member for generating a torque for driving the wheel is controlled. The transfer of the drive torque to the wheel is accomplished via the rim assembly bolts.

The invention relates to an aircraft wheel comprising a rim and a tyre (20) received on the rim, the rim comprising two parts (1; 2) assembled with one another by means of assembly bolts (5), one of the parts comprising a recess (3) in which is arranged a seal (4) which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct (6) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tyre, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.