A non-pneumatic tire assembly includes a non-pneumatic tire. The non-pneumatic tire includes an inner circumferential ring and an outer circumferential ring defining an annular space and a cylindrical space inside the inner circumferential ring. A plurality of partitions connect the circumferential rings within the annular space. A ground-contacting tread is located on the outer circumferential ring. A rim, including a plurality of pieces, is located within the cylindrical space. The non-pneumatic tire assembly further includes a hub that is removably connected to the rim.

A hybrid wheel including a functional rim, a center disc, and a wheel face insert, wherein the wheel rim and the center disc are made of a specified material, and wherein the wheel face insert is made of a dissimilar material. The wheel face insert can be secured to the center disc by at least one of screws, pins, rivets, or structural adhesive, and/or the wheel face insert can be secured to the functional rim by at least one of screws, pins, rivets, or structural adhesive.

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.

Provided is a wheel which is inexpensive, light, and sufficiently rigid. A wheel 6a includes an annular rim 60 to which a tire 6b is externally fitted, a hub 61 which is arranged at a center portion of the rim 60 and to which an axle is connected, and a disk 62 which is attached with the rim 60 at a periphery portion and which covers one side of the wheel 6a. The disk 62 includes a planar portion 62a and a first rib 62b provided at a surface of one side of the planar portion 62a and extending in the radial direction. The planar portion 62a is provided with a first groove 62d at a surface of the other side at a position corresponding to the first rib 62b.

A hermetically sealed wheel assembly which has been welding autogenously is provided, along with a method and system for welding the wheel assembly. The wheel assembly is made up of at least two components which are laser welded to each other without the use of filler material to create a hermetically sealed wheel assembly.

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.

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.

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.

While specific embodiments of the invention have been shown and described in detail to illustrate the application of the principles of the invention, it will be understood that the invention may be embodied otherwise without departing from such principles.

A disk wheel for a motor vehicle, in particular a single-track motor vehicle, includes: a wheel hub for mounting the disk wheel on the motor vehicle, which wheel hub is concentric to an axis of rotation of the disk wheel; a wheel rim, which is likewise concentric thereto; and a first and a second wheel disk. The first wheel disk and the second wheel disk each extend from the wheel rim toward the wheel hub, are mutually spaced on the wheel hub in a transverse direction which is parallel to the axis of rotation of the disk wheel, and run toward each other as they approach the wheel hub. The disk wheel also has at least two reinforcement ribs, which extend from the first wheel disk to the second wheel disk and interconnect the first wheel disk and the second wheel disk. The reinforcement ribs are distributed evenly around the axis of rotation of the disk wheel.