An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.

A bogey undercarriage having at least two axles, each carrying at least two wheels, wherein at least one of the axles carries a wheel fitted with a rotary drive device and no brake device, while the other wheels are provided with brake devices and no movement devices is provided. A braking method applied to such an undercarriage is also provided.

A bogey undercarriage having at least two axles, each carrying at least two wheels, wherein at least one of the axles carries a wheel fitted with a rotary drive device and no brake device, while the other wheels are provided with brake devices and no movement devices is provided. A braking method applied to such an undercarriage is also provided.

An auxiliary rotating structure adapted for a tire of an aircraft includes a first side wall and a second side wall. The first side wall is fixed on a wall of the tire and rotates along with the tire. A side of the second side wall is connected to a side of the first side wall to form a chamber between the first side wall and the second side wall. An opening is formed between the other side of the first side wall and the other side of the second side wall and communicated with the chamber. The second side wall is made of resilient material. When the auxiliary rotating structure is located at a lower side of the tire, an air flow passes through the opening into the chamber to generate a first torque along a first rotary direction for rotating the tire.

An auxiliary rotating structure adapted for a tire of an aircraft includes a first side wall and a second side wall. The first side wall is fixed on a wall of the tire and rotates along with the tire. A side of the second side wall is connected to a side of the first side wall to form a chamber between the first side wall and the second side wall. An opening is formed between the other side of the first side wall and the other side of the second side wall and communicated with the chamber. The second side wall is made of resilient material. When the auxiliary rotating structure is located at a lower side of the tire, an air flow passes through the opening into the chamber to generate a first torque along a first rotary direction for rotating the tire.

An outboard wheel half has an axis and includes an outboard wheel structure configured to receive at least a portion of a tire. The outboard wheel half also includes a structure defining an alignment hole usable to align a hubcap relative to the structure. The structure defines a pocket circumferentially aligned with the alignment hole to reduce an amount of stress at a location of the alignment hole.

An outboard wheel half has an axis and includes an outboard wheel structure configured to receive at least a portion of a tire. The outboard wheel half also includes a structure defining an alignment hole usable to align a hubcap relative to the structure. The structure defines a pocket circumferentially aligned with the alignment hole to reduce an amount of stress at a location of the alignment hole.

An aircraft wheel including a rim (2) comprising two assembled-together rim halves (3a, 3b), each rim half (3a, 3b) having a bearing surface (7) extending in a plane perpendicular to an axis of rotation (X) of the aircraft wheel. The aircraft wheel further includes a spacer (9) situated between the two bearing surfaces (7) when the rim halves (3a, 3b) are assembled together.

An aircraft wheel including a rim (2) comprising two assembled-together rim halves (3a, 3b), each rim half (3a, 3b) having a bearing surface (7) extending in a plane perpendicular to an axis of rotation (X) of the aircraft wheel. The aircraft wheel further includes a spacer (9) situated between the two bearing surfaces (7) when the rim halves (3a, 3b) are assembled together.

An aircraft hubcap/wheel cover which uses ambient airflow (120 mph-175 mph) to rotate wheels on the landing gear of an aircraft accomplished by using slightly protruding slats, blades, scoops or other air capturing shapes, (once the landing gear has been lowered). These air capturing shapes are integrated as part of the hubcap/wheel cover during manufacture and are directly determined by ground speed applicable to that aircraft with the ultimate purpose being tire longevity. The wheel cover hubcap is a single piece design and has no moving parts.