Aircraft wheel rim with removable flange

Patent metadata

Field	Value
Publication number	US-9676231-B2
Application number	US-201414572879-A
Country	US
Kind code	B2
Filing date	Dec 17, 2014
Priority date	Dec 31, 2013
Publication date	Jun 13, 2017
Grant date	Jun 13, 2017

Abstract

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 (β) 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.

First claim

The invention claimed is:

1. An aircraft wheel rim having an axis of rotation that defines a radial direction extending therefrom and comprising:
a main part ( 1 ) and an auxiliary removable part ( 10 ),
said main part comprising a hub ( 2 ), a disc ( 4 ) extending between the hub and an annular external portion ( 3 ) intended to accept a tyre, said annular external portion being shaped to have a first flange ( 5 ) at a first end thereof and a second flange ( 12 ) at a second end thereof, said second end being shaped to accept said auxiliary removable part ( 10 ), said removable part being attached to the annular external portion after the tyre has been fitted, and
rotation-prevention link-based structure for preventing the removable flange from rotating relative to the rim,
wherein the rotation-prevention link-based structure comprises at least one longitudinally-shaped link ( 20 ) having a first distal end coupled to the main part and a second distal end coupled to the auxiliary removable part, the first and second distal ends of the link having centres which define a longitudinal axis which extends in a plane perpendicular to the axis of rotation of the rim while at the same time extending obliquely to make an angle (β) with respect to the radial direction.

2. The aircraft wheel rim according to claim 1 , in which the main part and the removable auxiliary part comprise reservations ( 7 , 14 ) in which there are formed orifices ( 8 , 15 ) suited to accepting fasteners ( 9 , 16 ) for securing the distal ends of the link.

3. The aircraft wheel rim according to claim 1 , comprising at least two longitudinally-shaped links ( 20 ) arranged to be at opposite angles with respect to radial directions.

4. The aircraft wheel rim according to claim 3 , in which the two longitudinally-shaped links ( 20 ) are mounted in diametrically opposite regions of the rim.

5. The aircraft wheel rim according to claim 1 , in which the at least one longitudinally-shaped link ( 20 ) is cut from flat metal bar stock.

Assignees

• Messier Bugatti Dowty

Inventors

• Baldassara Patrick
• Delayre Xavier
• Galland Martial

Classifications

• B60B21/104

  the shape of flanges · CPC title

• B60B2900/541

  Servicing · CPC title

• B60B25/08

  Continuous flange rings; Arrangement of recesses enabling the flange rings to be slipped over the rim body · CPC title

• B60B2900/1214

  due to inertia · CPC title

• B60B23/08 Primary

  arranged radially · CPC title