Aircraft landing gear wheel with integral gear drive

Patent metadata

Field	Value
Publication number	US-2016229529-A1
Application number	US-201414514261-A
Country	US
Kind code	A1
Filing date	Oct 14, 2014
Priority date	Oct 14, 2014
Publication date	Aug 11, 2016
Grant date	—

Abstract

An aircraft landing gear wheel includes a main body with a hub portion and a driven gear portion. The hub portion includes a gear end and an attachment end. The driven gear portion integrally and drivingly connects with the hub portion at the gear end.

First claim

We claim:

1 . An aircraft landing gear wheel, comprising:
a main body, comprising;
a hub portion including a gear end and an attachment end; and
a driven gear portion integrally and drivingly connected with the hub portion at the gear end.

2 . The wheel of claim 1 , wherein the main body further comprises an intermediary portion integrally connected to the gear end of the hub portion and the driven gear portion.

3 . The wheel of claim 2 , wherein the intermediary portion comprises at least one connecting bar.

4 . The wheel of claim 3 , wherein the at least one connecting bar includes a fillet.

5 . The wheel of claim 1 , wherein the main body further comprises an attachment portion integrally connected to the attachment end of the hub portion, for attaching the wheel to a landing gear assembly of an aircraft.

6 . The wheel of claim 1 , wherein the main body is formed using a forging process.

7 . The wheel of claim 6 , wherein at least of portion the main body is formed with machining.

8 . The wheel of claim 1 , wherein the main body is formed of an aluminum alloy.

9 . The wheel of claim 1 , wherein;
the driven gear portion comprises a first annular stiff rail, and a second annular stiff rail; and the wheel further comprises one or more rollers rotatingly connected between the first annular stiff rail and the second annular stiff rail.

10 . The wheel of claim 9 , further comprising bearings rotatingly connecting the one or more rollers between the first annular stiff rail and the second annular stiff rail.

11 . The wheel of claim 10 , wherein the first annular stiff rail comprises roller apertures, and the bearings are disposed, at least partially in the roller apertures.

12 . The wheel of claim 10 , wherein the bearings comprise needle bearings.

13 . The wheel of claim 9 , wherein:
the gear portion further comprises a gear portion back section; and the first annular stiff rail, and the second annular stiff rail radially extend from the gear portion back section.

14 . The wheel of claim 9 , further comprising a low friction bushing rotatingly connecting the one or more rollers between the first annular stiff rail and the second annular stiff rail.

15 . An aircraft landing gear assembly, comprising:
a wheel, comprising a main body, and one or more rollers; the main body comprising a hub portion including a gear end and an attachment end, and a driven gear portion integrally and drivingly connected with the hub portion at the gear end; the driven gear portion comprising a first annular stiff rail and a second annular stiff rail; the one or more rollers rotatingly connected between the first annular stiff rail and a second annular stiff rail; a tire mounted on the hub portion; an electric motor assembly including a driving gear, and an electric motor drivingly connected to the driving gear; and an actuator disposed to move the driving gear into and out of a driving connection with the wheel.

16 . The landing gear assembly of claim 15 , wherein the driving gear is formed of a steel alloy

17 . The landing gear assembly of claim 15 , wherein the driving gear comprises driving gear teeth.

18 . The landing gear assembly of claim 17 , comprising the driving gear teeth mesh with the one or more rollers when the driving gear is in driving connection with the wheel.

19 . The landing gear assembly of claim 18 , wherein the wheel comprises spaces between the rollers; the driving gear drives the wheel when the driving gear and the wheel are in driving connection; and the driving gear teeth protrude into the spaces as the driving gear drives the wheel.

20 . An aircraft with an electric taxi drive system, comprising:
a landing gear assembly comprising;
a wheel, comprising a main body, and one or more rollers; the main body comprising a hub portion including a gear end and an attachment end, and a driven gear portion integrally and drivingly connected with the hub portion at the gear end; the driven gear portion comprising a first annular stiff rail and a second annular stiff rail; the one or more rollers rotatingly connected between the first annular stiff rail and a second annular stiff rail;
a tire mounted on the hub portion;
an electric motor drivingly connected to a driving gear; and
an actuator disposed to move the driving gear into and out of a driving connection with the wheel; and
an auxiliary power unit electrically connected with the electric motor, to selectively drive the electric motor.

Assignees

• Honeywell Int Inc

Inventors

• Christensen Donald Jeffrey
• Mitchell Robert

Classifications

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/405 Primary

  Powered wheels, e.g. for taxing · CPC title

• Y02T50/80

  Energy efficient operational measures, e.g. ground operations or mission management · CPC title