Device for driving at least one wheel of an aircraft landing gear

Patent metadata

Field	Value
Publication number	US-12448118-B2
Application number	US-202318457875-A
Country	US
Kind code	B2
Filing date	Aug 29, 2023
Priority date	Sep 16, 2022
Publication date	Oct 21, 2025
Grant date	Oct 21, 2025

Abstract

A device for driving at least one wheel of an aircraft landing gear including at least one landing gear wheel, this wheel including a rim, an electric motor including a shaft, a mechanical transmission system between the shaft of the motor and the rim, this mechanical transmission system including a mechanical reducer including a sun gear secured in rotation to the shaft of the motor, a ring gear, and planet gears which are carried by a planet carrier and which each includes three external toothings, including a median external toothing which is meshed with a toothing of the sun gear, and two lateral external toothings which are respectively meshed with toothings of the ring gear.

First claim

The invention claimed is:

1. An aircraft landing gear, comprising:
at least one landing gear wheel, said wheel comprising a rim having an axis of rotation,
an electric motor comprising a shaft,
a mechanical transmission system between the shaft of the motor and the rim, said mechanical transmission system comprising a mechanical reducer,
wherein the mechanical reducer comprises:
a sun gear secured in rotation to the shaft of the motor, said sun gear being centered on the axis and comprising an external toothing,
a ring gear centered on the axis and comprising two internal toothings, and
planet gears which are carried by a planet carrier and which each have a median plane of symmetry perpendicular to the axis, each of the planet gears comprising three external toothings, including a median external toothing which is meshed with the toothing of the sun gear, and two lateral external toothings which are respectively arranged on either side of the median external toothing and which are respectively meshed with the toothings of the ring gear, and
wherein the planet gears are each centered and guided by three needle bearings carried by the planet carrier, said three needle bearings including a median needle bearing that is radially in line with said median external toothing, and said three needle bearings further including two lateral needle bearings that are respectively radially in line with said lateral external toothings.

2. The aircraft landing gear according to claim 1 , wherein the ring gear is stationary and is attached to a stator of the aircraft landing gear, and the planet carrier is movable in rotation about the axis and is attached to the rim.

3. The aircraft landing gear according to claim 1 , wherein the ring gear is movable in rotation about the axis and is attached to the rim, and the planet carrier is stationary and is attached to a stator of the aircraft landing gear.

4. The aircraft landing gear according to claim 1 , wherein the toothings of the ring gear are identical.

5. The aircraft landing gear according to claim 1 , wherein the toothing of the sun gear and the median external toothing of each of the planet gears are herringbone-shaped.

6. The aircraft landing gear according to claim 1 , wherein the lateral external toothings of each of the planet gears and the toothings of the ring gear are helical.

7. The aircraft landing gear according to claim 1 , wherein the motor has an annular shape centered on the axis and is arranged next to the mechanical reducer.

8. The aircraft landing gear according to claim 1 , wherein the motor is arranged next to and at the level of the planet gears.

9. The aircraft landing gear according to claim 1 , wherein the median toothing has a diameter greater than the diameter of the lateral toothings.

10. The aircraft landing gear according to claim 1 , wherein the planet carrier comprises a single transverse wall which is perpendicular to the axis and on which the planet gears are cantilevered.

11. The aircraft landing gear according to claim 1 , wherein the planet carrier comprises two transverse walls which are perpendicular to the axis and between which the planet gears are mounted, at least one of these transverse walls or both comprising a central orifice for the passage of the shaft of the motor.

12. An aircraft landing gear comprising:
at least one landing gear wheel, said wheel comprising a rim having an axis of rotation,
an electric motor comprising a shaft,
a mechanical transmission system between the shaft of the motor and the rim, said mechanical transmission system comprising a mechanical reducer,
wherein the mechanical reducer comprises:
a sun gear secured in rotation to the shaft of the motor, said sun gear being centered on the axis and comprising an external toothing,
a ring gear centered on the axis and comprising two internal toothings, and
planet gears which are carried by a planet carrier and which each have a median plane of symmetry perpendicular to the axis, each of the planet gears comprising three external toothings, including a median external toothing which is meshed with the toothing of the sun gear, and two lateral external toothings which are respectively arranged on either side of the median external toothing and which are respectively meshed with the toothings of the ring gear, and
wherein the planet gears are each centered and guided by two roller bearings carried by the planet carrier, said three external toothings of each of the planet gears being located axially between these roller bearings which are then not located radially inside said three external toothings.

Assignees

• Safran Trans Systems

Inventors

• Fernandez Maxime
• Francois Loic
• Morelli Boris Pierre Marcel
• Peltier Jordane Emile Andre

Classifications

• F16H1/2809

  with means for equalising the distribution of load on the planet gears · CPC title

• F16H1/24

  involving gears essentially having intermeshing elements other than involute or cycloidal teeth (F16H1/16 takes precedence) · CPC title

• B64C25/34

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

• Y02T50/80

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

• F16H1/28

  with gears having orbital motion · CPC title