Aircraft landing gear equipped with means for driving in rotation wheels carried by the landing gear

Patent metadata

Field	Value
Publication number	US-9540098-B2
Application number	US-201414504605-A
Country	US
Kind code	B2
Filing date	Oct 2, 2014
Priority date	Oct 4, 2013
Publication date	Jan 10, 2017
Grant date	Jan 10, 2017

Abstract

A landing gear that comprises an axle ( 2 ) and a wheel ( 3, 3′ ). The wheel comprises a rim ( 4, 4′ ) mounted so as to rotate on the axle about a first axis of rotation (X), first blocks protruding from a lateral face (F, F′) of the rim, the first blocks being adapted to cooperate with a gearwheel ( 8 ) of a drive actuator ( 7 ) carried by the landing gear. The gearwheel is mounted rotatably about a second axis of rotation (Y) perpendicular to the first axis of rotation.

First claim

The invention claimed is:

1. An aircraft landing gear comprising:
an axle ( 2 ), and
a wheel ( 3 , 3 ′),
wherein said wheel comprises a rim ( 4 , 4 ′) mounted so as to rotate on the axle about a first axis of rotation (X), first blocks ( 11 , 11 ′) protruding from a lateral face (F, F′) of the rim, said first blocks cooperating with a gearwheel ( 8 ) of a drive actuator ( 7 ) carried by the landing gear, the gearwheel being mounted rotatably about a second axis of rotation (Y) perpendicular to the first axis of rotation, and
wherein said first blocks ( 11 , 11 ′) are mounted on the lateral face (F, F′) of the rim.

2. Landing gear according to claim 1 , wherein the first blocks ( 11 , 11 ′) are removable and are carried on the lateral face.

3. The aircraft landing gear according to claim 1 , wherein a safety cable ( 20 , 21 ) runs along the circumference of the lateral face of the rim and through first blocks so as to retain on the rim a first block in the case of accidental detachment of the first block from the rim.

4. The aircraft landing gear according to claim 1 , wherein the gearwheel comprises:
a hub ( 29 ) and
second removable blocks ( 28 ), which are carried on the circumference of the hub.

5. An aircraft landing gear comprising:
an axle ( 2 ), and
a wheel ( 3 , 3 ′),
wherein said wheel comprises a rim ( 4 , 4 ′) mounted so as to rotate on the axle about a first axis of rotation (X), first blocks ( 11 , 11 ′) protruding from a lateral face (F, F′) of the rim, said first blocks cooperating with a gearwheel ( 8 ) of a drive actuator ( 7 ) carried by the landing gear, the gearwheel being mounted rotatably about a second axis of rotation (Y) perpendicular to the first axis of rotation,
wherein the first blocks ( 11 , 11 ′) are removable and are carried on the lateral face, and
wherein the lateral face is shaped so as to have radial supports ( 14 , 26 ) separated by indentations ( 15 , 28 ), the first blocks being carried on the supports.

6. The aircraft landing gear according to claim 5 , wherein at least one first block is fixed on a radial support by means of at least one screw passing through the block and screwed into the radial support.

7. The aircraft landing gear according to claim 5 , wherein at least one first block comprises a positioning hole ( 17 ) complementary to a pin ( 19 ) arranged on the radial support on which the first block is carried.

8. The aircraft landing gear according to claim 5 , wherein at least one first block comprises two positioning ears ( 25 ) intended to extend into indentations ( 28 ) arranged on either side of the support on which the first block is carried.

9. An aircraft landing gear comprising:
an axle,
first and second wheels ( 103 a , 103 b ; 203 a , 203 b ), each wheel comprising a rim ( 104 a , 104 b ) mounted so as to rotate on the axle about a first axis of rotation,
first blocks protruding from a lateral face of the rim of said first wheel and first blocks protruding from a lateral face of the rim of said second wheel,
a first actuator ( 107 a ; 207 a ) for driving in rotation the first wheel comprising a first gearwheel ( 108 a ) engaging with the first blocks of the rim of the first wheel, the first gearwheel being mounted rotatably about a second axis of rotation that is perpendicular to the first axis of rotation,
a second actuator ( 107 b ; 207 b ) for driving in rotation the second wheel comprising a second gearwheel ( 108 b ) adapted to engage with the first blocks of the rim of the second wheel, the second gearwheel being mounted rotatably about a third axis of rotation that is perpendicular to the first axis of rotation, and
an engagement actuator ( 110 ; 210 ) carrying the drive actuators ( 107 a , 107 b ; 207 a , 207 b ) and adapted to displace said actuators simultaneously between an engagement position in which the first gearwheel engages with the first blocks of the rim of the first wheel and the second gearwheel engages with the first blocks of the rim of the second wheel, and a release position in which the first and second gearwheels are distanced from the rims of the first and second wheels.

10. The aircraft landing gear according to claim 9 ,
wherein the engagement actuator ( 110 ; 210 ) comprises:
an actuation element ( 111 ), and
two hinged arms ( 112 ; 219 ), each carrying one of the drive actuators, each of the arms being coupled by means of respective links ( 117 ; 221 ) to a first movable part ( 113 ; 209 ) of the actuation element, such that a displacement of the movable part causes a simultaneous rotation of the two arms, which drives a displacement of the first and second drive actuators between the engagement position and the release position.

11. The aircraft landing gear according to claim 10 , wherein the arms are hinged at fixed pivots ( 116 ) on the landing gear.

12. The aircraft landing gear according to claim 10 , wherein the arms are hinged at pivots mounted on a second movable part ( 213 ) of the actuation element and rotatable about a fourth axis that is parallel to the second and third axes, the first and second movable parts being displaceable by the actuation element along a fifth axis toward one another or away from one another, said fifth axis being perpendicular to said second and third axes.

13. The aircraft landing gear according to claim 12 , in which the first and second movable parts each comprise:
a nut ( 218 ) cooperating by helical connection to a first screw ( 215 ), and
a second screw ( 216 ) respectively,
said first and second screws being coaxial and having opposite thread directions, such that a simultaneous rotation of the screws by means of a motor of the engagement actuator causes the simultaneous axial displacement of the movable parts toward one another or away from one another.

14. The aircraft landing gear according to claim 13 , wherein the helical connection is a connection of the ball screw type. said second and third axes.

15. The aircraft landing gear according to claim 10 , further comprising a latching actuator mounted on the landing gear and cooperating with the first or the second movable part so as to block the drive actuators in the release position.

16. The aircraft landing gear according to claim 9 , wherein the engagement actuator ( 110 ) is mounted on the landing gear via a pivot connection allowing an angular displacement of the engagement actuator so as to compensate for a lateral displacement or a deformation of the rims parallel to an axis of the axle.

Assignees

• Messier Bugatti Dowty

Inventors

• Mazarguil Nicolas

Classifications

• B64C25/405 Primary

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

• Y02T50/823

  Cross-Sectional Technologies · mapped topic

• 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