Aircraft landing gear

Patent metadata

Field	Value
Publication number	US-10414489-B2
Application number	US-201715464420-A
Country	US
Kind code	B2
Filing date	Mar 21, 2017
Priority date	Mar 21, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

An aircraft landing gear comprising an axle ( 100 ), a wheel ( 102 ) borne by the axle, a stack of discs ( 104 ) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator ( 106 ) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer ( 107 ) designed to bear the electromechanical actuator. The electromechanical actuator is fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. There also is a method of demounting a stack of discs from such a landing gear.

First claim

The invention claimed is:

1. An aircraft landing gear comprising:
an axle ( 100 ; 201 ; 301 ; 403 ),
a wheel ( 102 ) borne by the axle and having a rim ( 103 ; 208 ; 308 ) mounted to rotate about a longitudinal axis (X) of the axle,
a stack of discs ( 104 ; 400 ) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs,
at least one electromechanical actuator ( 106 ) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and
an actuator bearer ( 107 ; 310 ) designed to bear the electromechanical actuator, the electromechanical actuator being fixed to the actuator bearer while at the same time being demountable, the actuator bearer being incorporated into the axle in such a way that the axle and the actuator bearer form a single component,
the aircraft landing gear further comprising a torque tube ( 105 ; 200 ; 300 ; 405 ) which extends around the axle between the stack of discs and the axle and to which stator discs of the stack of friction discs are rotationally secured, the torque tube being fixed to the axle while at the same time being demountable, by fixing means comprising means for blocking the rotation of the torque tube about the longitudinal axis of the axle and means of axially blocking the torque tube along the longitudinal axis of the axle, a free end of the torque tube having a circular edge,
the rotational-blocking means and/or the axle axial-blocking means comprising first blocking means formed on a free end ( 113 ) of the torque tube and second blocking means integrally formed with the axle, the second blocking means and the axle forming a single component, the first blocking means and the second blocking means having complementary shapes which are positioned in one another when the torque tube is mounted, the first blocking means comprising an axial protrusion ( 120 ),
wherein the axial protrusion comprises an axial portion ( 124 ) and a circumferential lug ( 125 ) projecting from the axial portion, and
wherein the axial protrusion projects out and does not extend around an entire circumference of the free end of the torque tube.

2. The aircraft landing gear according to claim 1 , in which the actuator bearer comprises an actuator support ( 108 ) to which the electromechanical actuator is fixed and which extends radially from the axle.

3. The aircraft landing gear according to claim 1 , in which the axial protrusion is situated in the extension of a tenon ( 123 ) of the torque tube used for rotationally securing the stator discs to the torque tube.

4. The aircraft landing gear according to claim 1 , in which the second blocking means comprise a housing ( 121 ) formed on the axle which comprises an axial section ( 126 ) and a circumferential section ( 127 ).

5. The aircraft landing gear according to claim 1 , in which the axial-blocking means comprise a hub nut ( 307 ) screwed around the axle.

6. The aircraft landing gear according to claim 5 , in which the hub nut ( 307 ) is positioned between the rim of the wheel and the actuator bearer.

7. The aircraft landing gear according to claim 1 , further comprising means for angular positioning of the torque tube on the axle.

8. The aircraft landing gear according to claim 7 , in which the angular-positioning means comprise an axial tab ( 130 ) which projects out from the free end of the torque tube.

9. The aircraft landing gear according to claim 7 , in which the angular-positioning means comprise an axial portion ( 210 ) which extends out from the free end of the torque tube and has the shape of a sawtooth.

10. A method of demounting a stack of discs of an aircraft landing gear according to claim 1 , comprising:
demounting the wheel from the aircraft landing gear;
bringing up close to the aircraft landing gear a mobile maintenance device ( 401 ) comprising a horizontal support element ( 402 );
positioning the horizontal support element of the mobile maintenance device parallel to a longitudinal axis of the axle, between the axle and an upper part of the torque tube;
demounting the torque tube from the axle and of offsetting the torque tube in such a way that the torque tube rests on the horizontal support element of the mobile maintenance device; and
moving the mobile maintenance device away from the aircraft landing gear.

11. The method of demounting a stack of discs according to claim 10 , further comprising:
replacing the stack of discs; and
moving the mobile maintenance device closer to the aircraft landing gear and of repositioning the torque tube on the axle.

Assignees

• Safran Landing Systems

Inventors

• Onfroy Dominique
• Chico Philippe

Classifications

• F16D2250/0084

  Assembly or disassembly · CPC title

• F16D2055/0008

  Brake supports · CPC title

• F16D65/186

  with full-face force-applying member, e.g. annular · CPC title

• F16D65/0043

  Brake maintenance and assembly, tools therefor · CPC title

• F16D55/38

  mechanically actuated · CPC title