Aircraft brake torque load reaction through landing gear bogie structure

Patent metadata

Field	Value
Publication number	US-11118620-B2
Application number	US-202016786854-A
Country	US
Kind code	B2
Filing date	Feb 10, 2020
Priority date	Sep 8, 2017
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

An aircraft landing gear arrangement may comprise a landing gear bogie having an axle, a torque tube surrounding the axle and mechanically coupled to the landing gear bogie. A brake stack may surround the torque tube. The torque tube may comprise a cylindrical body extending between a first end and a second end. A flange may be disposed at the first end. A mating surface may be disposed on the first end or the second end of the torque tube for mating the torque tube to the landing gear bogie. A bogie flange may extend from the landing gear bogie whereby the torque tube may be mounted to the landing gear bogie.

First claim

What is claimed is:

1. An aircraft landing gear arrangement, comprising:
a landing gear bogie comprising an axle and a bogie flange;
a torque tube comprising a first flange disposed at a first end of the torque tube and a second flange disposed at a second end of the torque tube, the torque tube surrounding the axle and mechanically coupled to the bogie flange of the landing gear bogie via the first flange; and
a brake stack surrounding the torque tube, wherein the brake stack comprises a plurality of rotating discs and a plurality of stators;
wherein the second flange is configured to be coupled to an actuator mounting plate for mounting a brake actuator to the torque tube for compressing the plurality of rotating discs and the plurality of stators located between the first end of the torque tube and the second end of the torque tube;
wherein the torque tube is configured to transfer torque from the brake stack to the landing gear bogie, and the torque tube is configured to be in thermal communication with the brake stack and is configured to transfer heat from the brake stack to the landing gear bogie.

2. The aircraft landing gear arrangement of claim 1 , wherein the first flange comprises a mating surface in contact with the landing gear bogie.

3. The aircraft landing gear arrangement of claim 2 , wherein the torque tube extends between a first end and a second end, the first flange being disposed at the second end.

4. The aircraft landing gear arrangement of claim 3 , wherein the mating surface is on an axially facing surface of the first flange.

5. The aircraft landing gear arrangement of claim 3 , wherein the mating surface is disposed on a radially outward facing surface of the first flange.

6. The aircraft landing gear arrangement of claim 1 , wherein the torque tube defines a mechanical load path from the brake stack to the landing gear bogie via the first flange.

7. The aircraft landing gear arrangement of claim 1 , wherein the torque tube defines a thermal load path from the brake stack to the landing gear bogie via the first flange.

8. The aircraft landing gear arrangement of claim 1 , wherein the bogie flange extends from the landing gear bogie, the first flange mechanically coupled to the landing gear bogie via the bogie flange.

9. A method of installing a torque tube to a landing gear bogie, wherein the landing gear bogie comprises an axle and a bogie flange, and the torque tube comprises a first flange disposed at an inboard end of the torque tube and a second flange disposed at an outboard end of the torque tube, the method comprising:
positioning the torque tube around an axle extending from the landing gear bogie;
moving the torque tube axially towards the landing gear bogie until the torque tube mechanically engages the landing gear bogie;
coupling the torque tube to the bogie flange via the first flange;
moving a brake stack to surround the torque tube, wherein the brake stack comprises a plurality of rotating discs and a plurality of stators; and
coupling an actuator mounting plate to the second flange for mounting a brake actuator to the outboard end of the torque tube for compressing the plurality of rotating discs and the plurality of stators located between the inboard end of the torque tube and the outboard end of the torque tube.

10. The method of claim 9 , further comprising positioning a mating surface of the torque tube in contact with a bogie flange extending from the landing gear bogie, wherein the mating surface comprises at least one of an axially facing surface and a radially outward facing surface of the inboard end of the torque tube.

11. The method of claim 10 , wherein the mating surface comprises a crenulated surface.

12. The method of claim 10 , wherein the mating surface comprises a plurality of primarily axially extending ridges.

13. The method of claim 9 ,
wherein the torque tube is configured to transfer torque from the brake stack to the landing gear bogie, and the torque tube is configured to be in thermal communication with the brake stack and is configured to transfer heat from the brake stack to the landing gear bogie.

Assignees

• Goodrich Corp

Inventors

• Whittle Scott
• Kipp Richard A
• Herrmann Nathaniel J

Classifications

• B64C25/42 Primary

  Arrangement or adaptation of brakes · CPC title

• B64C25/34

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

• F16D55/40

  actuated by a fluid-pressure device arranged in or one the brake · CPC title

• F16D2065/1388

  to shaft or axle · CPC title

• F16C2361/45

  Brakes · CPC title