Aircraft braking system

Patent metadata

Field	Value
Publication number	US-11753185-B2
Application number	US-202016850680-A
Country	US
Kind code	B2
Filing date	Apr 16, 2020
Priority date	Apr 23, 2019
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

A routine maintenance procedure performed in respect of a wheel of an aircraft landing gear is disclosed. Consumable brake lining material is integrated with the wheel. Re-treading or replacing the wheel tyre and inspecting or replacing the consumable brake lining material tyre are performed at the same successive intervals as part of the routine maintenance procedure. The sum volume and mass of brake material present on the aircraft may thus be reduced. Brake material providing for the demands of a maximum energy rejected take-off may be provided separately. The wheel may be made in one or two parts from carbon-fibre composite material. At least some of the brake material may be provided on an outwardly facing planar surface of the wheel.

First claim

The invention claimed is:

1. An aircraft wheel and a brake assembly comprising a first portion and a second portion configured such that the first portion of the brake assembly is provided as part of the wheel and removable therewith, wherein the second portion of the brake assembly is in use mounted on landing gear structure adjacent to the wheel,
the first portion being operable separately from the second portion to provide braking and dissipate energy at a first level, and
both the first portion and second portion being operable together to provide braking and dissipate energy at a second level, the second level being higher than the first.

2. The aircraft wheel and a brake assembly according to claim 1 , wherein the first portion of the brake assembly has a first mass of consumable brake lining material, the mass being at least 1 kg, and the second portion of the brake assembly has a second mass of consumable brake lining material, the second mass being greater than the first mass.

3. The aircraft wheel and a brake assembly according to claim 1 , wherein the aircraft wheel and the brake assembly are arranged to apply braking in response to a received braking demand such that below a first threshold level of braking demand, the first portion applies braking to the wheel but the second portion either does not apply braking to the wheel or applies braking at a lower level, and such that above a second threshold level of braking demand, the second threshold level being the same or higher than the first threshold level, the first portion applies braking to the wheel and the second portion applies more braking to the wheel.

4. The aircraft wheel and a brake assembly according to claim 3 , wherein the second portion is configured to apply braking to the wheel in the event of a maximum energy rejected take-off.

5. The aircraft wheel and the brake assembly according to claim 4 , wherein the first portion of the brake assembly is insufficient of itself to meet the demands of a maximum energy rejected take-off.

6. The aircraft wheel and a brake assembly according to claim 1 , wherein the first portion comprises at least one stator and at least one rotor and the second portion comprises at least one stator and at least one rotor, the rotors and stators of the first and second portions being arranged in series.

7. The aircraft wheel and a brake assembly according to claim 1 , wherein the first portion and the second portion of the brake assembly are arranged to be activated by the same actuator.

8. The aircraft wheel and a brake assembly according to claim 7 , wherein the same actuator is configured to activate the braking provided by the first portion of the brake assembly via a compressible pressure transfer device which above a threshold pressure compresses in a way that causes the actuation of the second portion of the brake assembly.

9. A method of applying braking to the aircraft wheel and the brake assembly of claim 1 , comprising applying braking to the wheel, in response to a rejected take-off, using both the first portion and the second portion so as to provide braking and dissipate energy at a second level, the second level being higher than the first level.

10. A method according to claim 9 , wherein the first portion of the brake assembly is in the form of a brake pack that forms an integrated part of the wheel, and the second portion of the brake assembly is in the form of a brake pack that is mounted on the landing gear and which does not form an integrated part of the wheel.

11. The method of braking according to claim 10 , wherein the first brake pack has less brake material than the second brake pack and the first and second brake packs are arranged to provide braking of the wheel by the first brake pack only.

12. The method of braking according to claim 9 , wherein the method includes a step of providing braking of the wheel by use of the first portion of the brake assembly and without use of the second portion of the brake assembly.

13. A method of applying braking to a wheel of a landing gear of an aircraft, in response to a rejected take-off, the method including operating both a first portion and a second portion of a brake assembly, the first portion being in the form of a brake pack that forms an integrated part of the wheel, and the second portion being in the form of a brake pack that is mounted on the landing gear and which does not form an integrated part of the wheel.

14. The method of applying braking according to claim 13 , wherein the first portion of the brake assembly is operable separately from the second portion to provide braking and dissipate energy at a first level, and the first portion and second portion when operating together in response to the rejected take-off, provide braking and dissipate energy at a second level, the second level being higher than the first level.

Assignees

• Airbus Operations Ltd

Inventors

• Bill Andrew

Classifications

• B64C25/36 Primary

  Arrangements or adaptations of wheels, tyres or axles in general · CPC title

• B60T17/221 Primary

  Procedure or apparatus for checking or keeping in a correct functioning condition of brake systems (hydraulic pressure systems in general F15B19/00, F15B21/04; testing structures or apparatus G01M) · CPC title

• F16D65/0043 Primary

  Brake maintenance and assembly, tools therefor · CPC title

• B64F5/40 Primary

  Maintaining or repairing aircraft · CPC title

• B64C25/42

  Arrangement or adaptation of brakes · CPC title