Braking system

Patent metadata

Field	Value
Publication number	US-12179728-B2
Application number	US-202117511373-A
Country	US
Kind code	B2
Filing date	Oct 26, 2021
Priority date	Dec 21, 2020
Publication date	Dec 31, 2024
Grant date	Dec 31, 2024

Abstract

An aircraft braking system for an aircraft, the aircraft including first and second brakes, and first and second energy distribution systems for delivering energy to the first and second brakes to operate the respective first and second brakes. The aircraft braking system is switchable between: a first configuration, in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake; and a second configuration, in which the first energy distribution system is coupled to both the first and second brakes.

First claim

The invention is:

1. An aircraft braking system for an aircraft including first and second brakes, the aircraft braking system comprising:
a first energy distribution system and a second energy distribution system configured to deliver energy to the first and second brakes to operate the respective first and second brakes,
an isolator configured to selectively permit or hinder a flow of hydraulic fluid from the first energy distribution system to the second energy distribution system, and
an unidirectional energy flow device in series with the isolator and configured to permit hydraulic fluid to flow from the first energy distribution system to the second energy distribution system and to prevent a flow of hydraulic fluid from the second energy distribution system to the first energy distribution system,
wherein the aircraft braking system is switchable between:
a first configuration in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake; and
a second configuration in which the first energy distribution system is coupled to both the first and second brakes,

wherein the first energy distribution system includes a first hydraulic pump and a first reservoir, and the second energy distribution system includes a second hydraulic pump and a second reservoir separate from the first reservoir,
wherein a first maximum power output of the first hydraulic pump is greater than a second maximum power output of the second hydraulic pump,
wherein the first hydraulic pump is adapted to operate up to the first maximum power output to pump hydraulic fluid to the first and second brakes while the aircraft braking system is in the second configuration, and
wherein the second hydraulic pump is adapted to operate up to the second maximum power output to supply hydraulic fluid to the second brake while the aircraft braking system is in the first configuration.

2. The aircraft braking system of claim 1 , wherein the aircraft braking system is operable in:
a normal mode in which the first and second hydraulic pumps are configured to receive power from one or more primary power supplies; and
a backup mode in which the first hydraulic pump is configured to receive power from a backup power supply.

3. The aircraft braking system of claim 2 , wherein the aircraft braking system is operable in the backup mode in response to a loss of power from the one or more primary power supplies to one or both of the first and second hydraulic pumps during the normal mode.

4. The aircraft braking system of claim 1 , wherein the first energy distribution system comprises a first flow control device, and the second energy distribution system comprises a second flow control device.

5. An aircraft braking system controller for controlling the aircraft braking system of claim 1 , wherein the aircraft braking system controller is configured to:
detect a reduction or a loss of energy in the second energy distribution system when the braking system is configured in the first configuration; and
cause the aircraft braking system to switch to the second configuration on the basis of a loss or reduction of energy in the second energy distribution system detected by the aircraft braking system controller.

6. The aircraft braking system controller according to claim 5 , comprising a primary avionics system configured to control the aircraft braking system, and a secondary avionics system configured to control the aircraft braking system in the event of a failure of the primary avionics system.

7. An aircraft comprising:
the aircraft braking system of claim 1 , and
the first and second brake.

8. The aircraft braking system of claim 1 , wherein the first and second energy distribution systems comprise respective first and second energy storage devices configured to store energy for supplying to the respective first and second brakes.

9. The aircraft braking system of claim 8 , wherein, when the aircraft braking system is configured in the second configuration, the second energy storage device is configured to receive and store energy from the first energy supply.

10. An aircraft braking system for an aircraft including first and second brakes, the aircraft braking system comprising:
a first energy distribution system and a second energy distribution system configured to deliver energy to the first and second brakes to operate the respective first and second brakes,
wherein the aircraft braking system is switchable between:
a first configuration in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake, and
a second configuration in which the first energy distribution system is coupled to both the first and second brakes,

wherein the first energy distribution system includes a first hydraulic pump and a first hydraulic fluid reservoir, and the second energy distribution system includes a second hydraulic pump and a second hydraulic fluid reservoir separate from the first reservoir,
wherein a first maximum power output of the first hydraulic pump is greater than a second maximum power output of the second hydraulic pump,
wherein the first hydraulic pump is adapted to operate up to the first maximum power output to pump hydraulic fluid to the first and second brakes while the aircraft braking system is in the second configuration,
wherein the second hydraulic pump is adapted to operate up to the second maximum power output to supply hydraulic fluid to the second brake while the aircraft braking system is in the first configuration,
wherein the first energy distribution system comprises a first normal circuit and a first alternative circuit, and the second energy distribution system comprises a second normal circuit and a second alternative circuit;
wherein the first and second normal circuits are configured to couple the respective first and second hydraulic pumps to the respective first and second brakes; and
wherein the first and second alternative circuits are configured to receive hydraulic fluid from the respective first and second hydraulic fluid reservoirs and supply hydraulic fluid to the respective first and second brakes.

11. The aircraft braking system of claim 10 , wherein:
the first reservoir has a first capacity to store hydraulic fluid sufficient to supply the first hydraulic pump operating at the first maximum power output,
the second reservoir has a second capacity to store hydraulic fluid sufficient to supply the second hydraulic pump operating at the second maximum power output, and
the first capacity is greater than the second capacity.

12. An aircraft braking system for an aircraft including first and second brakes, the aircraft braking system comprising:
a first energy distribution system and a second energy distribution system configured to deliver energy to the first and second brakes to operate the respective first and second brakes,
wherein the aircraft braking system is switchable between:
a first configuration in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake, and
a second configuration in which the first energy distribution system is coupled to both the first and second brakes,

wherein the first energy distribution system includes a first hydraulic pump and a firs

Assignees

• Airbus Operations Ltd

Inventors

• Howell George
• Navarro Laia
• Becher Florian
• David Steve
• Au Joy
• Kerr Benjamin

Classifications

• B60T2270/414

  Power supply failure · CPC title

• B60T17/22

  Devices for monitoring or checking brake systems; Signal devices · CPC title

• B60T2270/413

  Plausibility monitoring, cross check, redundancy · CPC title

• B60T2270/403

  Brake circuit failure · CPC title

• B60T13/686

  in hydraulic systems or parts thereof · CPC title