# US 12,179,728 B2 · Braking system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,179,728 B2 - Document ID: US12179728B2 - Status: Granted - Kind: B2 - Application number: 17/511,373 - Filed: 2021-10-26 - Published: 2022-06-23 - Granted: 2024-12-31 - Earliest claimed: 2020-12-21 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations Limited - Inventors: George Howell; Laia Navarro; Florian Becher; Steve David; Joy Au; Benjamin Kerr - Web page: https://patentgrep.com/patent/US12179728B2 ## CPC - B60T 8/1703: {for aircrafts} - B64C 25/42: Arrangement or adaptation of brakes - B60T 8/404: {Control of the pump unit} - B60T 13/662: {characterised by specified functions of the control system components} - B60T 13/686: {in hydraulic systems or parts thereof} - B60T 17/02: Arrangements of pumps or compressors, or control devices therefor - B60T 17/22: Devices for monitoring or checking brake systems; Signal devices - B60T 2270/414: Power supply failure - B60T: VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL (electrodynamic brake systems for vehicle, in general B60L; brakes per se, i.e. devices where braking effect occurs, including ultimate brake actuators, F16D); ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES - B64C: AEROPLANES; HELICOPTERS ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 2) 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. ### Claim 4 (depends on 1) 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. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 5) 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. ### Claim 7 (depends on 1) An aircraft comprising: the aircraft braking system of claim 1, and the first and second brake. ### Claim 8 (depends on 1) 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. ### Claim 9 (depends on 8) 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. ### Claim 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. ### Claim 11 (depends on 10) 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. ### Claim 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 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, 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 insufficient to supply hydraulic fluid to the first hydraulic pump operating at the first maximum power output, and wherein the first capacity is greater than the second capacity.