# US 12,179,729 B2 · Aircraft braking system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,179,729 B2 - Document ID: US12179729B2 - Status: Granted - Kind: B2 - Application number: 17/764,841 - Filed: 2020-09-25 - Published: 2022-10-13 - Granted: 2024-12-31 - Earliest claimed: 2019-09-30 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations Limited - Inventors: George Howell - Web page: https://patentgrep.com/patent/US12179729B2 ## CPC - B60T 8/1703: {for aircrafts} - B64C 25/42: Arrangement or adaptation of brakes - B64C 25/426: {Braking devices providing an automatic sequence of braking} - B64C 25/48: differentially operated for steering purposes - B64F 5/60: Testing or inspecting aircraft components or systems - 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 - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR ## Abstract An aircraft controller 5, aircraft braking system 13 and method for determining braking parameters. The aircraft controller 5 is configured to determine information associated with an aircraft taxiing route associated with an aircraft 1. On the basis of the information, the aircraft controller 5 determines a first braking parameter for a first main landing gear 8 of the aircraft 1 and a second braking parameter for a second main landing gear 9 of the aircraft 1 during a landing event. The first and second braking parameters are determined to result in asymmetrical braking between the first 8 and second 9 main landing gears during the landing event. ## Claims ### Claim 1 An aircraft controller configured to: before a landing event, determine information associated with an aircraft taxiing route associated with an aircraft and along which the aircraft is to travel after the landing event and/or traveled before a take-off event preceding the landing event; based on the information, determine a first braking parameter for a first main landing gear of the aircraft and a second braking parameter for a second main landing gear of the aircraft during the landing event, wherein the first braking parameter and the second braking parameter are determined to result in asymmetrical braking between the first main landing gear and the second main landing gear during the landing event; and cause actuating of a brake of the first main landing gear using the first braking parameter during the landing event, and/or cause actuation of a brake of the second main landing gear using the second braking parameter during the landing event. ### Claim 2 (depends on 1) The aircraft controller according to claim 1, further configured to determine a difference between a sum of right-hand braking and a sum of left-hand braking in the taxiing route based on the information. ### Claim 3 (depends on 2) The aircraft controller according to claim 2, wherein the first braking parameter and the second braking parameter are determined based on the difference. ### Claim 4 (depends on 1) The aircraft controller according to claim 1, wherein the first braking parameter and the second braking parameter are determined to achieve a wear on at least one brake of the first main landing gear that differs from a wear on at least one brake of the second main landing gear by less than a predetermined amount during a combination of the landing event and movement of the aircraft along the taxiing route. ### Claim 5 (depends on 1) The aircraft controller according to claim 1, wherein each of the first braking parameter and the second braking parameter comprises at least one of a hydraulic pressure, a braking torque, an angular deceleration of a landing gear wheel and braking authority. ### Claim 6 (depends on 1) The aircraft controller according to claim 1, wherein the taxiing route is a route along which the aircraft is due to taxi after the landing event. ### Claim 7 (depends on 6) The aircraft controller according to claim 6, wherein the first braking parameter and the second braking parameter are determined to cause a temperature of at least one brake of the first main landing gear to differ from a temperature of at least one brake of the second main landing gear by less than a predetermined amount at an end of the aircraft taxiing route. ### Claim 8 (depends on 1) The aircraft controller of claim 1, wherein the determined information includes information representative of braking events during the aircraft taxiing route. ### Claim 9 An aircraft braking system for an aircraft, the aircraft braking system comprising: a first main landing gear and a second main landing gear offset laterally from the first main landing gear on the aircraft; and an aircraft controller configured to determine a first braking parameter for the first main landing gear and a second braking parameter for the second main landing gear during a landing event of the aircraft, wherein the aircraft controller is configured to determine, before the landing event, the first braking parameter and the second braking parameter based on information indicative of an aircraft taxiing route to be taken by the aircraft after the landing event and/or travelled before a take-off event preceding the landing event, wherein the first braking parameter and the second braking parameter are determined to result in asymmetrical braking between the first main landing gear and the second main landing gear during the landing event, and wherein the aircraft braking system is configured to cause actuation of a brake on the first main landing gear based on the first braking parameter during the landing event and/or cause actuation of a brake on the second main landing gear based on the second braking parameter during the landing event. ### Claim 10 (depends on 9) The aircraft braking system according to claim 9, wherein the information comprises historical data associated with movement of the aircraft. ### Claim 11 (depends on 10) The aircraft braking system according to claim 10, wherein the historical data comprises historical data associated with the aircraft taxiing route. ### Claim 12 (depends on 9) The aircraft braking system according to claim 9, further comprising: an input device operable by an operator to override the aircraft controller by determining an alternative first braking parameter for the first main landing gear and/or an alternative second braking parameter for the second main landing gear during the landing event. ### Claim 13 (depends on 9) The aircraft braking system of claim 9, wherein the determined information includes information representative of braking events during the aircraft taxiing route. ### Claim 14 A method of operating an aircraft controller to determine and apply braking parameters for braking at least one wheel of each of a first main landing gear and a second main landing gear laterally offset from each other on an aircraft, the method comprising: before a landing event, determining information indicative of an aircraft taxiing route to be taken by the aircraft after the landing event and/or taken by the aircraft before a take-off event preceding the landing event; determining respective braking parameters for each of the first main landing gear and the second main landing gear during the landing event of the aircraft based on the information, wherein the braking parameters are determined to result in asymmetrical braking by the first main landing gear and the second main landing gear during the landing event; and applying the braking parameter respective to the first main landing gear to cause actuation of a brake on a wheel of the first main landing gear during the landing event and/or applying the braking parameter respective to the second main landing gear to a cause actuation of brake on a wheel of the second main landing gear during the landing event. ### Claim 15 (depends on 14) The method according to claim 14, wherein the determining the information indicative of the taxiing route comprises receiving the information from an input device operable by an operator. ### Claim 16 (depends on 14) The method according to claim 14, further comprising providing an indication associated with the braking parameters to an operator. ### Claim 17 (depends on 14) The method according to claim 14, further comprising receiving confirmation from an operator that the determined braking parameters are to be utilised during the landing event. ### Claim 18 (depends on 14) The method according to claim 14, wherein the determining the braking parameters comprises: determining the braking parameters such that braking of the first main landing gear differs from braking of the second main landing gear by an amount selected based on a difference between a sum of right-hand braking and a sum of left-hand braking in the taxiing route. ### Claim 19 (depends on 14) The method according to claim 14, wherein the determining the braking parameters comprises: determining the braking parameters such that wear of at least one brake of the first main landing gear differs from wear of at least one brake of the second main landing gear by less than a predetermined amount during a combination of the landing event and movement of the aircraft along the taxiing route. ### Claim 20 (depends on 14) The method according to claim 14, wherein the determining the braking parameters comprises: determining the braking parameters such that a temperature of at least one brake of the first main landing gear differs from a temperature of at least one brake of the second main landing gear by less than a predetermined amount at an end of the aircraft taxiing route subsequent to the landing event. ### Claim 21 (depends on 14) The method according to claim 14, wherein the braking parameters are for automatic application at a predetermined time during the landing event. ### Claim 22 (depends on 14) The method according to claim 14, wherein the braking parameters comprise braking authorities to be provided to an operator for actuation of brakes of the first and second main landing gears, respectively, during the steps of applying the first and second braking parameters. ### Claim 23 (depends on 14) The method of claim 14, wherein the determining information includes determining information representative of braking events during the aircraft taxiing route. ### Claim 24 An aircraft controller configured to: before a landing event, determine a difference between a sum of right-hand braking and a sum of left-hand braking in an aircraft taxiing route due to be taken by an aircraft after the landing event and/or taken before a take-off event preceding the landing event; based on the difference, determine a first braking parameter for a first main landing gear of the aircraft and a second braking parameter for a second main landing gear of the aircraft, and apply the first braking parameter to cause actuation of a brake on a wheel of the first main landing gear during the landing event, and/or apply the second braking parameter to cause actuation of a brake a wheel on the second main landing gear during the landing event.