# US 11,999,468 B2 · Hybrid brake systems and methods > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,999,468 B2 - Document ID: US11999468B2 - Status: Granted - Kind: B2 - Application number: 17/668,987 - Filed: 2022-02-10 - Published: 2023-08-10 - Granted: 2024-06-04 - Earliest claimed: 2022-02-10 - Assignees: Goodrich Corporation - Applicants: Goodrich Corporation - Inventors: Marc Georgin; Richard A. Poisson - Web page: https://patentgrep.com/patent/US11999468B2 ## CPC - B64C 25/44: Actuating mechanisms - B60T 8/1703: {for aircrafts} - B60T 8/325: {Systems specially adapted for aircraft} - B60T 8/885: {using electrical circuitry} - B60T 8/92: automatically taking corrective action - B60T 13/662: {characterised by specified functions of the control system components} - B60T 17/221: {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)} - B60T 2270/40: Failsafe aspects of brake control systems - B60T 2270/402: Back-up - B60T 2270/406: Test-mode; Self-diagnosis - B64C 25/42: Arrangement or adaptation of brakes - B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration} - B64C: AEROPLANES; HELICOPTERS - 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 - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT ## Abstract A braking system for an aircraft is disclosed herein. The braking system may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem and a hydraulic braking subsystem. During a flight, one of the electric braking subsystem and the hydraulic braking subsystem may be selected as a primary braking system. The braking system may be configured to command braking of a brake assembly by the hydraulic braking subsystem and the electric braking subsystem during an RTO phase of the flight. The braking system may be configured to command braking of a brake assembly by a secondary braking system in response to a failure of a primary braking system during the RTO phase of the flight. ## Claims ### Claim 1 A braking system for an aircraft, comprising: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem having an electric brake actuator configured to operate the brake assembly; a hydraulic brake control unit configured to operate the hydraulic braking subsystem; and an electric brake control unit configured to operate the electric braking subsystem, the electric brake control unit in operable communication with the hydraulic brake control unit, wherein the braking system is configured to: determine a primary braking system for a prior flight cycle; and activate the electric braking subsystem to be the primary braking system for a current flight cycle in response to determining the hydraulic braking subsystem was the primary braking system for the prior flight cycle. ### Claim 2 (depends on 1) The braking system of claim 1, wherein only the primary braking system is configured to operate the brake assembly for a flight cycle. ### Claim 3 (depends on 1) The braking system of claim 1, wherein the electric brake control unit and the hydraulic brake control unit are both configured to receive an indication that the braking system has been powered up prior to determining the primary braking system for the prior flight cycle. ### Claim 4 (depends on 1) The braking system of claim 1, wherein the electric brake control unit is configured to command the hydraulic brake control unit to be the primary braking system for the current flight cycle in response to determining the electric braking subsystem was the primary braking system for the prior flight cycle. ### Claim 5 (depends on 1) The braking system of claim 1, wherein the primary braking system is further configured to: determine a take off phase of the current flight cycle; and activate a secondary braking system for potential use during the take off phase of the current flight cycle. ### Claim 6 (depends on 5) The braking system of claim 5, wherein the primary braking system is further configured to determine a rejected take off (RTO) phase of the current flight cycle. ### Claim 7 (depends on 6) The braking system of claim 6, wherein the primary braking system is further configured to command the hydraulic braking subsystem and the electric braking subsystem to operate the brake assembly in response to determining the RTO phase of the current flight cycle. ### Claim 8 (depends on 6) The braking system of claim 6, wherein the primary braking system is further configured to command only the primary braking system to operate the brake assembly during the RTO phase of the current flight cycle. ### Claim 9 (depends on 8) The braking system of claim 8, wherein the primary braking system is further configured to determine a failure of the primary braking system during the RTO phase of the current flight cycle. ### Claim 10 (depends on 9) The braking system of claim 9, wherein the primary braking system is further configured to command the secondary braking system to take over braking controls in response to determining the failure of the primary braking system. ### Claim 11 An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: determining, by the processor, a take off phase of a flight for an aircraft; activating, by the processor, a secondary braking system of a braking system for possible use during the take off phase of the flight, the secondary braking system configured to operate independently from a primary braking system; determining, by the processor, a rejected take off (RTO) phase of the flight; and commanding, by the processor, braking of a brake assembly by the primary braking system and the secondary braking system during the RTO phase of the flight. ### Claim 12 (depends on 11) The article of manufacture of claim 11, wherein the primary braking system is a hydraulic braking system and the secondary braking system is an electric braking system. ### Claim 13 (depends on 11) The article of manufacture of claim 11, wherein the primary braking system is an electric braking system and the secondary braking system is a hydraulic braking system. ### Claim 14 (depends on 11) The article of manufacture of claim 11, wherein the operations further comprise determining, via the processor, a selected primary braking system for a prior flight during a powering up of the processor. ### Claim 15 (depends on 14) The article of manufacture of claim 14, wherein the operations further comprise selecting, via the processor, the primary braking system for the flight based on the selected primary braking system for the prior flight, the selected primary braking system for the prior flight being the secondary braking system for the flight. ### Claim 16 An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: determining, by the processor, a take off phase of a flight for an aircraft; activating, by the processor, a secondary braking system of a braking system for possible use during the take off phase of the flight, the secondary braking system configured to operate independently from a primary braking system; determining, by the processor, a rejected take off (RTO) phase of the flight; and commanding, by the processor, braking via the primary braking system only during the RTO phase of the flight. ### Claim 17 (depends on 16) The article of manufacture of claim 16, wherein the operations further comprise: determining, via the processor, a failure of the primary braking system; and commanding, via the processor, braking via the secondary braking system only. ### Claim 18 (depends on 17) The article of manufacture of claim 17, wherein the operations further comprise determining, via the processor, a selected primary braking system for a prior flight during a powering up of the processor. ### Claim 19 (depends on 18) The article of manufacture of claim 18, wherein the operations further comprise selecting, via the processor, the primary braking system for the flight based on the selected primary braking system for the prior flight, the selected primary braking system for the prior flight being the secondary braking system for the flight. ### Claim 20 (depends on 16) The article of manufacture of claim 16, wherein the primary braking system is an electric braking subsystem of the braking system or a hydraulic braking subsystem of the braking system, and wherein the secondary braking system is the hydraulic braking subsystem in response to the electric braking subsystem being the primary braking system.