Goodrich Corporation

Raytheon Technologies Corporation

Paul R Burte

Eric Daniel Cahill

Marc Georgin

Efrem E Ayichew

David B Stein

Lane B Robbins

Casey Canan

Richard A Poisson

Todd Eric Rook

Andrew C Walsh

Brian Keith Zell

Gregory Hickey

Thomas Clary

Clifton Randolph Boggs

Eric Meraz

Manju Maheve

Dharamveer Bathla

Udhayakumar Mani

Brian Ralph

Clifton R Boggs

Andrew Walsh

An aircraft braking system is disclosed that includes a first pedal, first and second pedal sensors for the first pedal, a first brake control unit (e.g., primary), and a separate second brake control unit (e.g., secondary). The first pedal position sensor is operatively interconnected with one of the first brake control unit and the second brake control unit, while the second pedal position sensor is operatively interconnected with the other of the first brake control unit and the second brake control unit. Outputs from these pedal sensors may be used to control operation of the aircraft braking system in at least some fashion.

Pedal processing for primary / alternate aircraft braking system architecture

A method for braking an aircraft is disclosed herein. The method includes receiving, by a brake controller, a first signal from a position sensor of a first pedal, receiving, by the brake controller, a second signal from a pedal sensor of the first pedal, determining, by the brake controller, that the pedal is being pressed based on the first and second signals, and sending, by the brake controller, an instruction to apply a brake pressure in response to the determination that the pedal is being pressed.

Additional safety feature in aircraft braking system

Systems and methods for shut off valve failure detection are provided. The system may comprise a housing, a shut off valve disposed within the housing, a first servovalve and a second servovalve coupled to the housing, and a pressure sensor disposed within the housing in fluid communication with the shut off valve. A controller may receive a pressure signal from the pressure sensor in the system, and a brake signal from a brake input device. The controller may determine whether there has been a shut off valve failure in the system in response to the pressure signal being greater than a pressure threshold and the controller failing to receive the brake signal, for a threshold period. The controller may then send a signal to a notification system in response to detection of the shut off valve failure and output a shut off valve failure notification.

Systems and methods to detect shut off valve failure for improved uncommanded braking

A method for brake health monitoring may include sending, by a brake control unit (BCU), a brake command signal to initiate a braking maneuver, and receiving a first wheel speed signal and a second wheel speed signal corresponding to the speed of first and second wheels, respectively, during the braking maneuver. The BCU may detect that the speed of the first wheel is greater than the speed of the second wheel by a predetermined threshold, and, in response thereto, post an alert indicating a failure in a brake control component associated with the first wheel based upon the detection of the speed of the first wheel being greater than the speed of the second wheel by the predetermined threshold.

Systems and methods for brake health monitoring

A system for detecting aircraft brake failure using retract braking may comprise a landing gear including a wheel, a brake coupled to the wheel, and a wheel sensor coupled to the wheel. A brake controller may be coupled to the brake and the wheel sensor. The brake controller may be configured to receive a begin retract braking signal, command the brake to apply a braking force to the wheel, calculate a wheel speed characteristic using data from the wheel sensor, and determine whether the wheel speed characteristic indicates a failure of the brake.

Systems and methods for brake failure detection using retract braking

A system for performing brake testing during flight of an aircraft, in accordance with various embodiments, includes a landing gear having at least one wheel assembly. The system further includes a brake configured to apply a braking force to the at least one wheel assembly. The system further includes a brake controller configured to determine a landing event indicating that the aircraft is approaching a landing, control the brake to apply a testing brake force to the at least one wheel assembly in response to determining the landing event, and determine an operational status of the brake based on the testing brake force.

Performing brake testing in flight on approach with a brake control system

A brake control system (BCS) may comprise a first controller, a second controller in electronic communication with the first controller, and a valve comprising a first coil and a second coil. The first controller may be configured to actuate the valve via the first coil. The second controller may be configured to actuate the valve via the second coil. The first controller may be configured to disable the second controller to take over control of the valve.

Arbitration of multiple systems using shared components

A brake control system (BCS) may comprise a shutoff valve configured to receive pressurized fluid, a one-way check valve configured to route the pressurized fluid, a first pressure transducer coupled between the one-way check valve and the shutoff valve, and an accumulator configured to supply pressurized fluid to a brake control valve module (BCVM) in response to the shutoff valve being in a closed position.

Brake control system channel protection

An emergency park brake system of an aircraft may include a user input interface configured to receive actuation input from a user. The emergency park brake system may also include a first displacement sensor and a second displacement sensor that are both coupled to the user input interface. The first displacement sensor may be configured to detect displacement of the user input interface and generate a first status of the user input interface and the second displacement sensor may be configured to also detect displacement of the user input interface and generate a second status of the user input interface. The emergency park brake system may also include a controller having a processor and memory. The controller may be configured to determine an emergency park brake condition.

Emergency park brake system

Braking control systems, such as for an aircraft, use a hydraulic failure isolation valve intermediate an accumulator power source and a dual valve assembly for mechanical operation when a hydraulic power source experiences a disruption.

Hydraulic failure isolation valve

An electrically controlled park and emergency brake system is disclosed. The brake system may comprise a brake control module having a shut-off valve in fluid communication with an outboard servo-valve and an inboard servo-valve. An emergency/park power source may supply fluid to the shut-off valve. The brake system may also comprise a vehicle management system in electronic communication with the brake control module. The brake system may also comprise mechanical inputs, including a wheel well brake handle and a cockpit brake handle. The brake system may also comprise redundant emergency/park power sources.

Electrically controlled park and emergency valve assembly

A system and method of identifying part failures is provided. The system may comprise monitoring a sensor, detecting a failure mode, selecting a row from a lookup table corresponding to the failure mode, looking up a line replaceable unit (LRU) failure probability for the detected failure mode, and reporting the LRU failure probability for the detected failure mode.

System and method for diagnosing line replaceable unit failure including measuring a hydraulic pressure and deriving a marginal distribution for each LRU

A valve includes an electrical park valve configured to receive an electrical park signal and to allow hydraulic fluid to flow through a first electrically-controlled channel in response to the signal indicating a parking request, and a main valve configured to receive the hydraulic fluid from the first electrically-controlled channel and to allow the hydraulic fluid to flow to a braking actuator in response to receiving the hydraulic fluid. The valve also includes an electrical emergency control valve configured to allow the hydraulic fluid to flow through a first control channel in response to a request for emergency braking. The valve also includes an emergency enable valve configured to receive the hydraulic fluid from the first control channel and to allow the hydraulic fluid to flow to the braking actuator in response to receiving the hydraulic fluid from the electrical emergency control valve.

Electrically activated park and emergency valve with on-valve manual actuation feature

In accordance with various embodiments, disclosed is a brake monitoring system for monitoring the health status of the brakes of an aircraft, the aircraft comprising a plurality of brakes, the brake monitoring system comprising conducting a statistical comparison of a brake temperature against a temperature data centrality value based on the temperature values of the plurality of brakes.

Brake monitoring system

A method of detecting an accumulator failure is provided. The method may comprise measuring a first pressure on a gas-side of an accumulator, measuring a second pressure on a fluid-side of the accumulator, finding a difference between the first pressure and the second pressure, and comparing the difference to a predetermined threshold. A system for detecting an accumulator failure is also provided. The system may comprise a non-transitory memory communicating with a processor, the non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the processor to perform operations. The operations may include receiving a first pressure measurement, receiving a second pressure measurement, determining a difference between the first pressure measurement and the second pressure measurement, and detecting the accumulator failure based on the difference.

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Clayton, OH, United States of America

Paul R Burte