Goodrich Corporation

Hamilton Sundstrand Corporation

Marc Georgin

Michael Kordik

Eric Daniel Cahill

Richard A Poisson

Efrem E Ayichew

Paul R Burte

Kevin Rehfus

Tyler Arsenault

Richard Paul Metzger, Jr

Gregory Hickey

Lane B Robbins

Resham Bains

Harald Klode

David Bernard Drennen

Naison E Mastrocola

Todd Eric Rook

Robert French

Paul L Summers

Michael Abbott

Eric Stein

Suk-Min Moon

Phillip E Cooley

Brian Keith Zell

Satinder Mann

Thomas M Fink

Clifton Randolph Boggs

Emad Al-Tabakha

Brian Ralph

Eric Meraz

Richard Metzger

Kaman Thapa Magar

Philip Hill

Jr Richard Paul Metzger

Clifton R Boggs

Thomas Fink

A braking system for an aircraft may comprise: a brake assembly including a brake stack; an electric braking subsystem having an electric brake actuator configured to operate the brake assembly; and a controller in operable communication with the electric braking subsystem, the controller configured to perform a wear depth measurement process, the wear depth measurement process comprising: determine a reference position of the electric brake actuator; command the electric brake actuator to extend toward the brake stack; receive a force measurement from a load cell in response to the electric brake actuator contacting the brake stack; determine a linear travel distance of the electric brake actuator based on an end position determined from the force measurement; and determine a wear depth based on calculating a difference between the linear travel distance and a prior linear travel distance of the electric brake actuator.

Hybrid brake systems and methods

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 of controlling an aircraft braking system includes initiating the aircraft braking system by receiving a first brake command at a primary system to actuate braking via the primary system, receiving the first brake command at an alternate system, and in response to the primary system losing an ability to control a brake, controlling the braking of the brake via the alternate system.

Alternate-secondary system in pressure control mode for minimal braking disruption in a primary-alternate braking system

A method for controlling brake assemblies of a vehicle is provided. Responsive to identifying a locked wheel protection event for a first wheel of a paired set of wheels on the vehicle, where the paired set of wheels is the first wheel on one side of the vehicle and a second wheel on an opposite side of the vehicle, a first brake pressure to a first brake assembly associated with the first wheel is released to zero pounds per square inch (PSI) and a second brake pressure to a second brake assembly associated with the second wheel of the paired set of wheels is reduced by a predetermined amount thereby reducing a yaw effect to the vehicle.

Advanced locked wheel protection functionality

A brake control system of the present disclosure calibrates a servo valve and calculates a calibrated transfer function associated with the servo valve for precise braking in open-loop mode. The calibration steps may include determining i) whether an aircraft is on a ground surface, ii) whether the aircraft is not moving relative to the ground surface, and iii) whether braking is applied to a brake system of the aircraft. The brake control unit may calibrate the servo valve in response to the brake control unit determining that i) the aircraft is on the ground surface, ii) the aircraft is not moving relative to the ground surface, and iii) the braking is not applied to the brake system of the aircraft. The calibration process includes sending two or more test currents to the servo valve, and determining braking pressures associated with those test currents to calculate the transfer function.

Systems and methods for pressure control mixed mode for braking operation

A braking system is disclosed. In various embodiments, the brake system includes a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; and an electric braking subsystem having an electric brake actuator configured to operate the brake assembly.

Hybrid brake system

A method of taxiing an aircraft may comprise determining, via a controller, whether the aircraft is taxiing with fewer brakes active than a total number of brakes; and modifying, via the controller, a brake pressure supplied to an active brake of the aircraft as a function of pedal deflection in response to determining the aircraft is taxiing with fewer brakes active relative to the total number of brakes.

Feel adjustment braking systems and methods

A method of taxiing an aircraft may comprise: determining, via a brake controller, whether the aircraft is taxiing with a first thrust provided from a first side of the aircraft, a second thrust from a second side of the aircraft, or both the first thrust and the second thrust; and modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal deflection in response to the taxiing with the first thrust only.

Modified braking systems and methods during taxi

A brake system and method of braking for an aircraft are provided. The brake system includes a primary brake control unit and an alternate brake control unit. In response to the primary brake control unit being placed in an active mode, the primary brake control unit is configured to send data on a set of channels to control brake operation of at least one brake, while the alternate brake control unit is configured to monitor brake temperature on another, separate set of channels coupled to at least one brake temperature sensor associated with the at least one brake.

System and method to address uncommanded brake (UCB) application and brake temperature sensing using primary and alternate architecture

A valve assembly may comprise: a housing defining an inlet port, an outlet port, a solenoid valve inlet port, and a solenoid valve outlet port, the inlet port in fluid communication with the solenoid valve inlet port; a shutoff valve disposed in the housing, the shutoff valve including a shutoff valve inlet port in fluid communication with the inlet port and a shutoff valve outlet port in fluid communication with the outlet port, and a second shutoff valve inlet port in fluid communication with the solenoid valve outlet port; a filter disposed downstream of the valve inlet port; and a check valve disposed between the shutoff valve outlet port and the outlet port of the housing.

Valve assembly for brake control 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 detecting an erroneous velocity data using a controller in communication with a velocity sensor onboard a vehicle includes receiving a time-series velocity data from the velocity sensor, calculating a time-series acceleration data using the time-series velocity data, calculating a time-series jerk data using the time-series acceleration data, calculating a saturated (numerically bounded) jerk data using the time-series jerk data, calculating an estimated acceleration data using the saturated jerk data, calculating a difference between the estimated acceleration data and the time-series acceleration data, and determining whether the difference is greater than a threshold value. The erroneous velocity data is detected in response to the difference being greater than the threshold value.

Erroneous velocity data detection algorithm systems and methods

An autobrake system includes a brake control unit (BCU), and a control knob in electronic communication with the BCU. The BCU is configured to receive a position signal from the control knob, the position signal corresponding a position of the control knob. The BCU is configured to select a braking deceleration based upon the position signal, wherein the braking deceleration continuously changes between a minimum braking deceleration and a maximum deceleration in response to the control knob moving between a first position and a second position for fine tuning of the braking deceleration.

Systems and methods for aircraft autobrake control

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.

A braking system for an aircraft may comprise: 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 and a load cell configured to measure a force supplied by the electric brake actuator; a hydraulic brake control unit configured to control the hydraulic braking subsystem; and an electric brake control unit configured to control the electric braking subsystem, the electric brake control unit in operable communication with the hydraulic brake control unit, the electric brake control unit configured to calibrate the load cell by a scale factor based on a measured force from the load cell, a measured hydraulic pressure used to exceed the measured force received from the hydraulic brake control unit, and a piston area of the hydraulic brake actuator.

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Dayton, OH, United States of America

Marc Georgin