Goodrich Corporation

Eric Daniel Cahill

Harald Klode

Marc Georgin

David Bernard Drennen

Kevin Rehfus

Paul R Burte

Efrem E Ayichew

Staffan Erickson

Michael Shaw

David B Stein

Casey Canan

Paul L Summers

Steven Thomas Keller

John P Swank

Andrew C Walsh

Mihai Ralea

Richard Paul Metzger, Jr

Lawrence F Corio

Thomas M Fink

Lane B Robbins

Thomas Clary

Bill May

Scott Snelling

Dale Prentice

Thomas Fink

John Swank

Harold Klode

A braking system may include a controller, a first wheel and a second wheel. The first wheel may be laterally displaced from the second wheel by a first distance. A first wheel speed sensor may be coupled to the first wheel and a second wheel sensor may be coupled to the second wheel. The controller may be configured to determine at least one of a slip ratio, a coefficient of friction, or a braking pressure of the second wheel in response to failure of the first wheel speed sensor. The controller may be configured to calculate a consistency value of the at least one of the slip ratio, the coefficient of friction, or the braking pressure. The controller may be configured to adjust a braking pressure of the first wheel speed sensor based upon the consistency value and the first distance.

Antiskid operation during degraded operation

A brake control system for a landing gear of an aircraft is provided. The system includes a first control channel for providing brake control signals to one or more brakes on the landing gear, and a second control channel for providing brake control signals to another one or more brakes on the landing gear. At least one of the first control channel and the second control channel is configured to act as an executive in monitoring braking efforts applied by the one or more brakes as compared to braking efforts applied by the another one or more brake, and to cause the braking efforts of at least one of the one or more brakes or the another one or more brakes to be modified in an effort to equalize the braking efforts.

Independent brake control of a common aircraft gear

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

Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage.

Systems and methods for landing identification

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

A displacement sensor includes a resistive element and a wiper element. The wiper element is separated from the resistive element in a parked mode the wiper element is in sliding electrical contact with the resistive element in a sensing mode. A user input interface may be coupled to at least one of the resistive element and the wiper element, wherein whether the displacement sensor is in the parked mode or the sensing mode is dependent on actuation of the user input interface.

Displacement sensor

Systems and methods for an aircraft emergency and park brake system are disclosed. The emergency and park brake system may comprise an emergency and park brake controller. The emergency and park brake controller may be configured to receive brake signals from mechanical and electrical inputs, generate a braking command comprising data from the brake signal, and transmit the braking command to control braking force. The emergency and park brake controller may receive brake signals from multiple locations including from the aircraft and from a remote location.

Systems and methods for aircraft emergency and park brakes

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 brake system for an aircraft is provided according to various embodiments. The system may include a left pedal arrangement comprising a left pedal, a first left sensor to generate a first left signal in response to translation of the left pedal. The system also includes a right pedal arrangement comprising a right pedal, a first right sensor to generate a first right signal in response to translation of the right pedal. Normal brake control logic controls the brake system in response to a normal condition being set. The normal brake control logic commands a left brake based on the left signal, and a right brake based on the first right signal. Emergency brake control logic controls the brake system in response to an emergency condition being set. The emergency brake control logic commands a same force to the left and right brakes based the left and right signals.

Systems and methods for emergency aircraft brake operation

A system, apparatus and method provide emergency differential braking for effecting braked steering of an aircraft. A brake input device is provided that not only allows for emergency and parking brake functions, but also enables differential braking. The brake input device (e.g., a parking and/or emergency brake lever, pedal, handle, etc.) can be used in a brake system including a brake system control unit (BSCU), one or more electro-mechanical actuator controllers (EMACs) and a brake assembly including one or more electrical actuators. Each EMAC is electrically coupled to one or more of the actuators so as to provide electrical power for driving the actuators. Each EMAC is also communicatively coupled to the BSCU so as to receive braking data therefrom. In an emergency, the input device sends braking signals directly to the brake actuators.

Differential emergency/park electric brake system

A brake system may comprise a controller, a vehicle management system (VMS) in communication with the controller, a valve in communication with the controller, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising determining, by the controller, that a first enable signal is received by the controller from the VMS, determining, by the controller, that a second enable signal is received by the controller from the VMS, and disabling, by the controller, the controller from control of the valve in response to the first enable signal and the second enable signal.

Brake control system with disabling features

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 controller unit for an aircraft control system includes an interface that is electrically connectable to a controller slot of an electronics bay of the aircraft control system, a processor coupled to the interface, and a tangible non-transitory computer-readable medium having instructions stored thereon that, in response to execution by the processor, cause the processor to perform various operations. The various operations include identifying, by the processor, a first aircraft assembly in electrical communication with the controller slot of the electronics bay, identifying, by the processor, a first program code stored on the tangible non-transitory computer-readable medium corresponding to the first aircraft assembly, and selecting, by the processor, the first program code to control the first aircraft assembly.

Aircraft control system architecture

A brake system of an aircraft may include a first brake control assembly, a second brake control assembly, a first brake control unit electrically coupled to the first brake control assembly, a second brake control unit electrically coupled to the second brake control assembly, and an arbitration control module. The arbitration control module may be configured to determine an operational integrity of the first brake control unit and the second brake control unit. In response to determining that one of the first brake control unit and the second brake control unit does not have sufficient operational integrity, the arbitration control module may enable the other of the first brake control unit and the second brake control unit to control both the first brake control assembly and the second brake control assembly.

Growing community of inventors

Troy, OH, United States of America

Eric Daniel Cahill