Aircraft Patents (Class 303/126)
  • Patent number: 11772622
    Abstract: An aircraft includes a brake lever for receiving a pilot braking input as a lever travel of the brake lever, a braking wheel operatively coupled with the brake lever to brake the aircraft based on the lever travel, a brake actuator operatively coupled with the braking wheel to apply a braking force in response to a braking pressure provided to the brake actuator, and a brake pressure circuit. The brake pressure circuit is configured for: estimating a maximum braking pressure above which the braking wheel will skid with respect to a ground surface; scaling a lever gain of the brake lever to command the maximum braking pressure at a full travel of the brake lever such that a remaining brake lever travel indicates the amount of braking capability remaining for the aircraft; and braking the braking wheel based on the lever gain and the lever travel.
    Type: Grant
    Filed: May 21, 2020
    Date of Patent: October 3, 2023
    Inventor: Thomas F. Landers
  • Patent number: 10259435
    Abstract: Systems and methods for aircraft braking are disclosed. The systems and methods may comprise a control mode executive configured to receive a pedal input and calculate a gear deceleration command comprising a desired deceleration rate based on the pedal input; a pedal deceleration controller in electronic communication with the control mode executive configured to receive the gear deceleration command from the control mode executive and calculate a gear pedal command based on at least one of the gear deceleration command and a deceleration feedback; and a pedal executive in electronic communication with the pedal deceleration controller configured to receive the gear pedal command, and generate a pedal braking command based on the gear pedal command.
    Type: Grant
    Filed: May 15, 2017
    Date of Patent: April 16, 2019
    Assignee: GOODRICH CORPORATION
    Inventor: Marc Georgin
  • Patent number: 10259571
    Abstract: 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.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: April 16, 2019
    Assignee: Goodrich Corporation
    Inventors: Eric Daniel Cahill, Paul R. Burte, Casey Canan, Efrem E. Ayichew, David B. Stein
  • Patent number: 10202204
    Abstract: A total runway safety system (TRSS) and method measures, monitors, manages, and informs flight crew on the progress of takeoffs and landings and of any hazardous runway conditions. In some embodiments, the TRSS measures, monitors, and informs flight crew of longitudinal and lateral runway tracks thus preventing overruns and veer-offs during takeoffs and landings. In some embodiments, backscatter of infrared laser beams emitted by the aircraft is used to evaluate groundspeed and the reflectivity of the runway surface to make estimates of the surface conditions, roughness and contamination, which affects rolling and braking efforts and acceleration. In some embodiments TRSS evaluates runway surface and predicts tire-surface rolling and braking coefficient of friction.
    Type: Grant
    Filed: March 25, 2017
    Date of Patent: February 12, 2019
    Assignee: AAR Aerospace Consulting, LLC
    Inventor: Nihad E. Daidzic
  • Patent number: 10017165
    Abstract: A method for regulating motor vehicle electrohydraulic brake systems having a pressure supply apparatus actuated by a control unit and hydraulically connected to wheel brakes via a pressure regulating valve. The pressure supply apparatus includes a cylinder-piston assembly operated by an electromechanical actuator. A set point pressure value is determined for each wheel brake. The cylinder-piston assembly is actuated to a predetermined pilot pressure in the hydraulic pressure chamber. A pilot pressure actual value and an actuator speed actual value are obtained. A pilot pressure set point value, the pilot pressure set point value and the pilot pressure actual value are fed as input variables to a regulator which outputs an actuator speed set point value. The actuator speed and actual set point values are fed as inputs to the speed regulator. The actuator speed set point value is modified as a function of the number of brakes.
    Type: Grant
    Filed: August 8, 2014
    Date of Patent: July 10, 2018
    Assignee: CONTINENTAL TEVES AG & CO. OHG
    Inventors: Jürgen Böhm, Georg Roll, Marco Besier
  • Patent number: 9896194
    Abstract: Methods and systems are provided for improved autobraking systems for aircraft. Such systems and methods include a pedal balance controller configured to receive one of a yaw angle, a yaw speed, and a wheel speed, and an autobrake pedal executive module configured to send an autobrake left pedal command and an autobrake right pedal command to a pedal executive module, wherein the pedal executive module is configured to execute a pedal command. These systems and methods may assist a pilot in maintaining a desired course during autobraking.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: February 20, 2018
    Assignee: GOODRICH CORPORATION
    Inventor: Marc Georgin
  • Patent number: 9783179
    Abstract: A hydraulic block of a hydraulic multi-circuit vehicle braking system having braking force regulation includes an installation space for a hydraulic reservoir of the vehicle braking system that is isolated from a braking circuit, for example by closing a connecting line using a pressed-in ball. The installation space is connected to another braking circuit via an additional bore, wherein a larger storage volume is available to the braking circuit as a result. The necessary changes to the hydraulic block are small.
    Type: Grant
    Filed: July 19, 2011
    Date of Patent: October 10, 2017
    Assignee: Robert Bosch GmbH
    Inventors: Volkmar Schlotter, Michael Kunz, Oliver Schmautz
  • Patent number: 9783173
    Abstract: An advanced braking system for an aircraft is disclosed. A controller calculates the braking required from each wheel in terms of force. A constant deceleration is achieved throughout a braking run by calculating the braking from other sources, principally aerodynamic drag, and commanding a complementary total level of braking from the wheel brakes. The performance of each wheel and brake are monitored during the braking run to determine whether their braking performance is limited by the brake discs or by the tire-ground interaction and to see whether the wheel is approaching the maximum slip ratio after which a skid occurs. The controller uses this information to distribute the total demand for braking amongst the wheels. In doing this, it also aims to keep the braking demand symmetrical across the aircraft and not to overheat the brakes. The controller further measures the braking force provided by a wheel and controls its brake pressure accordingly to achieve the force desired.
    Type: Grant
    Filed: March 11, 2005
    Date of Patent: October 10, 2017
    Assignee: Airbus UK Limited
    Inventor: Alessandro Riccardo Britannico Giazotto
  • Patent number: 9614465
    Abstract: An electric motor system having a power supply, an electric motor connected to the power supply, an object driven by the motor having a range of motion and a substantially neutral position within the range of motion, a power sensor configured to sense power from the power supply, a position sensor configured to sense position of the object in at least a portion of the range of motion, an energy storage, a controller connected to the power supply and the energy storage, wherein the controller is configured to brake the motor as a function of the position sensor, the neutral position and the power sensor.
    Type: Grant
    Filed: July 26, 2011
    Date of Patent: April 4, 2017
    Assignee: Moog Inc.
    Inventors: Michael H. Shriver, John W. Stevens
  • Patent number: 9573698
    Abstract: Flight deck display systems and methods for generating cockpit displays including dynamically-adjustable runway length symbology are provided. In one embodiment, the flight deck display system includes a display device to which a controller is operably coupled. A cockpit display, such as a primary fight display, is generated on the display device. The cockpit display is generated to include a runway graphic and a usable runway end marker. During operation of the display system, the controller receives runway usage restriction data identifying any currently restricted sections of a runway approached for usage by the aircraft. The controller further determines a dynamically-adjusted usable runway length as a function of the runway usage restriction data and then adjusts the position of the usable runway end marker, as generated on the cockpit display, along the length of the runway graphic in accordance with the dynamically-adjusted usable runway length.
    Type: Grant
    Filed: August 6, 2015
    Date of Patent: February 21, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Gang He
  • Patent number: 9157372
    Abstract: A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold.
    Type: Grant
    Filed: March 11, 2013
    Date of Patent: October 13, 2015
    Assignee: Bell Helicopter Textron Inc.
    Inventor: Chandler Sowden
  • Patent number: 9085285
    Abstract: In a system and method for aircraft brake metering to alleviate structural loading, one or more electric brake actuators for wheel brakes having a range of brake clamping force are provided, and a brake actuation controller is configured to monitor commanded initiation of the aircraft, to limit initial brake effort of the electric brake actuators to a preset fraction of a maximum possible braking effort for a preset period of time, and to permit brake effort of the electric brake actuators up to the maximum possible braking effort after the preset period of time after initiation of braking has been commanded. The preset fraction is preferably approximately 50% of the maximum possible braking effort, and may be tuneable. The preset period of time is preferably approximately one second, and also may be tuneable.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: July 21, 2015
    Assignee: Hydro-Aire, Inc.
    Inventors: Garrett H. DeVlieg, John Gowan
  • Patent number: 9082301
    Abstract: A system and method for determining a predicted stopping performance of an aircraft moving on a runway. A predicted stopping force acting on the aircraft to stop the aircraft is determined by a processor unit as the aircraft is moving on the runway. A predicted deceleration of the aircraft moving on the runway is determined by the processor unit using the predicted stopping force acting on the aircraft to stop the aircraft. The predicted stopping performance of the aircraft on the runway is determined by the processor unit using the predicted deceleration of the aircraft.
    Type: Grant
    Filed: October 28, 2013
    Date of Patent: July 14, 2015
    Assignee: THE BOEING COMPANY
    Inventors: Michael Gian Catalfamo, Jean Marie Crane, Marisa R. Jenkins, John David Anderson, Thomas Todd Griffith, Bechara J. Mallouk
  • Patent number: 9039102
    Abstract: Systems and methods disclosed herein may be useful emergency braking systems for use in, for example, an aircraft. A system is disclosed that allows emergency braking without the need for a manually operated emergency brake. For example, a system is provided comprising a potentiometer in mechanical communication with a brake pedal, a first electronic switch in electrical communication with the potentiometer, a second electronic switch indicating a displacement of the brake pedal, wherein a brake control valve opens in response to the first electronic switch, and wherein a shutoff valve opens in response to the second electronic switch.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: May 26, 2015
    Assignee: GOODRICH CORPORATION
    Inventors: Eric D. Cahill, Paul R. Burte
  • Patent number: 9043050
    Abstract: A reverse thrust detent system for an aircraft includes a throttle quadrant having an intermediate reverse thrust detent position, a reverse thrust scheduling system interfacing with the throttle quadrant, at least one aircraft engine interfacing with the reverse thrust scheduling system and a programmable input interfacing with the reverse thrust scheduling system and adapted to receive an engine reverse thrust setting. The reverse thrust scheduling system is adapted to operate the at least one aircraft engine according to the engine reverse thrust setting responsive to actuation of the intermediate reverse thrust detent position of the throttle quadrant. A reverse thrust detent method for an aircraft is also disclosed.
    Type: Grant
    Filed: August 13, 2008
    Date of Patent: May 26, 2015
    Assignee: The Boeing Company
    Inventors: William L. Goodman, Thomas Imrich
  • Patent number: 9028014
    Abstract: A system for electrical braking of a vehicle comprises a power bus coupled to a first driver associated with a first electromechanical actuator (EMA). The power bus is also coupled to a second driver associated with a second EMA, and the first EMA and the second EMA are associated with a wheel of the vehicle. The power bus provides braking power to the first EMA via the first driver and to the second EMA via the second driver. A normal braking command interface provides a first braking signal to the first driver and a second braking signal to the second driver. An emergency/park brake interface bypasses the normal braking command interface and sends a first emergency/park braking signal to the first driver and a second emergency/park braking signal to the second driver. A sensor measures a current at a single location of the power bus that is proportional to a braking force exerted on the wheel.
    Type: Grant
    Filed: December 8, 2010
    Date of Patent: May 12, 2015
    Assignee: Goodrich Corporation
    Inventors: Thomas Clary, William P. May, Paul L. Summers
  • Patent number: 9008873
    Abstract: Methods and systems for a go/no-go Landing Decision Point (LDP) are disclosed. The methods and systems provide a graphical LDP on a cockpit display that pilots can use to determine whether to continue the landing or execute a go-around. The methods and systems may be implemented in embodiments having an onboard portion, an off-board portion, or both operatively coupled to provide an LDP in a preview/planning mode and real time mode.
    Type: Grant
    Filed: October 7, 2013
    Date of Patent: April 14, 2015
    Assignee: The Boeing Company
    Inventors: Thomas J. Phillips, Jean M. Crane
  • Patent number: 8974012
    Abstract: An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be enable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition.
    Type: Grant
    Filed: December 12, 2012
    Date of Patent: March 10, 2015
    Assignee: The Boeing Company
    Inventors: T. Todd Griffith, David T. Yamamoto, Andreea D. Uta
  • Patent number: 8965657
    Abstract: Systems and methods for detecting an on ground condition of an aircraft are disclosed. A weight on wheel system may determine that an aircraft is on the ground. Wheel speed sensors may measure the speed of the aircraft wheels. Axle reference speeds may be calculated for each landing gear based on the speed of the aircraft wheels. A brake control unit may determine that the axle reference speed for each axle of the landing gears is above an on ground threshold speed, and the brake control unit may allow braking to be applied.
    Type: Grant
    Filed: July 2, 2013
    Date of Patent: February 24, 2015
    Assignee: Goodrich Corporation
    Inventors: Marc Georgin, Richard Metzger
  • Patent number: 8948994
    Abstract: The invention relates to an aircraft braking system having brakes with electromechanical braking actuators (103) adapted to press selectively against associated stacks of disks in order to generate a braking torque on associated wheels of the aircraft; at least one control module (130) receiving braking setpoints and responding by generating a braking command (121); and at least one power module (120) responding to the braking command by delivering AC power to the motors of actuators connected to the power module so that the motors develop a braking force corresponding to the braking setpoints. According to the invention, the control module includes a digital processor stage (131) and an analog processor unit (135).
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: February 3, 2015
    Assignee: Messier-Bugatti-Dowty
    Inventor: David Frank
  • Patent number: 8843254
    Abstract: Systems and methods are disclosed for detection of dragging brakes for use in, for example, an aircraft. A method is provided comprising calculating, by a brake controller, a slip ratio based upon an aircraft speed and a speed of an aircraft wheel, determining, by the brake controller, that the slip ratio is above a threshold value, and sending, by the brake controller and in response to the slip ratio being above the threshold value, a dragging brake signal to an aircraft component.
    Type: Grant
    Filed: July 11, 2012
    Date of Patent: September 23, 2014
    Assignee: Goodrich Corporation
    Inventors: Eric D. Cahill, Dale Prentice
  • Patent number: 8727454
    Abstract: The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force.
    Type: Grant
    Filed: October 17, 2012
    Date of Patent: May 20, 2014
    Assignee: Hydro-Aire, Inc.
    Inventors: Gary DeVlieg, John Gowan
  • Patent number: 8668279
    Abstract: A system for controlling an electronically actuated brake is described. The system includes a plurality of brakes controlled by an electronic brake control unit, a brake pedal, momentary switch contact, and a latching relay. When the brake pedal is deflected beyond a threshold and the momentary switch contact are engaged the electronic brake control unit will communicate to the brakes to change their state between on and off. The present state is saved in the latching relay even when power is removed from the system.
    Type: Grant
    Filed: November 9, 2011
    Date of Patent: March 11, 2014
    Assignee: The Boeing Company
    Inventor: Bruce Van Deventer
  • Patent number: 8641154
    Abstract: A system and procedures for adjusting brake mechanisms for an aircraft having an electric brake system are disclosed. The brake actuator mechanisms are controlled to achieve different parking brake actuation states as a function of the current engine run status (e.g., engine off, engine idle, or engine above idle). Procedures for adjusting an aircraft parking brake as disclosed herein include setting the brake actuator mechanisms to achieve a relatively low clamping force when the aircraft engines are off or idling, and setting the brake mechanisms to achieve a relatively high clamping force when the aircraft engines are running above idle, and to maintain commanded brake force without active or battery power by engaging a mechanical clutch or latch to the brake actuator.
    Type: Grant
    Filed: October 9, 2006
    Date of Patent: February 4, 2014
    Assignee: The Boeing Company
    Inventors: T. Todd Griffith, Pete Goranson, Dan Adkinson
  • Patent number: 8634971
    Abstract: A system, apparatus and method provide a means for managing wear of brake friction material such that even friction material wear is experienced between brakes. The available friction material of each brake is monitored to determine an amount of wear. Based on the amount of wear, a braking force applied by each brake may be varied to ensure even wear between brakes.
    Type: Grant
    Filed: May 5, 2009
    Date of Patent: January 21, 2014
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill
  • Patent number: 8584989
    Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.
    Type: Grant
    Filed: September 20, 2011
    Date of Patent: November 19, 2013
    Assignee: Messier-Bugatti-Dowty
    Inventors: David Lemay, David Frank, Michel Basset, Yann Chamaillard
  • Patent number: 8567874
    Abstract: The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs.
    Type: Grant
    Filed: July 28, 2011
    Date of Patent: October 29, 2013
    Assignee: Hydro-Aire, Inc.
    Inventors: Gary DeVlieg, John Gowan
  • Patent number: 8560150
    Abstract: Methods and systems for a go/no-go Landing Decision Point (LDP) are disclosed. The methods and systems provide a graphical LDP on a cockpit display that pilots can use to determine whether to continue the landing or execute a go-around. The methods and systems may be implemented in embodiments having an onboard portion, an off-board portion, or both operatively coupled to provide an LDP in a preview/planning mode and real time mode.
    Type: Grant
    Filed: July 5, 2011
    Date of Patent: October 15, 2013
    Assignee: The Boeing Company
    Inventors: Thomas J. Phillips, Jean M. Crane
  • Patent number: 8548652
    Abstract: A brake monitoring system is described for use on aircraft having carbon brakes. The system displays the number of times the brakes have been applied in a preselected counting interval such as during each takeoff and landing cycle. By raising the pilot's awareness of the number of times the brakes have been applied, a more efficient brake use is encouraged in view of the knowledge that carbon brake wear is substantially a function of the number of applications rather than the total energy that is converted thereby. Additionally, the monitoring system provides an indication of the temperature of the brakes which encourages the pilot to maintain a minimum temperature therein beyond which wear is reduced.
    Type: Grant
    Filed: January 31, 2006
    Date of Patent: October 1, 2013
    Assignee: Hydro-Aire, Inc., subsidiary of Crane Co.
    Inventors: Garrett H. DeVlieg, John Gowan
  • Patent number: 8463462
    Abstract: Systems and methods are provided that may he useful for testing braking systems for use in, for example, an aircraft. A system is disclosed that allows for built in testing. For example, a method if provided comprising sending, from a brake controller, a test command set to at least one of an electromechanical actuator (EMAC) and a brake servo valve (BSV) in response to a landing gear retraction, receiving, at the brake controller, feedback from the at least one of the EMAC and the BSV in response to the test command set, and comparing, at the brake controller, the feedback with a predetermined signature.
    Type: Grant
    Filed: September 2, 2011
    Date of Patent: June 11, 2013
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill
  • Patent number: 8423256
    Abstract: Systems and methods for adaptive deceleration are disclosed. A brake system controller may perform a method comprising receiving a pedal deflection signal comprising a pedal deflection level, determining a present level of deceleration, and mapping the pedal deflection level to a desired level of deceleration, wherein the desired level of deceleration is greater than the present level of deceleration.
    Type: Grant
    Filed: December 23, 2009
    Date of Patent: April 16, 2013
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill
  • Patent number: 8403429
    Abstract: A balanced brake control system is provided for use in aircraft. An embodiment of the invention is presented for an aircraft having struts with both inboard and outboard braked wheels on the struts. In the detailed embodiment, an equalizer circuit is interposed between right and left brake pedals on an input side thereof and right and left inboard and outboard brakes on an output side thereof. This equalizer circuit ensures a first equal application of brake pressure to the right inboard and outboard brakes and a second equal application of brake pressure to the left inboard and outboard brakes, dependent upon pilot control of brake pedals. The first and second equal applications of brake pressure may differ to accommodate differential braking.
    Type: Grant
    Filed: April 15, 2011
    Date of Patent: March 26, 2013
    Assignee: Meggitt Aircraft Braking Systems
    Inventors: Richard P. Hurst, Arnold A. Beck
  • Patent number: 8393689
    Abstract: An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be unable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition.
    Type: Grant
    Filed: December 22, 2006
    Date of Patent: March 12, 2013
    Assignee: The Boeing Company
    Inventors: T. Todd Griffith, David T. Yamamoto, Andreea D. Uta
  • Patent number: 8386094
    Abstract: A taxi brake inhibit system overcomes problems of discontinuities in pedal “feel” that can occur by use of a taxi brake inhibit system, by adding a new pedal “feel” logic in which twice the brake force is commanded for a given brake pedal application when taxi brake inhibit is active. The taxi brake inhibit system relies upon two different brake force vs. brake pedal application curves to compensate for the difference in deceleration that is achieved for a given brake pedal application depending upon whether the taxi brake inhibit is active or inactive. Such system effectively eliminates undesirable deceleration bumps, yaw effects and changes in pedal feel during braking. The taxi brake inhibit feature is also shut off to both fore-aft brake pairs if any non-normal taxi brake inhibit condition exists on either fore-aft brake pair.
    Type: Grant
    Filed: January 27, 2010
    Date of Patent: February 26, 2013
    Assignee: Hydro-Aire, Inc.
    Inventors: Garrett H. DeVlieg, John Gowan
  • Patent number: 8332114
    Abstract: A braking system (1) for an aircraft which includes a by-pass control system (9) for activation when undemanded braking or loss of braking is detected.
    Type: Grant
    Filed: November 8, 2007
    Date of Patent: December 11, 2012
    Assignee: Meggitt Aerospace Ltd.
    Inventor: Andrew Whittingham
  • Patent number: 8326506
    Abstract: The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: December 4, 2012
    Assignee: Hydro-Aire, Inc.
    Inventors: Ronald Raby, Jordan Silberling
  • Patent number: 8312973
    Abstract: The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: November 20, 2012
    Assignee: Hydro-Aire, Inc.
    Inventors: Gary DeVlieg, John Gowan
  • Patent number: 8280603
    Abstract: Systems and methods for determining aircraft brake pedal sensor failure are provided. A brake pedal sensor and/or a brake pedal may be “failed” if brake pedal sensor readings unlikely to be generated as a result of human input are detected. The method comprises acquiring brake pedal measurements from a brake pedal sensor, determining a state of the brake pedal sensor, and providing a notification of the state. Each brake pedal measurement comprises a brake pedal deflection amount. The brake pedal sensor test algorithm may be conducted at regular intervals, in preparation for aircraft landing, at the request of a human operator, and the like.
    Type: Grant
    Filed: March 9, 2009
    Date of Patent: October 2, 2012
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill
  • Patent number: 8214090
    Abstract: Disclosed is a method and device for generating a yaw rate command for an aircraft along a ground trajectory. The yaw rate command is generated by determining a current curvature, lateral deviation and angular deviation of the ground trajectory. A yaw rate calculator then calculates a yaw rate and generates the yaw rate command based on the determined current curvature, lateral deviation and angular deviation.
    Type: Grant
    Filed: December 8, 2008
    Date of Patent: July 3, 2012
    Assignee: Airbus Operations SAS
    Inventors: Fabrice Villaume, Pierre Scacchi
  • Patent number: 8180548
    Abstract: A system, apparatus and method of controlling a brake system of a vehicle having a brake input device, such as a brake pedal, a plurality of rotating wheels and a plurality of brakes, each brake of the plurality of brakes corresponding to one wheel of the plurality of wheels, is provided. In controlling the brakes, data indicative of a deflection of the brake pedal is received, and the received data is used to derive a target deceleration rate. A braking command is provided to each of the plurality of brakes, wherein the braking command is varied for each brake to regulate a deceleration rate the vehicle in accordance with the target deceleration rate.
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: May 15, 2012
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill
  • Patent number: 8172340
    Abstract: The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs.
    Type: Grant
    Filed: May 10, 2011
    Date of Patent: May 8, 2012
    Assignee: Hydro-Aire, Inc., Subsidiary of Crane Co.
    Inventors: Gary DeVlieg, John Gowan
  • Patent number: 8152247
    Abstract: A wheel brake for an aircraft, the brake comprising a support (2) that receives at least one electromechanical actuator (1) fitted with a pusher (8) facing friction elements (3) and movable under drive from an electric motor (6) to apply a braking force selectively against the friction elements. The actuator is non-reversible such that a reaction force applied on the pusher cannot cause the electric motor to turn, and the actuator is associated with elements (30, 31, 32, 33, 34) for selectively switching off an electric power supply to the electric motor, which elements allow power to be delivered to the actuator in normal circumstances, and switch off the power if (a) the measured speed of rotation (wmes) of the electric motor drops below a first predetermined threshold (S1); and (b) the commanded speed of rotation ( ?) of the electric motor drops below a second predetermined threshold (S2).
    Type: Grant
    Filed: February 9, 2009
    Date of Patent: April 10, 2012
    Assignee: Messier-Bugatti-Dowty
    Inventor: Emmanuel Colin
  • Patent number: 8147006
    Abstract: An anti-skid brake control system for a multi-wheeled vehicle includes both a paired function and an individual function. The paired function controls the wheels of the vehicle in unison. The individual function controls the wheels of the vehicle individually. A paired/individual logic circuit alternatively activates and deactivates the paired function and the individual function. A method for controlling the skid of a vehicle utilizing a paired function and a individual function is also provided.
    Type: Grant
    Filed: July 7, 2010
    Date of Patent: April 3, 2012
    Assignee: Hydro-Aire, Inc., a Subsidiary of Crane Co.
    Inventors: Harris K. Butler, III, Scott A. Brittian
  • Patent number: 8132757
    Abstract: A pitch-oscillation limitation system, applied to an aircraft having main landing gear located toward the center of the aircraft and forward landing gear located under the nose of the aircraft, wherein the system includes means for automatically applying, in the event of sudden braking, time-deferred braking between the wheels of the landing gear under the wings and the wheels of the landing gear under the fuselage, so as to reduce the amplitude of the aircraft's pitching motion.
    Type: Grant
    Filed: July 8, 2008
    Date of Patent: March 13, 2012
    Assignee: Airbus France
    Inventors: Olivier Regis, Gregory Sicault, Emmanuel Kopp
  • Patent number: 8118373
    Abstract: The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force.
    Type: Grant
    Filed: January 7, 2011
    Date of Patent: February 21, 2012
    Assignee: Hydro-Aire, Inc.
    Inventors: Gary DeVlieg, John Gowan
  • Patent number: 8112213
    Abstract: A system, apparatus and method provide a means for controlling an electric brake actuator. An electromechanical actuator controller (EMAC) is configured to receive first data indicative of a desired braking force, second data indicative of a braking command generated by a brake input device, the second data different from said first data, and third data indicative of a braking mode. Based on the third data, the EMAC selectively uses the first data or the second data to control the actuator.
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: February 7, 2012
    Assignee: Goodrich Corporation
    Inventors: Eric D. Cahill, Lawrence F. Corio, Bill May, Andrew B. Walsh, Scott Snelling
  • Patent number: 8083295
    Abstract: The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel.
    Type: Grant
    Filed: July 16, 2008
    Date of Patent: December 27, 2011
    Assignee: Hydro-Aire, Inc.
    Inventors: Ronald Raby, Jordan Silberling
  • Publication number: 20110278915
    Abstract: The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs.
    Type: Application
    Filed: July 28, 2011
    Publication date: November 17, 2011
    Applicant: HYDRO-AIRE, INC., SUBSIDIARY OF CRANE CO.
    Inventors: Gary DeVlieg, John Gowan
  • Publication number: 20110278916
    Abstract: The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs.
    Type: Application
    Filed: July 28, 2011
    Publication date: November 17, 2011
    Applicant: HYDRO-AIRE, INC., SUBSIDIARY OF CRANE CO.
    Inventors: Gary DeVlieg, John Gowan
  • Patent number: 8029074
    Abstract: A method for providing anti-skid braking control for a vehicle having a plurality of wheels, each wheel including a corresponding wheel speed sensor and brake, wherein when velocity data from at least one wheel speed sensor is lost, velocity data from a wheel speed sensor coupled to a different wheel is used as the wheel speed for the wheel with the non-operational sensor.
    Type: Grant
    Filed: February 21, 2008
    Date of Patent: October 4, 2011
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill