Landing Gear Indicator Patents (Class 340/960)
  • Patent number: 12039392
    Abstract: A fastener accessory includes a fastener body and a sacrificial radio frequency (RF) tag. A dielectric substrate of the tag is affixed to a contact surface of the fastener body. An RF antenna trace is connected to or printed on the substrate. The antenna trace transmits an RF response signal when energized by an external RF tracking circuit. The substrate is plastically deformed by an installation force to prevent transmission of the response signal. A method for locating the fastener body within a search area includes exciting a receiver trace of the tag using an interrogation signal, frequency-modulating an interrogation frequency using an RF modulating circuit, transmitting a response signal at a response frequency via a transmitting antenna trace of the tag, and detecting the response signal using an RF tracking circuit to locate the fastener body within the search area.
    Type: Grant
    Filed: September 8, 2021
    Date of Patent: July 16, 2024
    Assignee: The Boeing Company
    Inventor: Matthew L. Prendergast
  • Patent number: 11763684
    Abstract: A joint-decision making system for a vehicle operator and a dispatcher is disclosed, comprising: a vehicle operator engine implemented on a vehicle system configured to: detect a trigger event condition; retrieve vehicle information relevant to the event trigger condition; receive additional information relevant to the event trigger condition; generate a suggested response based on the trigger event condition, retrieved vehicle information, and received additional information; display the suggested response on a graphical user interface of the vehicle operator engine; and transmit the trigger event condition, vehicle information, and suggested response to a dispatcher engine; and the dispatcher engine implemented on a ground system configured to: receive the event trigger condition, vehicle information, and suggested response from the vehicle operator engine; retrieve the additional information relevant to the event trigger condition; and display the suggested response on a graphical user interface of the dis
    Type: Grant
    Filed: February 22, 2021
    Date of Patent: September 19, 2023
    Assignee: Honeywell International Inc.
    Inventors: Yi Zhong, Raghu Shamasundar, Dan Li, Ramkumar Rajendran, Kalimulla Khan, Visakh Sivadasan
  • Patent number: 11560028
    Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for payload estimation and fault detection using hitch integrated sensors. An example apparatus includes a pin orientation determiner to determine a first orientation of a first pin and a second orientation of a second pin, the first pin and the second pin disposed within a hitch and calculate a relative orientation of the first pin and the second pin based on the first orientation and the second orientation. The example apparatus further includes a hitch condition detector to determine if a physical change has occurred in the hitch by comparing the relative orientation to an installation orientation of the first pin and the second pin.
    Type: Grant
    Filed: June 7, 2019
    Date of Patent: January 24, 2023
    Assignee: Ford Global Technologies, LLC
    Inventors: Kevin Stanton Giaier, Andrew Niedert, Elliott Pearson, Anton Rogness
  • Patent number: 11541993
    Abstract: An adjustment tool for adjusting a maneuvering mechanism of a main landing gear of an aircraft, the landing gear having a plurality of wheels. The tool includes a telemeter, a locking system for locking the telemeter on the external face of a wheel, a wireless communication unit that is connected to the telemeter and makes it possible, when the tool is being used, to connect the telemeter with a control device provided with a display screen.
    Type: Grant
    Filed: March 3, 2021
    Date of Patent: January 3, 2023
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Antoine Rouiller, Jérémy Bonjean, Alain Segart
  • Patent number: 11492093
    Abstract: A system for displaying the state of an aircraft cargo door. The cargo door is configured pivot between a closed position and an open position, the closed and open positions defining a pivoting range. The cargo door is lockable both in the closed position and in the open position. The cargo door is in a regular state when locked in the closed position or the open position. The cargo door is in a warning state when in the pivoting range between the closed position and open position. The cargo door is in a faulty state when unlocked in the closed position or unlocked in the open position or when there is an obstacle in the pivoting range. The cargo door comprises at least one indicator configured to display the respective state of the cargo door, the indicator being detectable from a distance of at least 7.5 m.
    Type: Grant
    Filed: May 29, 2019
    Date of Patent: November 8, 2022
    Assignee: AIRBUS OPERATIONS GMBH HAMBURG
    Inventors: Ulf Kehlenbeck, Matias Mail, Sascha Rodewald, Philippe Raviart
  • Patent number: 11416871
    Abstract: An aircraft operation method of providing weight and center of gravity information is used to dispatch the aircraft. The aircraft has telescoping landing gear struts and strut seals that interfere with the free movement of the strut. An event trigger signaling departure is detected from aircraft operations at a loading area. Internal strut pressure is measured and recorded upon detection for a period of time as the aircraft moves away. The recorded pressure measurements are transmitted to a first off-aircraft computer, which determines the total weight and center of gravity of the aircraft and provides the information to an operator of the aircraft.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: August 16, 2022
    Inventor: C Kirk Nance
  • Patent number: 11407524
    Abstract: An aircraft undercarriage comprising a top portion (2) secured to the aircraft and a steerable bottom portion (3) carrying wheels and suitable for being steered by a steering control system (4) fitted to the undercarriage or else by an external towing device, the undercarriage being fitted with visual warning means (9) for indicating an angular overstroke. The visual warning means comprising at least one visual indicator (14) mounted to move between a retracted position that is invisible and an extended position that is visible. An aircraft provided with an undercarriage.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: August 9, 2022
    Assignee: SAFRAN LANDING SYSTEMS
    Inventors: Philippe Fernandes, Marc Farcy, Christophe Clement
  • Patent number: 11180130
    Abstract: An apparatus and method is disclosed for determining a temperature characteristic at a first location on a wheel or a brake assembly of an aircraft landing gear. The temperature characteristic at the first location is determined using relationship information based on a first temperature at a second location of the wheel or the brake assembly of the landing gear, the relationship information representing a relationship between the temperature characteristic at the first location and the first temperature. Also disclosed is a method to determine the relationship information.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: November 23, 2021
    Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS (S.A.S.), AIRBUS (S.A.S.)
    Inventors: Rodrigo Jimenez, Brice Cheray, Maud Consola
  • Patent number: 10777028
    Abstract: A method for estimating the damage to rotational driving actuators of the wheels borne by aircraft undercarriages. First, in service, recording data relating to the driving actuators, in particular data on torque developed by the driving actuators, on speed of rotation of the motors of the driving actuators, on number of revolutions of the motors. Then, deducing therefrom damage undergone by the driving actuators. Finally, estimating a remaining life of the driving actuators.
    Type: Grant
    Filed: October 10, 2017
    Date of Patent: September 15, 2020
    Assignee: SAFRAN LANDING SYSTEMS
    Inventor: Frederik Giraud
  • Patent number: 10112702
    Abstract: A hard-landing detection system includes a wheel assembly, a shock strut mechanically coupled to the wheel assembly and to landing gear structure of the landing gear assembly, a controller having a processor, and a tangible, non-transitory memory configured to communicate with the processor. The tangible, non-transitory memory has instructions stored thereon that, in response to execution by the processor, cause the hard-landing detection system to perform operations that include detecting, by the processor, a landing event and determining, by the processor, whether the landing event is hard. The hard-landing system may further include a stroke position sensor and detecting the landing event may include using the stroke position sensor to measure a stroke profile of the shock strut. Further, determining whether the landing event is hard may include comparing, by the processor, the stroke profile of the shock strut to a predetermined maximum shock strut stroke.
    Type: Grant
    Filed: February 8, 2017
    Date of Patent: October 30, 2018
    Assignee: GOODRICH CORPORATION
    Inventors: Adnan Cepic, Amir Fazeli, Susanne Reber
  • Patent number: 9285007
    Abstract: A method and system of monitoring condition of a shock strut senses gas temperature, gas pressure, and stroke of the strut during a landing event. Oil loss is determined based upon a deviation of a transient pressure coefficient derived from transient gas pressures at two different strokes from a nominal coefficient value. Gas loss is determined based upon a temperature adjusted transient gas pressure at a selected stroke and a nominal gas pressure value at the selected stroke.
    Type: Grant
    Filed: June 27, 2014
    Date of Patent: March 15, 2016
    Assignee: Goodrich Corporation
    Inventors: Amir M. Fazeli, Adnan Cepic, Susanne M. Reber
  • Publication number: 20150145703
    Abstract: Methods to monitor components of an aircraft landing system are disclosed herein. An example method includes determining a brake assembly temperature and determining a wheel temperature. The example method also includes retrieving an estimated increase in the wheel temperature from a data structure based on the wheel temperature and the brake assembly temperature. The example method further includes determining a maximum wheel temperature based on the wheel temperature and the estimated increase in the wheel temperature.
    Type: Application
    Filed: November 22, 2013
    Publication date: May 28, 2015
    Applicant: The Boeing Company
    Inventor: Casandra Jolene Martin
  • Publication number: 20150002318
    Abstract: Tire pressure monitoring systems and methods for detecting a tire burst are disclosed. The system may include a tire pressure sensor, a tire pressure monitor, and a tire burst indicator. The tire pressure sensor may measure tire pressure in an aircraft tire. The tire pressure monitor may analyze data from the tire pressure sensor to detect a tire burst. A tire burst may be detected in response to a rapid decrease in tire pressure. In response to detecting a tire burst, the tire pressure monitor may transmit a tire burst message to the tire burst indicator. The tire burst indicator may indicate to a pilot that a tire burst has been detected.
    Type: Application
    Filed: June 27, 2013
    Publication date: January 1, 2015
    Inventor: Eric Cahill
  • Patent number: 8902084
    Abstract: A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manual rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators.
    Type: Grant
    Filed: January 31, 2013
    Date of Patent: December 2, 2014
    Assignee: Messier-Dowty Inc.
    Inventor: Gary Ataman
  • Patent number: 8897935
    Abstract: This disclosure relates to a system for preventing collisions with a terrain. The system includes a detecting means for detecting risks of collision with the terrain after a predetermined forecasting delay. The system further includes a determining means for determining, based on a trajectory followed by the aircraft, a possible limit point for success of the vertical terrain avoidance maneuver. The system further includes indication means for giving indications on azimuth clearance sections, around the direction in which the aircraft is moving, suitable for success of the vertical terrain avoidance maneuver. The system further includes means for estimating a free-travel distance in each azimuth clearance sector on a straight distancing trajectory with constant gradient and over a distance correspond to more than one minute of flight, the free-travel distance being free of potential conflicts with the terrain.
    Type: Grant
    Filed: August 29, 2007
    Date of Patent: November 25, 2014
    Assignee: Thales
    Inventors: Hugues Meunier, Nicolas Marty, Julia Percier
  • Patent number: 8886402
    Abstract: Methods and apparatus are provided for an actively variable shock absorbing system for actively controlling the load response characteristics of a shock absorbing strut. In one embodiment the shock absorbing system comprises a controllable valve adapted for actively varying a load response characteristic of the shock absorbing strut. The shock absorbing system further comprises an electronic control system comprising an input for receiving a signal from a sensor, an algorithm adapted to determine an optimal position for the controllable valve in view of the sensor signal, and an output for sending a control signal to the controllable valve to place the valve in the optimal position.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: November 11, 2014
    Assignee: Armorworks Enterprises LLC
    Inventor: Ken-An Lou
  • Publication number: 20140210647
    Abstract: A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manually rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators.
    Type: Application
    Filed: January 31, 2013
    Publication date: July 31, 2014
    Applicant: MESSIER-DOWTY INC.
    Inventor: Gary Ataman
  • Patent number: 8565965
    Abstract: A system for use in monitoring, measuring, recording, computing and transmitting the oxygen levels and identification of oxygen contamination within an aircraft telescopic landing gear strut. An oxygen sensor is mounted in relation to each of the landing gear struts as to monitor, recognize, measure and record the identification of oxygen within the telescopic landing gear struts. The amount of oxygen within each landing gear strut is measured and recorded and downloaded to the responsible aircraft maintenance department. By detecting the amount of oxygen in a strut, steps can be taken to purge the gas from the strut to minimize corrosion of strut components and to prevent internal combustion of the gas and oil in the strut.
    Type: Grant
    Filed: March 28, 2012
    Date of Patent: October 22, 2013
    Inventor: C. Kirk Nance
  • Patent number: 8565968
    Abstract: A system for use in monitoring, measuring, computing and displaying the volumes of internal liquid and gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of hydraulic oil and nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.
    Type: Grant
    Filed: August 30, 2011
    Date of Patent: October 22, 2013
    Inventor: C. Kirk Nance
  • Patent number: 8531314
    Abstract: A visual display used to indicate when aircraft wheel chocks have been inserted against the aircraft tires and the tarmac. The display is mounted on the exterior of an aircraft terminal at an elevation that is easily viewable by an aircraft operator. The indicator system contains illuminated characters operated from an electrical switch. The electrical switch is located remotely from the display where it is accessible by personnel standing on the tarmac. The switch positions include “OUT” and “IN”. When the switch is moved to the “IN” position, the arrow characters are illuminated. When the switch is moved to the “OUT” position, the arrow characters are not illuminated. This system provides a safe and efficient means for ground personnel to signal the aircraft operator that the wheel chocks are in place against the aircraft wheel assembly.
    Type: Grant
    Filed: November 14, 2010
    Date of Patent: September 10, 2013
    Inventor: Kim Perkins
  • Patent number: 8446294
    Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.
    Type: Grant
    Filed: August 11, 2009
    Date of Patent: May 21, 2013
    Assignee: Messier-Dowty Inc.
    Inventor: R. Kyle Schmidt
  • Patent number: 8400330
    Abstract: A system for displaying first and second images to a pilot of an aircraft includes, but is not limited to, a sensor subsystem that detects a light transmission originating from outside the aircraft and generates a first signal indicative of the light transmission, a dynamic condition sensor that detects a dynamic condition of the aircraft and generates a second signal indicative of the dynamic condition of the aircraft, a display unit, and a processor that is communicatively coupled to the sensor subsystem and to the dynamic condition sensor and operatively coupled to the display unit. The processor is configured to command the display unit to display a first image corresponding to the first signal, to display a second image overlaid over the first image corresponding to the second signal, and to modify the appearance of the second image to enhance the pilot's ability to discern the first image.
    Type: Grant
    Filed: October 25, 2010
    Date of Patent: March 19, 2013
    Assignee: Honeywell International Inc.
    Inventors: Gang He, Thea L. Feyereisen
  • Patent number: 8390479
    Abstract: A device for locking a movable component of an aircraft. The device includes an electronic tag adapted for receiving a polling signal and returning an identification signal. An on-board system allows detection of such locking devices.
    Type: Grant
    Filed: May 9, 2007
    Date of Patent: March 5, 2013
    Assignee: Airbus
    Inventor: Richard Wilby
  • Patent number: 8374737
    Abstract: A low visibility landing system is provided for guiding aircraft on landing approaches. The low visibility landing system may aid a pilot during landing in low visibility conditions such that an aircraft may descend to lower altitudes without visual contact with the runway than is possible with other landing systems. The system may use various navigational systems to produce a hybrid signal that may be more stable than individual signals of those navigational systems. The hybrid signal is compared to a predetermined landing approach plan to determine the deviation of the aircraft from the landing approach plan and to provide guidance to the pilot to get the aircraft back onto the landing approach plan. The system may also use multiple navigational systems to perform checks on an operation of a primary navigational system to ensure that the primary navigational system is operating accurately.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: February 12, 2013
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Robert S. Takacs, Gary M. Freeman, Glenn L. Connor
  • Publication number: 20130021173
    Abstract: A method and apparatus for displaying aircraft information. A selection of a piece of dynamic information is detected about an aircraft on a first display on a user interface. The piece of dynamic information is used to operate the aircraft and changes during operation of the aircraft. The piece of dynamic information selected from the first display is added to a custom display on the user interface. The custom display is displayed on the user interface on a display system for the aircraft.
    Type: Application
    Filed: November 22, 2011
    Publication date: January 24, 2013
    Applicant: THE BOEING COMPANY
    Inventors: Cindy Chi-Lan Huang, Eduardo Raul Cajavilca
  • Patent number: 8350726
    Abstract: Methods and apparatus are provided for selecting a touchdown point for a vertical takeoff and landing aircraft. The eye movements of a user are tracked relative to an image being rendered on a display screen. An updated touchdown point location is determined from the tracked eye movements, and an updated touchdown point is rendered at the updated touchdown point location on the display screen.
    Type: Grant
    Filed: May 19, 2009
    Date of Patent: January 8, 2013
    Assignee: Honeywell International Inc.
    Inventors: Santosh Mathan, Patricia May Ververs
  • Publication number: 20120326894
    Abstract: A method of protecting an aircraft undercarriage (1) while it is being towed by means of a tow bar (13) hitched to a steerable bottom portion of the undercarriage, the method including the step of generating an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold. The threshold is caused to vary as a function of an orientation of the steerable bottom portion of the undercarriage.
    Type: Application
    Filed: March 31, 2011
    Publication date: December 27, 2012
    Applicant: MESSIER-BUGATTI-DOWTY
    Inventors: Robert Kyle Schmidt, Jean-Luc Alleau
  • Patent number: 8339284
    Abstract: A visual display system is provided, and includes a visual display element configured to display a visual display with three-dimensional, conformal background information at a first perspective; and a processor coupled to the visual display. The processor can be configured to evaluate flight path information and to adjust the visual display into a second perspective if the flight path information cannot be accurately displayed at the first perspective relative to the background.
    Type: Grant
    Filed: March 11, 2008
    Date of Patent: December 25, 2012
    Assignee: Honeywell International Inc.
    Inventor: Gang He
  • Patent number: 8255174
    Abstract: A method and device for determining critical buffeting loads on a structure of an aircraft is disclosed. The device (1) comprises means (2, UC) implementing a semi-empirical method for determining the critical loads generated by some buffeting on the structure of the airplane.
    Type: Grant
    Filed: May 27, 2010
    Date of Patent: August 28, 2012
    Assignee: Airbus Operations (SAS)
    Inventors: Guillermo Jenaro Rabadan, Juliane Havas, Stéphane Soumillon, Carole Despre-Flachard
  • Patent number: 8235326
    Abstract: An aircraft landing gear comprising a fibre optic load sensor for monitoring load in a component of the landing gear, such as an axle. The fibre optic cable is mounted on an inner surface of the component of the landing gear. Typically the fibre optic load sensor comprises one or more Bragg Grating sensors.
    Type: Grant
    Filed: July 1, 2008
    Date of Patent: August 7, 2012
    Assignee: Airbus Operations Limited
    Inventors: Stephen Briancourt, Trajan Seymour
  • Publication number: 20120119925
    Abstract: A visual display used to indicate when aircraft wheel chocks have been inserted against the aircraft tires and the tarmac. The display is mounted on the exterior of an aircraft terminal at an elevation that is easily viewable by an aircraft operator. The indicator system contains illuminated characters operated from an electrical switch. The electrical switch is located remotely from the display where it is accessible by personnel standing on the tarmac. The switch positions include “OUT” and “IN”. When the switch is moved to the “IN” position, the arrow characters are illuminated. When the switch is moved to the “OUT” position, the arrow characters are not illuminated. This system provides a safe and efficient means for ground personnel to signal the aircraft operator that the wheel chocks are in place against the aircraft wheel assembly.
    Type: Application
    Filed: November 14, 2010
    Publication date: May 17, 2012
    Inventor: Kim Perkins
  • Publication number: 20120056759
    Abstract: A system for displaying first and second images to a pilot of an aircraft includes, but is not limited to, a sensor subsystem that detects a light transmission originating from outside the aircraft and generates a first signal indicative of the light transmission, a dynamic condition sensor that detects a dynamic condition of the aircraft and generates a second signal indicative of the dynamic condition of the aircraft, a display unit, and a processor that is communicatively coupled to the sensor subsystem and to the dynamic condition sensor and operatively coupled to the display unit. The processor is configured to command the display unit to display a first image corresponding to the first signal, to display a second image overlaid over the first image corresponding to the second signal, and to modify the appearance of the second image to enhance the pilot's ability to discern the first image.
    Type: Application
    Filed: October 25, 2010
    Publication date: March 8, 2012
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Gang He, Thea L. Feyereisen
  • Patent number: 8102280
    Abstract: Systems and methods to determine whether a brake is dragging based on post-takeoff spindown data are provided. The method comprises measuring spindown of a wheel to obtain spindown data. The spindown data is compared with a spindown envelope, and notification is provided if the spindown data indicates a wheel is spinning down outside a spindown envelope.
    Type: Grant
    Filed: March 3, 2009
    Date of Patent: January 24, 2012
    Assignee: Goodrich Corporation
    Inventor: Eric D. Cahill
  • Patent number: 8094042
    Abstract: A steering angle warning system comprising a rotation-measuring unit located on an aircraft, and an alarm unit. The rotation-measuring unit is arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage. The alarm unit is arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value, for example, 60 degrees. The rotation-measuring unit may also be arranged to perform a function in relation to an aircraft steering system, for example to indicate the steering angle to the pilot during ground manoeuvres.
    Type: Grant
    Filed: February 23, 2007
    Date of Patent: January 10, 2012
    Assignee: Airbus Operations Limited
    Inventors: Terry George Read, Andreas Yiasoumi, David George Stinchcombe, Andrew David Sadler, Alex Robert Piddock
  • Patent number: 8055396
    Abstract: A landing gear monitor for aircraft landing gear including a plurality of pairs of wheels on a bogie, in which the main strut oil pressure serves to indicate landing load and is monitored in relation to, respectively, the two-wheel mode and the four-wheel mode, the two-wheel mode being the condition when a first of the plurality of pairs of wheels on the bogie contacts the ground and the four-wheel mode being the condition of a first and a second of the plurality of pairs of wheels on the bogie being in full contact with the ground.
    Type: Grant
    Filed: August 23, 2006
    Date of Patent: November 8, 2011
    Assignee: Airbus Operations Limited
    Inventors: Michael Stuart Yates, Philip Gregory Keen
  • Patent number: 7944372
    Abstract: A tip alarm system for an aircraft having a nose landing gear (NLG) includes a sensor having first and second parts respectively disposed on first and second portions of the NLG that are respectively fixed to the aircraft and moveable relative to the fixed portion and operable to detect the position of the first and second portions relative to each other and to produce a tip alarm signal when the first and second NLG portions are disposed at a selected position relative to each other corresponding to an imminent aircraft tipping condition and thereby prevent the aircraft from tipping back onto the ground due to improper loading of the aircraft.
    Type: Grant
    Filed: April 18, 2008
    Date of Patent: May 17, 2011
    Assignee: The Boeing Company
    Inventors: Geoffrey E. Gouette, Steven B. White, James M. Merrick, Kristine K. Weed, Paul A. VanGinhoven, Steven L. Wehr, Ralph E. Fossen, Farid Piroozmandi, Brian L. Collen, Sudershan K. Taneja
  • Patent number: 7844392
    Abstract: The field of the invention is that of optoelectronic taxi-assistance devices for aircraft, including a head-up display providing for the presentation of information in the pilot's field of vision. The invention applies in particular to large civil aircraft of the Boeing 747 or Airbus A380 type. The object of the invention is to propose the displaying of safety-related symbologies in the head-up display, providing for substantially improving aircraft safety and maneuverability during the taxiing phase. These symbologies relate substantially to the position of the aircraft on the taxiway and to the turning and stop maneuvers to be performed by the pilot. Said symbologies are particularly useful in poor visibility conditions.
    Type: Grant
    Filed: February 18, 2005
    Date of Patent: November 30, 2010
    Assignee: Thales
    Inventor: Bernard Dubourg
  • Publication number: 20100225503
    Abstract: Systems and methods to determine whether a brake is dragging based on post-takeoff spindown data are provided. The method comprises measuring spindown of a wheel to obtain spindown data. The spindown data is compared with a spindown envelope, and notification is provided if the spindown data indicates a wheel is spinning down outside a spindown envelope.
    Type: Application
    Filed: March 3, 2009
    Publication date: September 9, 2010
    Applicant: GOODRICH CORPORATION
    Inventor: Eric D. Cahill
  • Publication number: 20100114411
    Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.
    Type: Application
    Filed: August 11, 2009
    Publication date: May 6, 2010
    Applicant: Messier-Dowty Inc.
    Inventor: R. KYLE SCHMIDT
  • Patent number: 7589645
    Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.
    Type: Grant
    Filed: June 12, 2006
    Date of Patent: September 15, 2009
    Assignee: Messier-Dowty Inc.
    Inventor: R. Kyle Schmidt
  • Publication number: 20090207047
    Abstract: According to one embodiment, a verification system for an aircraft includes a cockpit instrument in communication with a wireless communication circuit. The wireless communication circuit is coupled to a landing gear member and operable to determine a position of the landing gear member and transmit the position to the cockpit instrument using a wireless signal.
    Type: Application
    Filed: February 20, 2008
    Publication date: August 20, 2009
    Applicant: Raytheon Company
    Inventor: W. Anthony Ross, III
  • Publication number: 20090091476
    Abstract: The present invention provides a lock sensor for use in an actuator such as is used in aircraft landing gear systems. The lock sensor comprises at least one field emitting device (46) mounted on a locking actuator pressure vessel where the field emitting device (46) monitors the position of at least one target (48). The field emitting device (46) emits a field that when breached by the target sends a signal to indicate that the actuator is in a locked state.
    Type: Application
    Filed: August 30, 2005
    Publication date: April 9, 2009
    Applicant: MESSIER-DOWTY, INC.
    Inventors: Gary Stephen Ataman, Mark Coffin, Robert Kyle Schmidt
  • Publication number: 20090040072
    Abstract: A steering angle warning system comprising a rotation-measuring unit located on an aircraft, and an alarm unit. The rotation-measuring unit is arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage. The alarm unit is arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value, for example, 60 degrees. The rotation-measuring unit may also be arranged to perform a function in relation to an aircraft steering system, for example to indicate the steering angle to the pilot during ground manoeuvres.
    Type: Application
    Filed: February 23, 2007
    Publication date: February 12, 2009
    Applicant: AIRBUS UK LIMITED
    Inventors: Terry George Read, Andreas Yiasoumi, David George Stinchcombe, Andrew David Sadler, Alex Robert Piddock
  • Patent number: 7414545
    Abstract: A system to identify junctions of restricted areas to approaching vehicles, including at least one warning signal generator, at least one antenna coupled to the generator transmitting the warning signal into areas traversed by the vehicles approaching the restricted areas, a receiver in each of the vehicles receiving the transmitted warning signals when the vehicle approaches one of the restricted areas, and an alarm responsive to the warning signal, which produces an alarm signal detectable by a vehicle operator.
    Type: Grant
    Filed: November 17, 2004
    Date of Patent: August 19, 2008
    Inventor: George Vickas
  • Patent number: 7274310
    Abstract: A system for use in monitoring, measuring, computing and displaying the Kinetic Energy generated and experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.
    Type: Grant
    Filed: September 13, 2005
    Date of Patent: September 25, 2007
    Inventor: C. Kirk Nance
  • Patent number: 7274309
    Abstract: A system for use in monitoring, measuring, computing and displaying the initial touch-down descent velocity experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.
    Type: Grant
    Filed: September 13, 2005
    Date of Patent: September 25, 2007
    Inventor: C. Kirk Nance
  • Patent number: 7212135
    Abstract: Method and system for monitoring and comparing, in real time, performance of an aircraft during an approach to touchdown along a conventional approach path and along a contemplated modified approach path to touchdown. In a first procedure, a flight parameter value at a selected location is compared and displayed, for the planned path and for the modified path. In a second procedure, flight parameter values FP(tn) at a sequence {tn}n of measurement times is compared and displayed, for the planned path and for a contemplated or presently-executed modified path. If the flight parameter for the planned path and for the modified path differ too much from each other, the pilot in command has an option of terminating the approach along the modified path.
    Type: Grant
    Filed: February 22, 2005
    Date of Patent: May 1, 2007
    Assignee: United States of America as represented by the Administrator of the National Aeronautics and Space Administration (NASA)
    Inventors: Robert E. Lynch, Thomas R. Chidester, Robert E. Lawrence
  • Patent number: 7193530
    Abstract: A system for use in monitoring, measuring, computing and displaying the landing loads experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft sink rates; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the landing loads experienced by each landing gear strut and determines if a hard landing event has occurred. Additional features include automating the inspections required to aircraft components, after overweight or hard landing events.
    Type: Grant
    Filed: March 29, 2005
    Date of Patent: March 20, 2007
    Inventor: C. Kirk Nance
  • Patent number: 6927702
    Abstract: The present invention provides for a computer that accepts inputs from a surface monitor to determine whether the terrain below the aircraft is water or land. In a preferred embodiment an improved landing gear warning system is provided to warn a pilot when landing gear of an aircraft are in the improper configuration for a landing on a particular surface. The warning system comprises a computer operatively connected to a surface monitor and a gear-status warning indicator. The computer also accepts an input from the gear status sensors to determine if the landing gear is extended or retracted. If the system senses a water surface and the landing gear is down, a warning light and/or buzzer alerts the pilot that the landing gear is in the incorrect configuration. If the landing surface is land and the gear is up, the “gear status” indicator warning is initiated.
    Type: Grant
    Filed: June 11, 2002
    Date of Patent: August 9, 2005
    Inventor: Robert D. Wiplinger
  • Patent number: 6704634
    Abstract: A method and system for braking aircraft landing gear wheels after initialization of landing gear retraction. The system includes monitors, controlling components, measurement components, a fault recording memory, fault annunciation components, wheel braking system and brakes. The monitors monitor speed of the landing gear wheels and landing gear position. The control component generates braking instructions based on the monitored speed of the wheels and position of the landing gear.
    Type: Grant
    Filed: November 6, 2002
    Date of Patent: March 9, 2004
    Assignee: The Boeing Company
    Inventors: John J. Gowan, Scott D. Maxwell, Tu-Luc H. Nguyen, Beth L. Sundquist