Attitude (including Yaw, Angle Of Attack, Roll, Pitch, Glide Slope) Patents (Class 340/967)
  • Patent number: 10571318
    Abstract: A simple device for accurately measuring real-time air flows along a wall, and relating to a measuring device including an optical sensor configured to measure an illuminance distribution on a free surface of the optical sensor. A mobile member movably is mounted on the light sensor by partially covering its free surface, the mobile member being adapted to be freely directed by a local air flow pattern, thus, modulating the illuminance distribution on the free surface so as a current illuminance distribution measurement by the optical sensor indicates the current direction of the mobile member representing the current air flow pattern.
    Type: Grant
    Filed: September 14, 2016
    Date of Patent: February 25, 2020
    Assignees: AIRBUS (S.A.S.), Airbus Operations (S.A.S.)
    Inventors: Jean-Luc Vialatte, Philippe Tatry, Gilles Studer, Laurent Malard, Nicolas Benoit
  • Patent number: 10336467
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: July 2, 2019
    Assignee: Safe Flight Instrument Corporation
    Inventors: Randall A. Greene, Shawn P. Beyer, Robert D. Teter
  • Patent number: 9828113
    Abstract: An aircraft tailstrike warning method includes identifying a first value representing an aircraft angle of attack, identifying a second value representing a maximum aircraft angle of attack, identifying a difference between the first value and the second value, and providing a tailstrike warning when the difference between the first value and the second value is less than a threshold amount.
    Type: Grant
    Filed: November 5, 2013
    Date of Patent: November 28, 2017
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. Greene, Shawn Beyer
  • Patent number: 9701422
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: July 11, 2017
    Assignee: Safe Flight Instrument Corporation
    Inventors: Randall A. Greene, Shawn P. Beyer, Robert D. Teter
  • Patent number: 9384586
    Abstract: An image processing system for enhanced flight vision includes a processor and memory coupled to the processor. The memory contains program instructions that, when executed, cause the processor to receive radar returns data for a runway structure, generate a three-dimensional model representative of the runway structure based on the radar returns data, generate a two-dimensional image of the runway structure from the three-dimensional model, and generate an aircraft situation display image representative of the position of the runway structure with respect to an aircraft based on the two-dimensional image.
    Type: Grant
    Filed: June 10, 2014
    Date of Patent: July 5, 2016
    Assignee: Rockwell Collins, Inc.
    Inventors: Patrick D. McCusker, Richard D. Jinkins, Richard M. Rademaker
  • Publication number: 20150123821
    Abstract: An aircraft tailstrike warning method includes identifying a first value representing an aircraft angle of attack, identifying a second value representing a maximum aircraft angle of attack, identifying a difference between the first value and the second value, and providing a tailstrike warning when the difference between the first value and the second value is less than a threshold amount.
    Type: Application
    Filed: November 5, 2013
    Publication date: May 7, 2015
    Applicant: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. GREENE, Shawn BEYER
  • Patent number: 9008870
    Abstract: A terrain warning system includes an indicator to inform a pilot of a proposed degree of flight parameters for safely clearing terrain. An aural message may identify a vertical speed that may be used to safely traverse terrain to the pilot. A visual indicator on a display informs the pilot of a vertical speed or climb angle to traverse terrain. The display may be a vertical speed indicator also capable of displaying traffic advisories.
    Type: Grant
    Filed: March 14, 2003
    Date of Patent: April 14, 2015
    Assignee: Aviation Communication & Surveillance Systems LLC
    Inventors: James Peter Redmond, Richard Darrell Ridenour
  • Patent number: 8976043
    Abstract: A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft.
    Type: Grant
    Filed: August 20, 2012
    Date of Patent: March 10, 2015
    Assignee: Textron Innovations, Inc.
    Inventor: Robert Edward Voros
  • Publication number: 20150054663
    Abstract: A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated.
    Type: Application
    Filed: October 1, 2014
    Publication date: February 26, 2015
    Inventors: Sean M. Pennell, Noah Eric Aaron, Darren Gordon McDonald
  • Publication number: 20150022380
    Abstract: A system and method monitor aircraft state parameters, for example, aircraft movement and flight parameters, applies those inputs to a spatial disorientation model, and makes a prediction of when pilot may become spatially disoriented. Once the system predicts a potentially disoriented pilot, the sensitivity for alerting the pilot to conditions exceeding a threshold can be increased and allow for an earlier alert to mitigate the possibility of an incorrect control input.
    Type: Application
    Filed: July 16, 2013
    Publication date: January 22, 2015
    Inventors: Kevin J Conner, Santosh Mathan, Steve Johnson
  • 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: 20140232568
    Abstract: A method and apparatus for monitoring an aircraft. A pilot control input signal is received. A response of a control surface system controlled by a flight control model is identified using the pilot control input signal. An alert is generated when the control surface system reaches a threshold with respect to the control surface system becoming saturated.
    Type: Application
    Filed: February 18, 2013
    Publication date: August 21, 2014
    Applicant: THE BOEING COMPANY
    Inventor: THE BOEING COMPANY
  • Publication number: 20140218216
    Abstract: A vehicle system is provided. The system includes a processor configured to receive data representative of a current attitude and a desired attitude and to generate display signals associated with the current attitude and the desired attitude. The system further includes a display device configured to receive the display signals and operable to selectively render an image including roll angle alert symbology. The roll angle alert symbology includes a first curved arrow.
    Type: Application
    Filed: May 23, 2013
    Publication date: August 7, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: HONEYWELL INTERNATIONAL INC.
  • Patent number: 8767013
    Abstract: Methods and systems are provided for improving pilot situational awareness during brown-over-brown display situations. An image is rendered, on a display, that includes one of, or both, rendered terrain and rendered sky. A sky veil is at least selectively rendered on a portion of the display. The sky veil, when rendered, is rendered at least partially transparent and in a manner that portions of the sky veil that overlap with rendered sky are not discernable, and rendered terrain is viewable through portions of the sky veil that overlap with terrain.
    Type: Grant
    Filed: December 7, 2011
    Date of Patent: July 1, 2014
    Assignee: Honeywell International Inc.
    Inventors: Vivek Jain, David A. Wright, Jason F. Harvey, Jary Engels
  • Patent number: 8723696
    Abstract: Present novel and non-trivial system, device, and method for generating location information presented to a pilot are disclosed. A processing unit is configured to receive manual input data representative of one or more selected image location(s) on a first image data set; determine a selected geographic location for each selected image location; and update the second image data set to include location pointer data. As embodied herein, first and second images represented in the first and second image data sets, respectively, could be displayed simultaneously on the same display unit or separately on different display units. Also, the first image and second image could correspond to an egocentric view and a plan view, respectively, or vice-versa. Additionally, the first image data set and/or second image data set could be updated include first and/or second location pointer data, respectively.
    Type: Grant
    Filed: August 6, 2012
    Date of Patent: May 13, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Travis S. VanderKamp, David A. Frank
  • Patent number: 8674851
    Abstract: A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: March 18, 2014
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Jean Muller, Stéphane Delannoy
  • Patent number: 8653990
    Abstract: A method and system for indicating a potential stall condition for an aircraft during flight. An alert lift coefficient is identified for the aircraft. The alert lift coefficient is adjusted in response to a number of changes in a current state of the aircraft. A set of thresholds is identified for use in generating an alert indicating that the aircraft has reached the potential stall condition using the alert lift coefficient.
    Type: Grant
    Filed: June 18, 2012
    Date of Patent: February 18, 2014
    Assignee: The Boeing Company
    Inventors: Joseph Michael Smyth, IV, Frank J. Lyman
  • Patent number: 8571728
    Abstract: Present novel and non-trivial systems and methods for embedding aircraft attitude data within a pixel data set and detecting inconsistent aircraft attitude information are disclosed. A pixel data set representative of the scene outside the aircraft is generated based upon the navigation data and the terrain data, attitude-exclusive data is generated based upon orientation data, and attitude-exclusive data is embedded into the pixel data set to form an embedded pixel data set. Attitude-exclusive data is comprised of attitude-exclusive pixel data having first and second pixel locations or attitude-exclusive ancillary data. Attitude-exclusive data is compared against separately-provided reference attitude data for the purpose of detecting inconsistent attitude information.
    Type: Grant
    Filed: February 18, 2010
    Date of Patent: October 29, 2013
    Assignee: Rockwell Collins, Inc.
    Inventors: Jason C. Wenger, Travis S. VanderKamp
  • Patent number: 8538669
    Abstract: Methods and apparatus are provided for transmitting incursion alerts to a plurality of in-flight aircraft in accordance with preconfigured pilot preferences. The apparatus comprises a data store module containing data sets against which the pilot preferences are evaluated during flight, including weather, airspace and flight restrictions, ground delay programs, and air traffic information. The apparatus further includes a flight path module containing route and position information for each aircraft. An incursion alert processing module evaluates the flight path, data store, and pilot preferences and generates incursion alerts which are transmitted to each aircraft during flight, either directly or via ground based dispatchers or flight operations personnel.
    Type: Grant
    Filed: September 9, 2011
    Date of Patent: September 17, 2013
    Assignee: Honeywell International Inc.
    Inventors: Anand Agarwal, David Brabham, Trip Redner, SatyaBhaskar Payasam
  • Patent number: 8457889
    Abstract: A display system and method for a vehicle are provided. The display system includes a processor configured to receive data representative of a waypoint and terrain and to supply display commands associated with the waypoint and the terrain; and a display device coupled the processor for receiving the display commands and operable to render three-dimensional terrain and a first symbol elevated from the terrain representing the waypoint.
    Type: Grant
    Filed: March 31, 2008
    Date of Patent: June 4, 2013
    Assignee: Honeywell International Inc.
    Inventors: Thea L. Feyereisen, Gang He, Ivan Wyatt
  • Patent number: 8421649
    Abstract: Aircraft attitude systems are provided, in which a representative system includes: an instrument face having a bank angle scale, a bank status indicator, a pitch angle scale and a pitch status indicator; the bank angle scale being fixed in position relative to the instrument face and being operative to present increments of bank angle of an aircraft; the bank status indicator being operative to move relative to the bank angle scale such that a current aircraft bank angle is indicated; the pitch angle scale being fixed in a vertical orientation relative to the instrument face and being operative to present increments of pitch angle of an aircraft; the pitch status indicator being operative to move relative to the pitch angle scale such that a current aircraft pitch angle is indicated.
    Type: Grant
    Filed: February 21, 2011
    Date of Patent: April 16, 2013
    Inventors: Jerry Lee Marstall, Shakeel Mozaffar
  • Patent number: 8405516
    Abstract: A method executes a gyroscope function to unlock a portable electronic device. A user can rotate the portable electronic device to set a predetermined rotation direction and a predetermined rotation angle for unlocking the portable electronic device. In an unlock procedure, the gyroscope detects the rotated portable electronic device and outputs detected information of the portable electronic device. If the rotation direction and the rotation angle are the same as the predetermined rotation direction and the predetermined rotation angle, the locked portable electronic device is unlocked.
    Type: Grant
    Filed: August 31, 2010
    Date of Patent: March 26, 2013
    Assignee: Chi Mei Communications Systems, Inc.
    Inventors: Po-Tai Huang, Chia-Hui Liao
  • Patent number: 8295997
    Abstract: The present invention relates to a pilot assistance method for giving assistance in piloting a rotary wing aircraft, the method consisting in using a scale with collective pitch graduations that is movable on a display screen to indicate the position of the collective pitch, in determining the desynchronization pitch, in using a maximum limit value and a minimum limit value for the speed of rotation of the rotor, in transforming the maximum limit value and the minimum limit value in real time and as a function of physical flight parameters respectively into a bottom limit position and a top limit position for the collective pitch, and when a determined difference appears between the real value and the reference value Nr0 for the speed of rotation of the rotor, in displaying at least one item of corrective information about the adjustment of the collective pitch.
    Type: Grant
    Filed: March 11, 2010
    Date of Patent: October 23, 2012
    Assignee: Eurocopter
    Inventors: Karine De Bono, Michel Godard
  • Patent number: 8219265
    Abstract: A display system and method for an aircraft simultaneously displays the terrain under the flight plan, or under the current track of the aircraft, as both a two-dimensional lateral situation view image and as a perspective vertical situation view image. This provides improved tactical flight planning, and that does not erroneously show the flight plan passing through the displayed terrain.
    Type: Grant
    Filed: August 25, 2009
    Date of Patent: July 10, 2012
    Assignee: Honeywell International Inc.
    Inventors: David B. Dwyer, Troy A. Nichols, Mathew Hilbert, Michael C. Little
  • Patent number: 8200421
    Abstract: An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve with the altitude profile, the terrain avoidance maneuver is interrupted.
    Type: Grant
    Filed: October 20, 2009
    Date of Patent: June 12, 2012
    Assignee: Airbus Operations SAS
    Inventors: Paule Botargues, Nicolas Caule, Christelle Ledauphin, Jerome Bailly, Isabelle Lacaze, Sylvain Thezelais, Jerome Goyet
  • Patent number: 8190309
    Abstract: Disclosed is a method and device for detecting lateral dissymmetry of an aircraft. A control parameter determination unit is used to determine a current value of a control parameter representative of all roll control surfaces of the aircraft, and a control parameter comparison unit is used to compare the determined current value with a predetermined reference value. A current deflection angle of a lateral stick of the aircraft is also determined, and the determined current deflection angle is compared with a predetermined angle value. A visual alarm signal is output, when the current value of the roll control surfaces of the aircraft is greater than a predetermined reference value and the lateral stick is at a deflection angle that is greater than a predetermined angle value.
    Type: Grant
    Filed: February 14, 2007
    Date of Patent: May 29, 2012
    Assignee: Airbus Operations SAS
    Inventors: Regis Boe, Dominique Chatrenet
  • Patent number: 8164487
    Abstract: A present novel and non-trivial system, module, and method for presenting messages to a pilot of an aircraft are disclosed. The system comprises a source for providing message data, a message generating (“MG”) processor, and a presentation system. Message data received from a message data source includes data fields for providing message location on a flight plan and one or more modes of presentation. After receiving the message data, an MG processor generates a message presentation data set corresponding to the message data; the message presentation data set represents a message object shown at the message location on a flight plan and at least one presentation mode. Then, a presentation system receives the message presentation data set and presents the information contained in such data set to one or more units of the presentation system including a visual display unit and/or an aural alert unit.
    Type: Grant
    Filed: September 18, 2009
    Date of Patent: April 24, 2012
    Assignee: Rockwell Collins, Inc.
    Inventor: Hung-i B. Tsai
  • Patent number: 8160809
    Abstract: A method is provided for automatically controlling a first vehicle (follower vehicle) that is to follow a second vehicle (leader vehicle) in a desired manner with respect to movement of the second vehicle. In the follower vehicle, bearing and acceleration control inputs are generated based on data representing bearing and acceleration control inputs made at the leader vehicle and a position of the follower vehicle relative to the leader vehicle so as to mimic in the follower vehicle the bearing and acceleration control inputs made in the leader vehicle. Adjustments may be made to the control inputs applied in the follower vehicle based on deviation between the velocity of the follower vehicle and velocity of the leader velocity, and on deviation between estimated (actual) follow distance and lateral offset and target follow distance and lateral offset between the follower vehicle and the leader vehicle.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: April 17, 2012
    Assignee: Exelis Inc.
    Inventors: Mark Lalon Farwell, Chad Martin Seldomridge, Robert Eric Larson
  • Patent number: 8098175
    Abstract: The invention relates to aircraft instrument panel equipment. According to the invention, the proposal is for an instrument panel which, in addition to a main display system for horizon and necessary piloting parameters, comprises two items of equipment identical from the point of view of hardware and the point of view of software, each provided with a display screen, automatic pilot set point adjustment buttons, computing means and standby data (standby horizon, altitude, speed). In normal operating conditions, one of the items of equipment is configured in an “automatic pilot set point display” mode; its control buttons are used to give the set points to the automatic pilot computer, and the set points are displayed on the screen. The other item of equipment is configured in “integrated standby data display” mode. It displays on the screen the standby horizon, the standby speed and the standby altitude. The mode may be switched at will or in the event of a failure of one of the two items of equipment.
    Type: Grant
    Filed: October 23, 2003
    Date of Patent: January 17, 2012
    Assignee: Thales
    Inventors: Nicolas Berthou, Bruno Aymeric, Jean-Yves Favard
  • Patent number: 8098176
    Abstract: Systems and methods for improving landing gear alerting on a rotary wing aircraft. An example system includes a user interface device that allows a user to set a bug altitude value and a radio altimeter that produces an altitude value, both of which are in communication with a processor. The processor receives a bug altitude setting, generates a landing gear alert altitude value based on the received bug altitude setting and a predefined additive, receives a radio altitude value for the rotary-wing aircraft, and generates a landing gear alert if the radio altitude value is less than the landing gear alert altitude value and the landing gear is not in a landing position. An output device in signal communication with the processor, outputs the generated landing gear alert.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: January 17, 2012
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Steve Johnson, Gary Ostrom
  • Patent number: 8086396
    Abstract: A method is provided for automatically controlling a first vehicle (follower vehicle) that is to follow a second vehicle (leader vehicle) in a desired manner with respect to movement of the second vehicle. In the follower vehicle, bearing and acceleration control inputs are generated based on data representing bearing and acceleration control inputs made at the leader vehicle and a position of the follower vehicle relative to the leader vehicle so as to mimic in the follower vehicle the bearing and acceleration control inputs made in the leader vehicle. Adjustments may be made to the control inputs applied in the follower vehicle based on deviation between the velocity of the follower vehicle and velocity of the leader velocity, and on deviation between estimated (actual) follow distance and lateral offset and target follow distance and lateral offset between the follower vehicle and the leader vehicle.
    Type: Grant
    Filed: December 7, 2006
    Date of Patent: December 27, 2011
    Assignee: ITT Manufacturing Enterprises, Inc.
    Inventors: Mark Lalon Farwell, Chad Martin Seldomridge, Robert Eric Larson
  • Patent number: 8078343
    Abstract: The general field of the invention relates to devices for controlling the two attitude reference units of the AHRS type for aircraft, each AHRS comprising at least a first set of magnetometer measurements and at least a second set of gyroscopic measurements, each AHRS having two modes of operation, the first mode, called slave mode supplying the flight system with the information coming from the first set, the second mode, called DG mode supplying the flight system with the information coming from the second set. The device according to the invention comprises a display and means for displaying within this display a control window for these two attitude reference units, said window comprising three regions, the first region dedicated to the first AHRS unit, the second region dedicated to the second AHRS unit, the third region dedicated to the simultaneous control of the two AHRS units.
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: December 13, 2011
    Assignee: Thales
    Inventors: Thierry Ferreira, Sylvie Loizeau
  • Patent number: 8063798
    Abstract: Embodiments include systems and methods for assisting a pilot of an aircraft. The system includes a near-eye display and a processing subsystem. The near-eye display includes a transparent display panel that is adapted to be oriented in proximity to at least one eye of the pilot. The processing subsystem is adapted to receive aircraft data that indicates an attitude of the aircraft, and to determine whether the aircraft data indicates a potential spatial disorientation situation. When the aircraft data indicates the potential spatial disorientation situation, the processing system is adapted to cause the near-eye display to display an exterior display indicator overlying at least a portion of the windshield of the aircraft. The exterior display indicator includes a visual representation of an earth-based reference, and the exterior display indicator is oriented to indicate the attitude of the aircraft.
    Type: Grant
    Filed: June 3, 2008
    Date of Patent: November 22, 2011
    Assignee: Honeywell International Inc.
    Inventors: Andrei Cernasov, Robert Mead, Fernando de la Vega
  • Patent number: 8060296
    Abstract: Systems and methods for determining center of gravity for an aircraft. An example system includes one or more load measurement devices that generate one of nose gear or main gear weight information and a processing device that determines center of gravity of the aircraft based on previously received gross weight information and the generated nose or main gear weight information. The number of gear sets with load measurement devices is one less that the total number of gear sets having distinct longitudinal positions along a fuselage of the aircraft. The processing device further determines center of gravity based on temperature and/or pitch attitude information. The system includes a user interface that allows a user to enter the gross weight information that might be included in a flight manifest or a load and trim sheet and/or a communication component that receives the gross weight information from a ground-based system.
    Type: Grant
    Filed: November 12, 2008
    Date of Patent: November 15, 2011
    Assignee: Honeywell International Inc.
    Inventor: LeRoy E. Vetsch
  • Patent number: 8049644
    Abstract: A terrain advisory display including a display, a processing circuit coupled to the display and wherein the display is configured to generate a three-dimensional image.
    Type: Grant
    Filed: April 17, 2007
    Date of Patent: November 1, 2011
    Assignee: Rcokwell Collins, Inc.
    Inventors: Steve L. Oehlert, Jason C. Wenger, Alex Postnikov, Andrew M. Pelzer, Sarah Barber
  • Patent number: 8031209
    Abstract: A method for displaying an operating parameter for a mobile platform. A plurality of different graphs can be digitized to place them in electronic form. Each graph represents a different operational or environmental characteristic relating to operation of the mobile platform, and each is further related to a common parameter. A first one of the digitized graphs is selected by a user. A user positionable marker is displayed on the first digitized graph at a specific, user selected location on the first digitized graph. Next a second one of the digitized graphs is selected. The second one of the digitized graphs is then overlayed over at least a portion of the first digitized graph, with the marker remaining visible and superimposed on the second digitized graph, and without having moved relative to the first digitized graph. The second digitized graph is then aligned relative to the first digitized graph. The marker is then used to assist in reading information from the second digitized graph.
    Type: Grant
    Filed: December 11, 2007
    Date of Patent: October 4, 2011
    Assignee: The Boeing Company
    Inventor: Mark L. Sadler
  • Patent number: 8019491
    Abstract: A system and method for generating lateral guidance image data and presenting information representative of the image data is disclosed. A system is disclosed for determining lateral guidance information based upon the elevation of terrain cells and a level of terrain threat associated with the elevation. A left or right turn angle, or both could be formed between a projected flight path and a vector extending to a tangent point of a terrain boundary to the left and right, respectively. The degree of angle could be determined for each, and lateral guidance image data based upon the boundary location of a level of terrain threat with respect to the projected flight path determined. A lateral processor provides an alert signal associated with the generation of the lateral guidance information and provide such signal to a crew visual and aural alerting system.
    Type: Grant
    Filed: September 27, 2007
    Date of Patent: September 13, 2011
    Assignee: Rockwell Collins, Inc.
    Inventor: Patrick D. McCusker
  • Patent number: 8014910
    Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.
    Type: Grant
    Filed: May 4, 2006
    Date of Patent: September 6, 2011
    Assignee: Airbus France
    Inventors: Gerard Mathieu, Franck Delaplace, Xavier Le Tron
  • Patent number: 7957852
    Abstract: An aviation yoke HSI interface and flight deck control indicator and selector safety system enhances flight safety. The system incorporates a multi-controlled HSI with a yoke heading adjustment control, a yoke VOR radial selector, and a yoke heading centering control positioned on the captain yoke. The system may also incorporate a first officer multi-controlled HSI with a first officer yoke heading adjustment control, a first officer yoke VOR radial selector, and a first officer yoke heading and course centering control positioned on the first officer yoke. An autopilot mode indicator visually indicates whether an autopilot is flying according to a desired heading or according to a VOR radial signal. A side selector-indicator control permits selection of which side controls the flight of the aircraft. A first control unit and a second control unit may be in electrical communication with both sides to fly the aircraft in autopilot.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: June 7, 2011
    Inventor: Stephen Baxter
  • Patent number: 7952493
    Abstract: A flight deck display element for an aircraft includes a primary flight display rendered thereon. The primary flight display includes a primary display region having a perimeter, a perspective view of terrain corresponding to a flight deck viewpoint, and an attitude frame surrounding the perimeter of the primary display region. The perspective view of terrain is rendered in the primary display region, and the attitude frame includes a first region and a second region rendered with different visually distinguishable characteristics. The boundaries of the first region and the second region are defined by a current attitude condition of the aircraft.
    Type: Grant
    Filed: December 10, 2008
    Date of Patent: May 31, 2011
    Assignee: Honeywell International Inc.
    Inventors: Ivan Sandy Wyatt, Jary Engels
  • Patent number: 7840315
    Abstract: An aviation yoke HSI interface and flight deck control indicator and selector safety system enhances flight safety. The system incorporates a multi-controlled HSI with a yoke heading adjustment control, a yoke VOR radial selector, and a yoke heading centering control positioned on the captain yoke. The system may also incorporate a first officer multi-controlled HSI with a first officer yoke heading adjustment control, a first officer yoke VOR radial selector, and a first officer yoke heading and course centering control positioned on the first officer yoke. An autopilot mode indicator visually indicates whether an autopilot is flying according to a desired heading or according to a VOR radial signal. A side selector-indicator control permits selection of which side controls the flight of the aircraft. A first control unit and a second control unit may be in electrical communication with both sides to fly the aircraft in autopilot.
    Type: Grant
    Filed: November 27, 2006
    Date of Patent: November 23, 2010
    Inventor: Stephen Baxter
  • Publication number: 20100292872
    Abstract: The device (1) includes means (2, 3, 4) for observing the overall conditions of the aircraft and for determining whether the lateral behaviour thereof is normal.
    Type: Application
    Filed: May 14, 2010
    Publication date: November 18, 2010
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Pierre Ezerzere, Stephane Puig
  • Patent number: 7825830
    Abstract: This simplified self powered aircraft attitude survival indicator is easily and readily transportable from one aircraft to another and provides a simple indicator which gives a visual indication of aircraft attitude and alarms when the aircraft is in a dangerous attitude. The aircraft attitude indicator includes a housing containing a power source, multiple attitude sensors, and at least one piezoelectric alarm, and a front panel display with an arrangement of light emitting elements (electric bulbs or LEDs) providing visual attitude indicators.
    Type: Grant
    Filed: October 26, 2007
    Date of Patent: November 2, 2010
    Inventor: Danny C. Joyner
  • Patent number: 7783393
    Abstract: A vertical situation display system for use in a vehicle such as, for example, an aircraft, is provided. A side view of an intended route of flight may be shown with altitude restrictions, airspace and instrument approach information, a projected flight path and range to airspeed symbol. The system may show terrain, weather, and traffic information along the intended route of flight. The system may be used in conjunction with a navigational display to enhance situational awareness. The system includes a computer, an electronic display device, an electronic entry device, a memory and a database. The database may contain terrain, airspace and flight planning data and may be updatable.
    Type: Grant
    Filed: June 30, 2004
    Date of Patent: August 24, 2010
    Assignee: The Boeing Company
    Inventors: Michael J. Tucker, Sherwin S. Chen, John Wiedemann, Jason L. Hammack
  • Patent number: 7772994
    Abstract: A system and method for displaying aircraft glide slope includes determining a glide slope deviation that is representative of a difference between a desired aircraft glide slope and an actual aircraft glide slope. A glide slope icon that is representative of the desired aircraft glide slope and a glide slope deviation icon that is representative of the determined glide slope deviation are simultaneously rendered on a display.
    Type: Grant
    Filed: January 11, 2007
    Date of Patent: August 10, 2010
    Assignee: Honeywell International Inc.
    Inventor: Gang He
  • Patent number: 7756637
    Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: July 13, 2010
    Assignee: The Boeing Company
    Inventors: Patrick Ralf Wipplinger, Richard William Ellerbrock
  • Patent number: 7724155
    Abstract: An avionics display is disclosed. A synthetic rendering of terrain is created using stored terrain data. A horizon line is overlaid upon the synthetic rendering of terrain. The horizon line represents zero degrees pitch attitude in a direction of travel of an aircraft in which the avionics display is installed. The horizon line is configured to move in response to attitude-changing movement of the aircraft. An attitude cue is overlaid upon the synthetic rendering of terrain and depicted on first and second sides of the horizon line such that the synthetic rendering of terrain remains substantially visible. The attitude cue has a first appearance on the first side of the horizon line and a second appearance on the second side of the horizon line. The first appearance is visually contrasted from the second appearance.
    Type: Grant
    Filed: September 7, 2006
    Date of Patent: May 25, 2010
    Assignee: Rockwell Collins, Inc.
    Inventors: Eric N. Anderson, John C. Frank, Craig D. Pettit, Sarah Barber, Matthew Carrico
  • Publication number: 20100121560
    Abstract: Systems and methods for determining center of gravity for an aircraft. An example system includes one or more load measurement devices that generate one of nose gear or main gear weight information and a processing device that determines center of gravity of the aircraft based on previously received gross weight information and the generated nose or main gear weight information. The number of gear sets with load measurement devices is one less that the total number of gear sets having distinct longitudinal positions along a fuselage of the aircraft. The processing device further determines center of gravity based on temperature and/or pitch attitude information. The system includes a user interface that allows a user to enter the gross weight information that might be included in a flight manifest or a load and trim sheet and/or a communication component that receives the gross weight information from a ground-based system.
    Type: Application
    Filed: November 12, 2008
    Publication date: May 13, 2010
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Le Roy E. Vetsch
  • Patent number: 7714744
    Abstract: An airspace awareness and warning system (“AAWS”) provides input to an airspace alert (“AA”) processor from at least one real-time aircraft system or sensor, a navigation system, and an airspace database containing three-dimensional delineations of defined airspace; the processor determines an airspace clearance surface and an aircraft airspace alert surface, and if one surface penetrates the other, the processor generates an alert signal and provides an alert signal to a crew alerting system. The two surfaces are determined by the processor by executing an algorithm(s) embedded in software containing the disclosed embodiments and methods. At least one criterion used to define an aircraft airspace alert surface is programmed to include real-time and/or static input factor data provided by at least one system or sensor input from an aircraft. Such input factor could be used to define an airspace clearance surface.
    Type: Grant
    Filed: February 8, 2008
    Date of Patent: May 11, 2010
    Assignee: Rockwell Collins, Inc.
    Inventor: Joel M. Wichgers