Speed Patents (Class 340/978)
  • Patent number: 9233762
    Abstract: The display device comprises display means which highlight on a screen, preferably of PFD type, the information useful to the pilot relating to at least one flight parameter, especially while reducing the corresponding scale on said screen.
    Type: Grant
    Filed: October 8, 2013
    Date of Patent: January 12, 2016
    Assignee: Airbus Operations (SAS)
    Inventors: Pascale Louise, Fabien Perrin, Delphine MacDonald, Nicolas Chauveau
  • Publication number: 20140266807
    Abstract: A system and method are provided for graphically displaying airspace data including speed restrictions on an aircraft display. The system comprises an avionics display system coupled to a processor that is configured to retrieve airspace data from a database, display the aircraft data on the display, and display a visual representation of the airspace. Then the processor may alter the format of the visual representation of the airspace to a second visual representation, if the airspace data meets predetermined criteria.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Dilip Kumar Behara, Naveen Venkatesh Prasad Nama, Aaron Gannon, Marc L. Lajeunesse
  • Patent number: 8803709
    Abstract: A method of presenting attitude and heading information of a vehicle on a display to a viewer inside the given vehicle, comprising the steps of: using a 2D display, using data provided by an inertial reference system, using a computer and graphical software for treating the data and defining graphical elements, depicting the graphical elements in 3D on the 2D display, and presenting the attitude and heading information on the 2D display by associating them to at least one graphical element.
    Type: Grant
    Filed: December 8, 2011
    Date of Patent: August 12, 2014
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventor: Sven Schmidt
  • Patent number: 8744768
    Abstract: A method and device establishes trajectory planning, predictions and guidance so as to obtain the satisfaction of a time constraint (RTA). This objective is achieved by undertaking a computation of a trajectory up to the point where the flypast time constraint applies, on the basis of a profile of altitude and speeds, and then by computing the profile of speeds and altitudes making it possible, throughout the computed trajectory, to comply with the RTA. The method is also a method for readapting the trajectory and the vertical profile when during a mission, the data outside the aeroplane have caused the time predictions to drift and the constraint is no longer complied with under the initial speeds and trajectory assumptions.
    Type: Grant
    Filed: November 29, 2010
    Date of Patent: June 3, 2014
    Assignee: Thales
    Inventors: Manuel Gutierez-Castaneda, Philippe Chaix, Benoît Dacre-Wright
  • Patent number: 8706324
    Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.
    Type: Grant
    Filed: March 23, 2011
    Date of Patent: April 22, 2014
    Assignee: Dassault Aviation
    Inventors: Jérôme Barral, Salvador Lopez, Eric Gerard
  • Publication number: 20140106333
    Abstract: In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.
    Type: Application
    Filed: October 17, 2013
    Publication date: April 17, 2014
    Inventor: Brian M. Dugan
  • Patent number: 8665121
    Abstract: Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.
    Type: Grant
    Filed: March 28, 2011
    Date of Patent: March 4, 2014
    Assignee: Cloudahoy, Inc
    Inventor: Tsachi C. Shavit
  • Patent number: 8645008
    Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: February 4, 2014
    Assignee: EADS Deutschland GmbH
    Inventor: Thomas Muensterer
  • Patent number: 8604942
    Abstract: Avionics display system is provided for deployment onboard an aircraft and includes an air traffic data source that provides the avionics display system with data indicative of at least position and velocity of a neighboring aircraft. The system comprises a cockpit display system, and a monitor included within the cockpit display system. The cockpit display system receives and displays position and velocity data pertaining to the neighboring aircraft on the cockpit monitor as a position symbol and a velocity vector graphic. A processor operatively coupled to the monitor is configured to generate an air traffic display on the monitor including symbology indicative of (1) the current position of the neighboring aircraft (2) a velocity of the neighboring aircraft, and (3) the rate-of-change of the velocity of the neighboring aircraft.
    Type: Grant
    Filed: November 8, 2011
    Date of Patent: December 10, 2013
    Assignee: Honeywell International Inc.
    Inventors: Stephen Whitlow, Jan Flasar, Trent Reusser
  • Patent number: 8552888
    Abstract: A device calculates a first air speed representing an estimated air speed during flight using measurements of static pressure and total pressure onboard the aircraft. The device includes a storage device for storing in memory, in case of detection of a ground taxiing of the aircraft, the most recently determined value of static pressure corrected from induced aerodynamic effects. As a result, a second air speed representing the estimated air speed during the ground taxiing may be calculated by implementing a correction and using the most recently determined value of static pressure when the ground taxiing of the aircraft is detected. A method for automatically estimating an air speed of an aircraft is also provided.
    Type: Grant
    Filed: March 31, 2011
    Date of Patent: October 8, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Jean-Damien Perrie, Valérie Brivet, Stéphane Saint-Aroman
  • Patent number: 8509967
    Abstract: The invention relates to a system and a method for calculating flight predictions of an aircraft in which an intermediate prediction horizon is defined between the flight phase and the leg. This horizon, that is called vertical section, is defined such that the limit conditions that are applicable to it, for example the target speed, target altitude, characteristic altitude and maximum end-of-section distance, are valid for the entire vertical section. Thus, it is not necessary, in calculations to check the compatibility of the flight parameters with the applicable constraints, to arbitrarily select the constraint that must be given priority. Furthermore, this intermediate level architecture allows for a greater modularity of the prediction management software and therefore a greater factorization of the developments and greater ease of maintenance.
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: August 13, 2013
    Assignee: Thales
    Inventors: Alexandre Grattard, Nicolas Simi, Alex Bourdon
  • Patent number: 8466809
    Abstract: The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics.
    Type: Grant
    Filed: July 18, 2007
    Date of Patent: June 18, 2013
    Assignee: Thales
    Inventors: Philippe Chesne, Yves Jaulain
  • Patent number: 8386097
    Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.
    Type: Grant
    Filed: March 11, 2008
    Date of Patent: February 26, 2013
    Assignee: Airbus Operations SAS
    Inventors: Jean-Louis de Menorval, Fabrice Lucas, David Gerasimovic
  • Patent number: 8354943
    Abstract: The general field of the invention is, within the framework of the terrain anti-collision systems for aircraft, the presentation on the displays for aiding the piloting and the navigation of a simplified symbology suited to these critical situations. More precisely, the symbols comprise guidance indications in the depictions representing the horizontal and vertical situation indicators as well as speed instructions and altitude instructions, indications relating to the propulsion of the jets as well as guidance messages.
    Type: Grant
    Filed: May 21, 2008
    Date of Patent: January 15, 2013
    Assignee: Thales
    Inventors: Corinne Bacabara, Christian Nouvel
  • Patent number: 8314719
    Abstract: Methods and systems for operating an avionics system are provided. A set of data that is representative of traffic advisory information is received. A visual indicator is displayed to a user based on the set of data that is representative of the traffic advisory information. The traffic advisory information may be received by a user through a receiver and manually entered into an interface for viewing. Alternatively, the avionics system may automatically generate the visual indicator based on the traffic advisory information.
    Type: Grant
    Filed: December 19, 2008
    Date of Patent: November 20, 2012
    Assignee: Honeywell International Inc.
    Inventor: Steven Paul Grothe
  • Patent number: 8223039
    Abstract: A method and a device for detecting a thrust dissymmetry of an aircraft during a landing are disclosed. The detection device (6) comprises means (7) for detecting, upon a landing, that at least one of the engine control levers occupies an intermediary position comprised between a position threshold and a maximum speed position, as well as at least another engine control lever occupies an idling position, and means (9, 13) for triggering a warning when a landing condition is validated and at least one of the control levers occupies said intermediary position, at least another control lever occupying said idling position.
    Type: Grant
    Filed: May 24, 2010
    Date of Patent: July 17, 2012
    Assignee: Airbus Operations (SAS)
    Inventors: Pierre Campagne, Alexandre Broquet, Nicolas Marty
  • Publication number: 20120133529
    Abstract: Embodiments for displaying first and second images to a pilot of an aircraft are presented. The embodiments include, but are not limited to, obtaining a first image signal and a second image signal, commanding a display unit to display a first image on a display screen corresponding to the first signal, and computing an image moving velocity of the first image. The method further comprises estimating an image flow velocity for the second image based on the second image signal and comparing the image moving velocity of the first image to the image flow velocity of the second image. After the comparison, the display unit is commanded to display the second image overlaid on the first image, and commanding the display unit to establish an intensity of the second image within a predefined range based upon the comparison.
    Type: Application
    Filed: November 30, 2010
    Publication date: May 31, 2012
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Gang He
  • Publication number: 20120001774
    Abstract: The present general inventive concept relates to a system of method having an electronic flight display that meets the FAR 23.1311(b) regulatory requirement for redundant backup instruments in the cockpit. The present general inventive concept also provides a system and method to detect failures, obstructions, or improper operation of the aircraft pitot pressure sensing system using a combination of dissimilar sensor data that is independent from each other, e.g., allocated from different sources and employed for different purposes on different displays, and displays information on an avionics display screen.
    Type: Application
    Filed: July 26, 2010
    Publication date: January 5, 2012
    Inventors: Peter Lyons, Jeffrey D. Bethel
  • Publication number: 20110241902
    Abstract: Systems and methods are provided for automated collection and analysis of aircraft flight data. In accordance with one aspect, a system for collecting flight data associated with an aircraft is provided to transmit collected flight data to a remote system for storage and processing. In accordance with another aspect, a remote system utilizes received aircraft location data to determine whether an aircraft flight incident has occurred, and to alert appropriate emergency services. In accordance with another aspect, a remote system analyzes received aircraft flight data and quantitatively evaluates performance of a pilot. In yet another aspect, a system is provided for graphical and textual display of collected aircraft flight data and pilot performance evaluation data.
    Type: Application
    Filed: March 28, 2011
    Publication date: October 6, 2011
    Inventor: Tsachi C. Shavit
  • Publication number: 20110238240
    Abstract: This device for displaying information relative to a flight configuration of the aircraft provided with at least one propulsion system, able to generate a thrust force on said aircraft comprised in a thrust range, said information comprising information relative to an energy variation of the aircraft, is characterized in that the energy variation of the aircraft is expressed by a size representative of this energy variation and homogenous at a gradient of the aircraft, and in that said device is capable of representing a range of energy variations that can be achieved by said aircraft and a current energy variation of said aircraft. Corresponding method and system for displaying an energy variation.
    Type: Application
    Filed: March 23, 2011
    Publication date: September 29, 2011
    Inventors: Jérôme Barral, Salvador Lopez, Eric Gerard
  • Patent number: 7970501
    Abstract: An inertial navigation system which includes a first control system and a second control system is described. The first control system is configured to estimate a vertical velocity based in part on received vertical acceleration data. The second control system is configured to receive the estimated vertical velocity from the first control system and determine a compensated vertical velocity utilizing the estimated vertical velocity and airspeed.
    Type: Grant
    Filed: March 8, 2005
    Date of Patent: June 28, 2011
    Assignee: Honeywell International Inc.
    Inventors: Jeffrey W. Kirkland, John F. Anderson
  • Patent number: 7777647
    Abstract: The field of the invention is that of the display in map form of an operating zone of an aircraft on a screen, and more particularly a method of processing topographic data of this operating zone of an aircraft in real time, based on a calculation of radials (R) centred on a reference point (O) defining an angular segment of topographic data. According to the invention, the method includes a subdivision of the operating zone to be mapped into a plurality of angular segment sections, each forming an individual zone (3), and an assignment of a processing priority and a refresh frequency specific to each individual zone defined according to a criterion of operational interest of the element to the aircraft.
    Type: Grant
    Filed: February 13, 2008
    Date of Patent: August 17, 2010
    Assignee: Thales
    Inventors: Aurélie Sallier, Julia Percier, Nicolas Marty
  • Patent number: 7756632
    Abstract: A system and method are disclosed for computing a vehicle's motion in four dimensions (e.g., three spatial dimensions and time) and reliably predicting the vehicle's arrival time at a predetermined location, by providing a graphical display to an operator of the vehicle's progress that enables the operator to adjust the vehicle's movement and achieve the desired arrival time. Specifically, a system and method are disclosed for computing the movement of an aircraft in four dimensions, predicting its arrival time at a predetermined waypoint, and displaying (in a highly intuitive format) the aircraft's progress in achieving that desired arrival time. The pilot can then adjust the movement (e.g., speed) of the aircraft in accordance with the parameter(s) displayed, in order to achieve the desired arrival time. Thus, for example, numerous aircraft could be scheduled to arrive at a specific final approach waypoint at a predetermined rate (e.g.
    Type: Grant
    Filed: October 13, 2009
    Date of Patent: July 13, 2010
    Assignee: Honeywell International Inc.
    Inventors: John A. Wise, Blake W. Wilson
  • Publication number: 20100164754
    Abstract: The invention relates to a system including two integrated electronics instruments mounted onboard an aircraft and communication links between the two integrated electronics instruments, each integrated electronics instrument including independent determination of flight parameters of the aircraft and display of either flight parameters or navigation parameters of the aircraft. The system also includes a selection module making it possible to choose, from the sensors of the two integrated electronics instruments, those retained for determining the flight parameters. Embodiments of the invention also relate to a method using the system described above. The method includes selecting from the two integrated electronics instruments the sensors retained for determination of the flight parameters according to their availability, and displaying the determined flight parameters on the display of any one or both of the integrated electronics.
    Type: Application
    Filed: July 18, 2007
    Publication date: July 1, 2010
    Applicant: Thales
    Inventors: Philippe Chesne, Yves Jaulain
  • Patent number: 7679529
    Abstract: A method and a system for indicating a target idle running speed, a predicted core speed, a predicted time to running, current engine state or automation modes of an operating aircraft engine, and indicating that the current core speed of the aircraft engine is less than a target idle running speed or is abnormally decreasing towards a target idle running speed. The indicators may be visual or aural. The visual indicators may include graphical or numeric symbols indicating the target idle running speed, the direction of core speed change, the predicted core speed at some future time, or current engine state or automation mode.
    Type: Grant
    Filed: December 7, 2006
    Date of Patent: March 16, 2010
    Assignee: The Boeing Company
    Inventors: Samuel T. Clark, Andrew W. Houck, Joseph A. Sikora, Roglenda R. Bowe
  • Patent number: 7650232
    Abstract: Method and system for analyzing and processing information on one or more aircraft flight paths, using a four-dimensional coordinate system including three Cartesian or equivalent coordinates (x, y, z) and a fourth coordinate ? that corresponds to a distance estimated along a reference flight path to a nearest reference path location corresponding to a present location of the aircraft. Use of the coordinate ?, rather than elapsed time t, avoids coupling of along-track error into aircraft altitude and reduces effects of errors on an aircraft landing site. Along-track, cross-track and/or altitude errors are estimated and compared with a permitted error bounding space surrounding the reference flight path.
    Type: Grant
    Filed: September 22, 2005
    Date of Patent: January 19, 2010
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration (NASA)
    Inventor: Russell A. Paielli
  • Publication number: 20090295600
    Abstract: A flight instrument, having an electronic display, is configured to fit within a standard instrument mount and within an array of standard instrument mounts. The instrument has the ability to emulate any standard or other instrument. This instrument can share its installed optional sensors with other instances of itself that do not include the optional sensors by way of network interfaces. The instrument can contain emulation for all standard instruments and have a menu to select which to display.
    Type: Application
    Filed: June 2, 2008
    Publication date: December 3, 2009
    Inventors: David Robert Stubben, Todd Keller Sprague
  • Patent number: 7623960
    Abstract: A system and method are disclosed for computing a vehicle's motion in four dimensions (e.g., three spatial dimensions and time) and reliably predicting the vehicle's arrival time at a predetermined location, by providing a graphical display to an operator of the vehicle's progress that enables the operator to adjust the vehicle's movement and achieve the desired arrival time. Specifically, a system and method are disclosed for computing the movement of an aircraft in four dimensions, predicting its arrival time at a predetermined waypoint, and displaying (in a highly intuitive format) the aircraft's progress in achieving that desired arrival time. The pilot can then adjust the movement (e.g., speed) of the aircraft in accordance with the parameter(s) displayed, in order to achieve the desired arrival time. Thus, for example, numerous aircraft could be scheduled to arrive at a specific final approach waypoint at a predetermined rate (e.g.
    Type: Grant
    Filed: October 31, 2005
    Date of Patent: November 24, 2009
    Assignee: Honeywell International Inc.
    Inventors: John A. Wise, Blake W. Wilson
  • Publication number: 20080198041
    Abstract: The field of the invention is that of the display in map form of an operating zone of an aircraft on a screen, and more particularly a method of processing topographic data of this operating zone of an aircraft in real time, based on a calculation of radials (R) centred on a reference point (O) defining an angular segment of topographic data. According to the invention, the method includes a subdivision of the operating zone to be mapped into a plurality of angular segment sections, each forming an individual zone (3), and an assignment of a processing priority and a refresh frequency specific to each individual zone defined according to a criterion of operational interest of the element to the aircraft.
    Type: Application
    Filed: February 13, 2008
    Publication date: August 21, 2008
    Applicant: Thales
    Inventors: Aurelie Sallier, Julia Percier, Nicolas Marty
  • Patent number: 7324016
    Abstract: Red, green and white colored lights are emitted from navigation orientation indicating light emitting devices mounted within a helicopter rotor blade near its tip. The light emissions from such devices are under control to respectively indicate passage of the rotor blade through limited arcuate portions of the travel path of the rotor blade end tip. Operational control over the light emitting devices is effected by data processing of outputs from air-speed responsive sensors on the blade end tip.
    Type: Grant
    Filed: November 22, 2005
    Date of Patent: January 29, 2008
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventor: Judah H. Milgram
  • Patent number: 7205907
    Abstract: A graphical display of a nonlinear scale emulating the view of a mechanical drum gauge. The nonlinear scale may be used for the display of aircraft flight data including airspeed, altitude, heading, and other aircraft data suitable for presentation on a nonlinear scale. The nonlinear scale may scroll to display current aircraft data.
    Type: Grant
    Filed: September 15, 2003
    Date of Patent: April 17, 2007
    Assignee: Universal Avionics Systems Corporation
    Inventors: Joachim Laurenz Naimer, Sam Hyatt, Jim Brannen, Tom Lawrence
  • Patent number: 7123749
    Abstract: Apparatus and methods for enhancing the accuracy of height above ground measurements in which the registration error between successive images taken of the terrain over which an aircraft is flying is minimized, the earlier image having first been transformed according to measurements of the aircraft linear and angular velocities, the focal length and attitude of the image sensor, and an initial, coarse height estimate. By an iterative process, a more accurate height estimate is obtained.
    Type: Grant
    Filed: July 24, 2001
    Date of Patent: October 17, 2006
    Assignee: Bae Systems plc
    Inventor: David R Parker
  • Patent number: 7062364
    Abstract: A method and apparatus is disclosed for displaying a dynamic parameter of an aircraft, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing to said scale in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.
    Type: Grant
    Filed: September 26, 2003
    Date of Patent: June 13, 2006
    Assignee: Marivent Corporation
    Inventor: John Maris
  • Patent number: 7015829
    Abstract: A method for displaying flight information includes displaying a first characteristic sign illustrating a speed vector of an aircraft. The method also includes determining a first longitudinal margin of maneuver of the aircraft as a load factor, and displaying a second characteristic sign such that a position of the second characteristic sign relative to the first characteristic sign illustrates the first longitudinal margin of maneuver.
    Type: Grant
    Filed: November 19, 2003
    Date of Patent: March 21, 2006
    Assignee: Airbus France S.A.S.
    Inventors: Eric Godard, David Chabe, Jacques Espinasse
  • Patent number: 6980128
    Abstract: A display system for an aircraft includes a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft. The longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver. The display system also includes a display unit connected to the central unit. The display unit includes a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver.
    Type: Grant
    Filed: November 19, 2003
    Date of Patent: December 27, 2005
    Assignee: Airbus France S.A.S.
    Inventors: Eric Godard, David Chabe, Jacques Espinasse
  • Patent number: 6879887
    Abstract: In an aircraft flight instrument display system having a display screen for displaying flight information, an airspeed indicator is displayed in a vertical tape format, and has a low speed range indicator with a low speed range identified on the airspeed indicator by highlighting the low speed range, and has at least a settable indicator within the low speed range indicating a critical airspeed. The low speed range indicator and the critical airspeed indicator are both set with only manual inputs.
    Type: Grant
    Filed: April 2, 2003
    Date of Patent: April 12, 2005
    Assignee: Honeywell International Inc.
    Inventors: John A. Gaidelis, Jr., Thomas G. Frazier, Jary E. Engels, Thomas M. Leard, Clarence D. Nygaard, Robert C. Odgers, David A. Tunheim, Ivan S. Wyatt
  • Publication number: 20040183699
    Abstract: Method and indicator for displaying information showing the airspeed tolerance margins for an aircraft.
    Type: Application
    Filed: March 16, 2004
    Publication date: September 23, 2004
    Applicant: AIRBUS FRANCE
    Inventors: Pascal Vialleton, Martin Delporte, Jean-Christophe Reinmuth, Jacques Rosay
  • Patent number: 6781512
    Abstract: A novel graphical display apparatus (and methods) for motor vehicles. The apparatus has a display coupled to an interior portion of a motor vehicle and facing a driver of the motor vehicle. The display is coupled to an output for identifying a revolution per minute (RPM) value of an engine of the motor vehicle. The display has a first graphical display portion of the display for outputting a current gear indication of a current gear. The current gear is one of a plurality of gears in the motor vehicle. A second graphical display portion of the display for outputting one or more indication(s) of a past gear is coupled to the first portion of the display. The past gear is one of the plurality of gears in the motor vehicle that is used before the current gear. A third graphical display portion is also coupled to the display. The third display portion outputs an RPM value indication that corresponds to a current RPM value of the engine of the motor vehicle. The RPM value indication is coupled to the output.
    Type: Grant
    Filed: March 1, 2002
    Date of Patent: August 24, 2004
    Assignee: Coato Workshop Inc.
    Inventors: Toshiaki Hayashi, Robert S. Murdock, Norio Fujikawa, Peter Petras
  • Patent number: 6756903
    Abstract: A system and methodology for determining the alertness of a driver of a motor vehicle including sensing at least one first movement characteristic of at least a first part of a motor vehicle, sensing at least one second movement characteristic of at least a second part of the motor vehicle, employing at least one time relationship between the at least one first movement characteristic and the at least one second movement characteristic in order to sense and to distinguish between driver initiated movements and non-driver initiated movements and determining the alertness of the driver of the motor vehicle based on at least one relationship between the driver initiated movements and the non-driver initiated movements.
    Type: Grant
    Filed: December 26, 2001
    Date of Patent: June 29, 2004
    Assignee: Sphericon Ltd.
    Inventors: Dan Omry, Zvi Ben-Ami Slovin
  • Publication number: 20030088342
    Abstract: The device (1) comprises a first means (3) for measuring the effective value of the velocity vector of the aircraft, a computing unit (4) which determines a display value automatically and repetitively and which comprises a filtering means (6) which filters the value measured by the first means (3) so as to form a first term, a display unit (7) for presenting on a screen (2) a characteristic sign illustrating the velocity vector whose position on the screen (2) is representative of the display value, and a second means (9) for determining the derivative of a velocity vector controlled by an aircraft pilot. The computing unit (4) further comprises a computing means (10) which determines a second term from the derivative of the controlled velocity vector and a summator (12) which sums the first and second terms so as to form the display value.
    Type: Application
    Filed: October 4, 2002
    Publication date: May 8, 2003
    Inventors: Eric Godard, David Chabe
  • Patent number: 6489898
    Abstract: The present invention provides an alternative means of displaying aircraft flight information traditionally provided by a standalone rate of turn indicator on the aircraft instrumentation panel. The bank angle effective to achieve a rate of turn equal to a desired rate of turn for an aircraft is displayed to the pilot by generating and displaying one or more bank angle markers on the roll scale of an aircraft attitude indicator. The position of the desired rate of turn bank angle markers may be updated continuously as a function of airspeed and other flight parameters. The present invention enables a pilot to perform a coordinated turn at a desired rate of turn without having to reference a separate rate of turn indicator on the instrumentation panel and/or without having to independently calculate the associated bank angle according to any known “rule of thumb” or other estimation method.
    Type: Grant
    Filed: November 16, 2000
    Date of Patent: December 3, 2002
    Assignee: Honeywell International Inc.
    Inventor: James Nicholls
  • Patent number: 6486799
    Abstract: A human centered informational display is disclosed that can be used with vehicles (e.g. aircraft) and in other operational environments where rapid human centered comprehension of an operational environment is required. The informational display integrates all cockpit information into a single display in such a way that the pilot can clearly understand with a glance, his or her spatial orientation, flight performance, engine status and power management issues, radio aids, and the location of other air traffic, runways, weather, and terrain features. With OZ the information is presented as an integrated whole, the pilot instantaneously recognizes flight path deviations, and is instinctively drawn to the corrective maneuvers. Our laboratory studies indicate that OZ transfers to the pilot all of the integrated display information in less than 200 milliseconds. The reacquisition of scan can be accomplished just as quickly. Thus, the time constants for forming a mental model are near instantaneous.
    Type: Grant
    Filed: July 19, 2000
    Date of Patent: November 26, 2002
    Assignees: The University of West Florida, The United States of America as represented by the Secretary of the Navy
    Inventors: David L. Still, Leonard A. Temme
  • Patent number: 6389354
    Abstract: Terrain navigation apparatus (1) for a stationary or moving vehicle (2) when the apparatus (1) is mounted thereon, including a system (3) for determining position, velocity, altitude and attitude incorporating at least six sensing means operable to provide signals indicative of a first measured height (5), a first velocity (7) and a first position (9) of the vehicle (2), scanning means (11) operable to scan terrain (13) around the vehicle (2) and measure a range (15) from the vehicle (2) thereto, first combining means (17) for combining signals indicative of the first measured height, the range and the first position (5, 15, 9) of the vehicle (2), together with error estimates (19) associated therewith, and for outputting results of said combining process, error-estimating means (21) for receiving as input signals results of said combining process and for providing said error estimates(19), such that the error-estimating means (21) and first combining means (17) operatively interact to effect terrain navigati
    Type: Grant
    Filed: August 1, 2000
    Date of Patent: May 14, 2002
    Assignee: BAE Systems plc
    Inventors: Andrew C Hicks, Ian W Scaysbrook, John R Fountain
  • Publication number: 20010002817
    Abstract: Indicator of a variable for an aircraft. The indicator (1A) according to the invention comprises means (13) for determining first and second target values respectively of a variable and of its derivative with respect to time, and display means (5, 6, 7) which depict on a display screen (7) a means of indication (14) of the first target value, which is arranged in such a way as to indicate this first target value on a graduated scale (8), and a means of indication (16B) of the second target value which is associated at least with an indicator element (11) indicating said derivative so that, when the latter points toward said means of indication (16B), said variable of the aircraft becomes equal to and remains equal to said first target value and said derivative is equal to said second target value.
    Type: Application
    Filed: December 5, 2000
    Publication date: June 7, 2001
    Inventors: Raymond Berlioz, Jean-Pierre Baudry
  • Patent number: 6175315
    Abstract: An aircraft instrument system that informs the pilot of whether, during the takeoff roll, the aircraft's acceleration rate is sufficient to ensure that V1 speed will be achieved at the expected time (and thus distance), and, if not, how far in distance the aircraft is lagging behind the required acceleration schedule.
    Type: Grant
    Filed: November 10, 1998
    Date of Patent: January 16, 2001
    Inventors: Wayne C. Millard, Carl W. Millard
  • Patent number: 6150960
    Abstract: An integrated flight control indicator for providing visual information indicative of aircraft flight parameters has a sky arc and an earth arc which are visually distinguishable from one another. The sky arc and the earth arc cooperate to generally define a circle wherein the relative lengths of the sky arc and the earth arc indicate the pitch of the aircraft. A horizon line extends approximately between the two intersections of the sky arc and the earth arc so as to provide a visual indication of the roll of the aircraft. Other indicia are provided for indicating radar or barometric altitude, vertical speed, heading, ground track, minimum altitude break, etc. Thus, the present invention provides a visual indication suitable for use in instrument panel displays, heads-up display, and helmet-mounted displays.
    Type: Grant
    Filed: November 8, 1999
    Date of Patent: November 21, 2000
    Assignee: Northrop Grumman Corporation
    Inventor: Theodore J. Voulgaris
  • Patent number: 6028536
    Abstract: An integrated flight control indicator for providing visual information indicative of aircraft flight parameters has a sky arc and an earth arc which are visually distinguishable from one another. The sky arc and the earth arc cooperate to generally define a circle wherein the relative lengths of the sky arc and the earth arc indicate the pitch of the aircraft. A horizon line extends approximately between the two intersections of the sky arc and the earth arc so as to provide a visual indication of the roll of the aircraft. Other indicia are provided for indicating radar or barometric altitude, vertical speed, heading, ground track, minimum altitude break, etc. Thus, the present invention provides a visual indication suitable for use in instrument panel displays, heads-up display, and helmet-mounted displays.
    Type: Grant
    Filed: November 16, 1995
    Date of Patent: February 22, 2000
    Assignee: Northrop Grumman Corporation
    Inventor: Theodore J. Voulgaris
  • Patent number: 5912627
    Abstract: The present invention provides a device for indicating an operating point of an aircraft comprising a sensor to measure air speed and a sensor to measure vertical acceleration. The device also comprises a processor in communicative connection with each of the airspeed sensor and the vertical acceleration sensor. The processor is also in communicative connection with a display. The display presents an operating envelope diagram of the aircraft. The display also displays the current operating point of the aircraft relative to the operating envelope diagram. The present invention also provides a method for indicating an operating point of an aircraft in which the operating envelope diagram and the measured operating point of the aircraft are displayed upon the same display.
    Type: Grant
    Filed: October 17, 1997
    Date of Patent: June 15, 1999
    Inventor: William J. Alexander
  • Patent number: 5886649
    Abstract: The present invention relates to an aircraft flight indicator intended to supply a data item regarding the power margin available on at least one engine of the aircraft as a function of the flight conditions. According to the invention, the indicator comprises: a sensor (2) capable of delivering data relating to the speed (Ng) of the gas generator of the engine; means (3) for calculating, using the data relating to the speed (Ng) of the gas generator, a data item .DELTA.Ng representing the difference between the actual value of Ng and the reference value on take-off and for processing said data so that it can be displayed; and display means (4) showing the data relating to the values of the speed Ng of the gas generator and/or of .DELTA.Ng on a display screen (5).
    Type: Grant
    Filed: June 6, 1997
    Date of Patent: March 23, 1999
    Assignee: Eurocopter
    Inventor: Daniel Claude Francois
  • Patent number: 5844504
    Abstract: An altimeter is disclosed which includes an arcuate top portion and an arcuate bottom portion. Side portions connect the arcuate top portion to the arcuate bottom portion. The side portions have a curvature less than a curvature of the top portion or the bottom portion, thus giving the altimeter a narrower footprint while preserving important features of conventional dial-type altimeters. An indicator moves about the perimeter of the altimeter based on altitude information, thus displaying altitude of the aircraft.
    Type: Grant
    Filed: July 22, 1997
    Date of Patent: December 1, 1998
    Assignee: Rockwell International
    Inventor: Tim Etherington